System for calibrating an electromagnetic navigation system

Description

INTRODUCTION

The present disclosure generally relates to electromagnetic navigation, and more particularly, to systems, methods, and computer-readable media for calibrating and optimizing an electromagnetic navigation system.

BACKGROUND

Electromagnetic navigation (EMN) has helped expand medical imaging, diagnosis, prognosis, and treatment capabilities by enabling a location and/or an orientation of a medical device to be accurately determined while the device is within the body of a patient. One example of a medical procedure in which EMN is employed is ELECTROMAGNETIC NAVIGATION BRONCHOSCOPY® (ENB™), which includes a planning phase and a navigation phase. During the planning phase, a computed tomography (CT) scan of the chest of the patient is used to generate a virtual three-dimensional bronchial map of the patient and a planned pathway for the navigation phase. During the navigation phase, a field generating antenna assembly radiates an electromagnetic signal (for example, including one or more cosine waves) throughout a sensing volume within which the chest of the patient is positioned. A practitioner inserts into the airway of the patient an electromagnetic sensor that senses the radiated electromagnetic signal. A computing device captures a sample of the electromagnetic signal during a sampling window, and determines a location and/or an orientation (e.g., relative to the planned pathway) of the electromagnetic sensor based on characteristics (e.g., amplitude and/or phase) of the sampled electromagnetic signal and based on a previously generated mapping of electromagnetic signal measurements at respective sensor locations in the sensing volume.

In some cases—for instance, because of various sensor or antenna inductances, signal chain delays (e.g., analog or digital), and/or any delay from when the synchronization pulse occurs to when the acquisition or electromagnetic field generation actually begins—the sampled electromagnetic signal captured during the sampling window may not include a perfect cosine (or sine) waveform. Also, because of variations in the output current level(s) of transmitter channel(s) and/or in the gain(s) of receiver channel circuitry, the amplitude of the sampled electromagnetic signal captured at a particular location and orientation within the sensing volume relative to the field generating antenna assembly may vary from system to system. Additionally, because generating the mapping of electromagnetic signal measurements at respective sensor locations in the sensing volume can be laborious and time consuming, it may be desirable to reuse in multiple other systems a mapping that was previously generated based on an initial system. In order to do so, however, the initial system and the multiple other systems may require calibration to some common baseline.

Given the foregoing, a need exists for systems and methods for calibrating and/or optimizing an electromagnetic navigation system.

SUMMARY

In accordance with one aspect of the present disclosure, a method for calibrating an electromagnetic navigation system is provided. The method includes receiving, by way of a receiving antenna, a signal having a first magnitude value and a first phase value. A non-calibrated in-phase component and a non-calibrated quadrature component are computed based on the first magnitude value and the first phase value. A calibrated phase value is computed based on the non-calibrated in-phase component and the non-calibrated quadrature component. A calibrated in-phase component is computed based on the calibrated phase value, the non-calibrated in-phase component, and the non-calibrated quadrature component. A calibrated quadrature component is computed based on the calibrated phase value, the non-calibrated in-phase component, and the non-calibrated quadrature component. A calibrated magnitude value is computed based on the calibrated in-phase component. The calibrated phase value and the calibrated magnitude value are stored in a table for use during an electromagnetic navigation procedure.

In another aspect of the present disclosure, the method further includes transmitting the signal by way of a transmitting antenna, with the transmitting and receiving being synchronized to one another.

In yet another aspect of the present disclosure, the method further includes performing a lookup in a sine table and/or a cosine table based on the first magnitude value and the first phase value, with the computing of the non-calibrated in-phase component and/or the non-calibrated quadrature component being based on a result of the lookup.

In a further aspect of the present disclosure, the calibrated phase value is computed according to the equation:

$θ_{cal} = \tan^{- 1} (\frac{Q_{n on - calibrated}}{I_{n on - calibrated}}),$

where θ_calrepresents the calibrated phase value, Q_{non-calibrated}represents the non-calibrated quadrature component, and I_{non-calibrated}represents the non-calibrated in-phase component.

In still another aspect of the present disclosure, the calibrated in-phase component is computed according to the equation:

I_calibrated=I_{non-calibrated}×cos(θ_cal)+Q_{non-calibrated}×sin(θ_cal),

where I_calibratedrepresents the calibrated in-phase component, I_{non-calibrated}represents the non-calibrated in-phase component, θ_calrepresents the calibrated phase value, and Q_{non-calibrated}represents the non-calibrated quadrature component.

In another aspect of the present disclosure, the calibrated quadrature component is computed according to the equation:

Q_calibrated=−I_{non-calibrated}×sin(θ_cal)+Q_{non-calibrated}×cos(θ_cal),

where Q_calibratedrepresents the calibrated quadrature component, I_{non-calibrated}represents the non-calibrated in-phase component, θ_calrepresents the calibrated phase value, and Q_{non-calibrated}represents the non-calibrated quadrature component.

In yet another aspect of the present disclosure, the calibrated magnitude value is computed according to the equation:

$M_{cal} = \frac{1}{I_{calibrated}},$

where M_calrepresents the calibrated magnitude value and I_calibratedrepresents the calibrated in-phase component.

In a further aspect of the present disclosure, the method further includes determining whether the calibrated magnitude value is less than zero. In response to a determination that the calibrated magnitude value is less than zero, a second calibrated phase value is computed, and the calibrated magnitude value, the calibrated in-phase component, and the calibrated quadrature component are recomputed based on the second calibrated phase value.

In still another aspect of the present disclosure, the method further includes determining whether the calibrated magnitude value is less than zero and whether the calibrated phase value is less than or equal to zero. In response to a determination that the calibrated magnitude value is less than zero and the calibrated phase value is less than or equal to zero, a second calibrated phase value is computed according to the equation:

θ_cal′=θ_cal+π,

where θ_cal′ represents the second calibrated phase value and θ_calrepresents the calibrated phase value. The calibrated magnitude value, the calibrated in-phase component, and the calibrated quadrature component are recomputed based on the second calibrated phase value.

In another aspect of the present disclosure, the method further includes determining whether the calibrated magnitude value is less than zero and whether the calibrated phase value is greater than zero. In response to a determination that the calibrated magnitude value is less than zero and the calibrated phase value is greater than zero, a second calibrated phase value is computed according to the equation:

θ_cal′=θ_cal−π,

where θ_cal′ represents the second calibrated phase value and θ_calrepresents the calibrated phase value. The calibrated magnitude value, the calibrated in-phase component, and the calibrated quadrature component are recomputed based on the second calibrated phase value.

In yet another aspect of the present disclosure, the method further includes, during the electromagnetic navigation procedure, receiving a second signal having a second magnitude value and a second phase value; computing a second non-calibrated in-phase component and a second non-calibrated quadrature component based on the second magnitude value and the second phase value; and computing a corrected in-phase component and a corrected quadrature component based on the calibrated phase value, the calibrated magnitude value, the second non-calibrated in-phase component, and the second non-calibrated quadrature component.

In a further aspect of the present disclosure, the corrected in-phase component is computed according to the equation:

I_c=M_cal×((I_non-cal2)×cos(θ_cal)+(Q_non-cal2)×sin(θ_cal)), and

the corrected quadrature component is computed according to the equation:

Q_c=M_cal×(−(I_non-cal2)×sin(θ_cal)+(Q_non-cal2)×cos(θ_cal)),

where I_crepresents the corrected in-phase component, M_calrepresents the calibrated magnitude value, I_non-cal2represents the second non-calibrated in-phase component, θ_calrepresents the calibrated phase value, Q_non-cal2represents the second non-calibrated quadrature component, and Q_crepresents the corrected quadrature component.

In accordance with another aspect of the present disclosure, a system for calibrating an electromagnetic navigation system is provided. The system includes a processor and a memory. The memory includes instructions that, when executed by the processor, cause the processor to receive, by way of a receiving antenna, a signal having a first magnitude value and a first phase value. A non-calibrated in-phase component and a non-calibrated quadrature component are computed based on the first magnitude value and the first phase value. A calibrated phase value is computed based on the non-calibrated in-phase component and the non-calibrated quadrature component. A calibrated in-phase component is computed based on the calibrated phase value, the non-calibrated in-phase component, and the non-calibrated quadrature component. A calibrated quadrature component is computed based on the calibrated phase value, the non-calibrated in-phase component, and the non-calibrated quadrature component. A calibrated magnitude value is computed based on the calibrated in-phase component. The calibrated phase value and the calibrated magnitude value are stored, in a table in the memory, for use during an electromagnetic navigation procedure.

In another aspect of the present disclosure, the memory further stores instructions that, when executed by the processor, cause the processor to compute the calibrated phase value according to the equation:

In a further aspect of the present disclosure, the memory further stores instructions that, when executed by the processor, cause the processor to compute the calibrated in-phase component according to the equation:

I_calibrated=I_{non-calibrated}×cos(θ_cal)+Q_{non-calibrated}×sin(θ_cal),

where I_calibratedrepresents the calibrated in-phase component, I_{non-calibrated}represents the non-calibrated in-phase component, θ_calrepresents the calibrated phase value, and Q_{non-calibrated}represents the non-calibrated quadrature component.

In yet another aspect of the present disclosure, the memory further stores instructions that, when executed by the processor, cause the processor to compute the calibrated quadrature component according to the equation:

Q_calibrated=−I_{non-calibrated}×sin(θ_cal)+Q_{non-calibrated}×cos(θ_cal),

where Q_calibratedrepresents the calibrated quadrature component, I_{non-calibrated}represents the non-calibrated in-phase component, θ_calrepresents the calibrated phase value, and Q_{non-calibrated}represents the non-calibrated quadrature component.

In another aspect of the present disclosure, the memory further stores instructions that, when executed by the processor, cause the processor to compute the calibrated magnitude value according to the equation:

$M_{cal} = \frac{1}{I_{calibrated}},$

where M_calrepresents the calibrated magnitude value and I_calibratedrepresents the calibrated in-phase component.

In a further aspect of the present disclosure, the memory also stores instructions that, when executed by the processor, cause the processor to determine whether the calibrated magnitude value is less than zero. In response to a determination that the calibrated magnitude value is less than zero the processor executes the instructions to compute a second calibrated phase value, and recompute the calibrated magnitude value, the calibrated in-phase component, and the calibrated quadrature component based on the second calibrated phase value.

In yet another aspect of the present disclosure, the memory further stores instructions that, when executed by the processor, cause the processor to, during the electromagnetic navigation procedure, (1) receive a second signal having a second magnitude value and a second phase value; (2) compute a second non-calibrated in-phase component and a second non-calibrated quadrature component based on the second magnitude value and the second phase value; and (3) compute a corrected in-phase component and a corrected quadrature component based on the calibrated phase value, the calibrated magnitude value, the second non-calibrated in-phase component, and the second non-calibrated quadrature component.

In accordance with another aspect of the present disclosure, a non-transitory computer-readable medium is provided. The computer-readable medium stores sequences of instructions that, when executed by a processor, cause the processor to perform a method for calibrating an electromagnetic navigation system. The method includes receiving, by way of a receiving antenna, a signal having a first magnitude value and a first phase value. A non-calibrated in-phase component and a non-calibrated quadrature component are computed based on the first magnitude value and the first phase value. A calibrated phase value is computed based on the non-calibrated in-phase component and the non-calibrated quadrature component. A calibrated in-phase component is computed based on the calibrated phase value, the non-calibrated in-phase component, and the non-calibrated quadrature component, and a calibrated quadrature component is computed based on the calibrated phase value, the non-calibrated in-phase component, and the non-calibrated quadrature component. A calibrated magnitude value is computed based on the calibrated in-phase component. The calibrated phase value and the calibrated magnitude value are stored in a table for use during an electromagnetic navigation procedure.

In accordance with another aspect of the present disclosure, a system including an antenna assembly for calibrating an electromagnetic navigation system is provided. The antenna assembly includes a substrate, multiple pairs of transmit coils, multiple receive coils, multiple input terminals, and multiple output terminals. The substrate includes multiple layers, with each of the transmit coils being deposited on a respective one of the layers, and each of the receive coils being deposited on another respective one of the layers. Each of the pairs of transmit coils corresponds to a respective one of the receive coils. Each of the input terminals is coupled to a respective one of the pairs of transmit coils, and each of the output terminals is coupled to a respective one of the receive coils.

In another aspect of the present disclosure, each of the receive coils of the system is arranged on a respective one of the layers that is located in between a pair of the layers on which the corresponding pair of transmit coils are respectively deposited.

In further aspects of the present disclosure, each of the pairs of transmit coils of the system forms a Helmholtz pair and/or the antenna assembly of the system is an impedance-controlled antenna assembly.

In yet another aspect of the present disclosure, the system further includes a computing device including a processor and a memory. The processor is coupled to the pairs of transmit coils by way of the input terminals, respectively, and is coupled to the receive coils by way of the output terminals, respectively. The memory includes instructions that, when executed by the processor, cause the processor to transmit, by way of at least one of the pairs of transmit coils, a signal having a first magnitude value and a first phase value. The signal is received by way of at least one of the receive coils. A non-calibrated in-phase component and a non-calibrated quadrature component are computed based on the first magnitude value and the first phase value. A calibrated phase value is computed based on the non-calibrated in-phase component and the non-calibrated quadrature component. A calibrated in-phase component is computed based on the calibrated phase value, the non-calibrated in-phase component, and the non-calibrated quadrature component. A calibrated quadrature component is computed based on the calibrated phase value, the non-calibrated in-phase component, and the non-calibrated quadrature component. A calibrated magnitude value is computed based on the calibrated in-phase component. The calibrated phase value and the calibrated magnitude value are stored in a table for use during an electromagnetic navigation procedure.

In another aspect of the present disclosure, the system is configured such that the transmitting of the signal by way of one or more of the pairs of transmit coils and the receiving of the signal by way of one or more of the receive coils are synchronized to one another.

In a further aspect of the present disclosure, the memory stores further instructions that, when executed by the processor, cause the processor to perform a lookup in a sine table and/or a cosine table based on the first magnitude value and the first phase value, and the computing of the non-calibrated in-phase component and/or the non-calibrated quadrature component is further based on a result of the lookup.

In yet another aspect of the present disclosure, the memory stores further instructions that, when executed by the processor, cause the processor to compute the calibrated phase value according to the equation:

$θ_{cal} = \tan^{- 1} (\frac{Q_{n on - calibrated}}{I_{n on - calibrated}}),$

where θ_calrepresents the calibrated phase value, θ_{non-calibrated}represents the non-calibrated quadrature component, and I_{non-calibrated}represents the non-calibrated in-phase component.

In another aspect of the present disclosure, the memory stores further instructions that, when executed by the processor, cause the processor to compute the calibrated in-phase component according to the equation:

I_calibrated=I_{non-calibrated}×cos(θ_cal)+Q_{non-calibrated}×sin(θ_cal),

where I_calibratedrepresents the calibrated in-phase component, I_{non-calibrated}represents the non-calibrated in-phase component, θ_calrepresents the calibrated phase value, and Q_{non-calibrated}represents the non-calibrated quadrature component.

In a further aspect of the present disclosure, the memory further stores instructions that, when executed by the processor, cause the processor to compute the calibrated quadrature component according to the equation:

Q_calibrated=−I_{non-calibrated}×sin(θ_cal)+Q_{non-calibrated}×cos(θ_cal),

where Q_calibratedrepresents the calibrated quadrature component, I_{non-calibrated}represents the non-calibrated in-phase component, θ_calrepresents the calibrated phase value, and Q_{non-calibrated}represents the non-calibrated quadrature component.

In yet another aspect of the present disclosure, the memory further stores instructions that, when executed by the processor, cause the processor to compute the calibrated magnitude value according to the equation:

$M_{cal} = \frac{1}{I_{calibrated}},$

where M_calrepresents the calibrated magnitude value and I_calibratedrepresents the calibrated in-phase component.

In another aspect of the present disclosure, the memory further stores instructions that, when executed by the processor, cause the processor to determine whether the calibrated magnitude value is less than zero, and, in response to a determination that the calibrated magnitude value is less than zero: (1) compute a second calibrated phase value, and (2) recompute the calibrated magnitude value, the calibrated in-phase component, and the calibrated quadrature component based on the second calibrated phase value.

In still a further aspect of the present disclosure, the memory stores further instructions that, when executed by the processor, cause the processor to determine whether the calibrated magnitude value is less than zero and whether the calibrated phase value is less than or equal to zero; and, in response to a determination that the calibrated magnitude value is less than zero and the calibrated phase value is less than or equal to zero: (1) compute a second calibrated phase value according to the equation:

θ_cal′=θ_cal+π,

where θ_cal′ represents the second calibrated phase value and θ_calrepresents the calibrated phase value; and (2) recompute the calibrated magnitude value, the calibrated in-phase component, and the calibrated quadrature component based on the second calibrated phase value.

In another aspect of the present disclosure, the memory further stores instructions that, when executed by the processor, cause the processor to determine whether the calibrated magnitude value is less than zero and whether the calibrated phase value is greater than zero; and, in response to a determination that the calibrated magnitude value is less than zero and the calibrated phase value is greater than zero: (1) compute a second calibrated phase value according to the equation:

θ_cal′=θ_cal−π,

where θ_cal′ represents the second calibrated phase value and θ_calrepresents the calibrated phase value; and (2) recompute the calibrated magnitude value, the calibrated in-phase component, and the calibrated quadrature component based on the second calibrated phase value.

In yet another aspect of the present disclosure, the memory further stores instructions that, when executed by the processor, cause the processor to: (1) receive a second signal having a second magnitude value and a second phase value; (2) compute a second non-calibrated in-phase component and a second non-calibrated quadrature component based on the second magnitude value and the second phase value; and (3) compute a corrected in-phase component and a corrected quadrature component based on the calibrated phase value, the calibrated magnitude value, the second non-calibrated in-phase component, and the second non-calibrated quadrature component.

In a further aspect of the present disclosure, the memory further stores instructions that, when executed by the processor, cause the processor to compute the corrected in-phase component according to the equation:

I_c=M_cal×((I_non-cal2)×cos(θ_cal)+(Q_non-cal2)×sin(θ_cal)),

where I_crepresents the corrected in-phase component, M_calrepresents the calibrated magnitude value, I_non-cal2represents the second non-calibrated in-phase component, θ_calrepresents the calibrated phase value, and Q_non-cal2represents the second non-calibrated quadrature component.

In another aspect of the present disclosure, the memory stores further instructions that, when executed by the processor, cause the processor to compute the corrected quadrature component according to the equation:

Q_c=M_cal×(−(I_non-cal2)×Sin(θ_cal)+(Q_non-cal2)×cos(θ_cal)),

where Q_crepresents the corrected quadrature component, M_calrepresents the calibrated magnitude value, I_non-cal2represents the second non-calibrated in-phase component, θ_calrepresents the calibrated phase value, and Q_non-cal2represents the second non-calibrated quadrature component.

In accordance with another aspect of the present disclosure, a system including an antenna assembly for calibrating an electromagnetic navigation system is provided. The antenna assembly includes a substrate, multiple pairs of transmit coils, multiple pairs of receive coils, multiple input terminals, and multiple output terminals. The substrate includes multiple layers, with each of the transmit coils being deposited on a respective one of the layers and each of the receive coils being deposited on another respective one of the layers. Each of the pairs of transmit coils corresponds to a respective pair of receive coils. The multiple input terminals are coupled to the multiple pairs of transmit coils, respectively, and the multiple output terminals are coupled to the multiple pairs of receive coils, respectively.

In another aspect of the present disclosure, the system further includes a computing device having a processor and a memory. The processor is coupled to the pairs of transmit coils by way of the input terminals, respectively, and is also coupled to the pairs of receive coils by way of the output terminals, respectively. The memory includes instructions that, when executed by the processor, cause the processor to: (1) transmit, by way of at least one of the pairs of transmit coils, a signal having a first magnitude value and a first phase value; (2) receive the signal by way of at least one of the pairs of receive coils; (3) compute a non-calibrated in-phase component and a non-calibrated quadrature component based on the first magnitude value and the first phase value; (4) compute a calibrated phase value based on the non-calibrated in-phase component and the non-calibrated quadrature component; (5) compute a calibrated in-phase component based on the calibrated phase value, the non-calibrated in-phase component, and the non-calibrated quadrature component; (6) compute a calibrated quadrature component based on the calibrated phase value, the non-calibrated in-phase component, and the non-calibrated quadrature component; (7) compute a calibrated magnitude value based on the calibrated in-phase component; and (8) store the calibrated phase value and the calibrated magnitude value in a table for use during an electromagnetic navigation procedure.

In yet another aspect of the present disclosure, each of the pairs of receive coils includes a first receive coil, deposited on a first layer of the plurality of layers, and a second receive coil, deposited on a second layer of the plurality of layers, with the first layer and the second layer each being located between a pair of the layers on which the corresponding pair of transmit coils are respectively deposited.

In accordance with yet a further aspect of the present disclosure, a method for optimizing an electromagnetic navigation system is provided. The method includes generating multiple test signals corresponding to multiple combinations of phase offset values of multiple frequency components, respectively. Based on the test signals, a table is generated, the table including multiple peak signal amplitudes associated with the multiple test signals, respectively. A minimum value of the stored peak signal amplitudes is identified in the table. Based on the table, a determination is made as to which one of the combinations of phase offset values is associated with the minimum value of the stored peak signal amplitudes. The determined combination of phase offset values is stored in a memory for use, during an electromagnetic navigation procedure, in generating a signal including the frequency components having the determined combination of phase offset values, respectively.

In another aspect of the present disclosure, as part of the method, the generating the multiple test signals includes, for each of the combinations of phase offset values, respectively: (1) generating a test signal including the frequency components having the respective combination of phase offset values, respectively; and (2) transmitting the test signal by way of a transmitting antenna.

In a further aspect of the present disclosure, the method further includes, for each of the combinations of phase offset values, respectively: (1) receiving the test signal by way of a receiving antenna; (2) capturing, during a sampling window, a sample of the received test signal; (3) measuring a peak signal amplitude of the captured sample; and (4) storing, in the table, the peak signal amplitude in association with the respective combination of phase offset values.

In yet another aspect of the present disclosure, as part of the method, the generating the test signal, the transmitting the test signal, and/or the receiving the test signal is performed by way of computer-implemented simulation.

In still another aspect of the present disclosure, each of the combinations of phase offset values employed in the method includes multiple phase offset values that correspond to the multiple frequency components, respectively.

In another aspect of the present disclosure, the method further includes generating the multiple combinations of phase offset values based on the multiple frequency components and a phase offset step size. Each of the combinations of phase offset values includes a respective set of phase offset values that correspond to the set of frequency components, respectively, and each of the phase offset values has a value in a range from zero to a maximum value, in increments of the phase offset step size.

In a further aspect of the present disclosure, the method further includes, during the electromagnetic navigation procedure: (1) generating a second signal including the multiple frequency components having the determined combination of phase offset values, respectively; (2) amplifying the second signal so as to have a magnitude greater than a magnitude of the test signal; and (3) transmitting the second signal.

In yet another aspect of the present disclosure, the method further includes, during the electromagnetic navigation procedure, (1) receiving a second signal that includes the multiple frequency components having the determined combination of phase offset values, respectively; and (2) amplifying the second signal so as to have a magnitude greater than a magnitude of the test signal.

In accordance with another aspect of the present disclosure, a system for optimizing an electromagnetic navigation system is provided. The system includes a processor and a memory. The memory stores instructions that, when executed by the processor, cause the processor to: (1) generate multiple test signals corresponding to multiple combinations of phase offset values of multiple frequency components, respectively; (2) generate, based on the multiple test signals, a table that includes a plurality of peak signal amplitudes associated with the multiple test signals, respectively; (3) identify, in the table, a minimum value of the stored peak signal amplitudes; (4) determine, based on the table, which one of the plurality of combinations of phase offset values is associated with the minimum value of the stored peak signal amplitudes; and (5) store the determined combination of phase offset values in the memory for use, during an electromagnetic navigation procedure, in generating a signal including the multiple frequency components having the determined combination of phase offset values, respectively

In another aspect of the present disclosure, the memory of the system further stores instructions that, when executed by the processor, cause the processor to generate the plurality of test signals by, for each of the combinations of phase offset values, respectively: (1) generating a test signal including the multiple frequency components having the respective combination of phase offset values; and (2) transmitting the test signal by way of a transmitting antenna.

In a further aspect of the present disclosure, the memory of the system further stores instructions that, when executed by the processor, cause the processor to, for each of the combinations of phase offset values, respectively: (1) receive the test signal by way of a receiving antenna; (2) capture a sample of the received test signal during a sampling window; (3) measure a peak signal amplitude of the captured sample; and (4) store, in the table, the peak signal amplitude in association with the respective combination of phase offset values.

In yet another aspect of the present disclosure, each of the combinations of phase offset values employed in the system includes multiple phase offset values that correspond to the multiple frequency components, respectively.

In another aspect of the present disclosure, the memory of the system further stores instructions that, when executed by the processor, cause the processor to generate the multiple combinations of phase offset values based on the multiple frequency components and a phase offset step size. In this example, each of the combinations of phase offset values includes a respective set of phase offset values corresponding to the set of frequency components, respectively, and each of the phase offset values has a value in a range from zero to a maximum value, in increments of the phase offset step size.

In a further aspect of the present disclosure, the memory further stores instructions that, when executed by the processor, cause the processor to, during the electromagnetic navigation procedure: (1) generate a second signal including the multiple frequency components having the determined combination of phase offset values, respectively; (2) amplify the second signal so as to have a magnitude greater than a magnitude of the test signal; and (3) transmit the second signal.

In yet another aspect of the present disclosure, the memory further stores instructions that, when executed by the processor, cause the processor to, during the electromagnetic navigation procedure: (1) receive a second signal that includes the multiple frequency components having the determined combination of phase offset values, respectively; and (2) amplify the second signal so as to have a magnitude greater than a magnitude of the test signal.

In accordance with another aspect of the present disclosure, a non-transitory computer-readable medium is provided. The computer-readable medium stores sequences of instructions that, when executed by a processor, cause the processor to perform a method for optimizing an electromagnetic navigation system. The method includes generating multiple test signals corresponding to multiple combinations of phase offset values of multiple frequency components, respectively. Based on the multiple test signals, a table is generated, the table including multiple peak signal amplitudes associated with the multiple test signals, respectively. A minimum value of the stored peak signal amplitudes is identified in the table. Based on the table, a determination is made as to which one of the combinations of phase offset values is associated with the minimum value of the stored peak signal amplitudes. The determined combination of phase offset values is stored in a memory for use, during an electromagnetic navigation procedure, in generating a signal including the frequency components having the determined combination of phase offset values, respectively

In another aspect of the present disclosure, the non-transitory computer-readable medium further stores sequences of instructions that cause the generating of the test signals to include, for each of the combinations of phase offset values, respectively: (1) generating a test signal including the frequency components having the respective combination of phase offset values; and (2) transmitting the test signal by way of a transmitting antenna.

In a further aspect of the present disclosure, the computer-readable medium further stores sequences of instructions that, when executed by the processor, cause the processor to, for each of the combinations of phase offset values, respectively: (1) receive the test signal by way of a receiving antenna; (2) capture a sample of the received test signal during a sampling window; (3) measure a peak signal amplitude of the captured sample; and (4) store the peak signal amplitude in the table in association with the respective combination of phase offset values.

In yet another aspect of the present disclosure, each of the combinations of phase offset values includes multiple phase offset values that correspond to the multiple frequency components, respectively.

In still a further aspect of the present disclosure, the computer readable medium further stores sequences of instructions that, when executed by the processor, cause the processor to generate the combinations of phase offset values based on the multiple frequency components and a phase offset step size. In this example, each of the combinations of phase offset values includes a respective set of phase offset values that correspond to the set of frequency components, respectively, and each of the phase offset values has a value in a range from zero to a maximum value, in increments of the phase offset step size.

Any of the above aspects and embodiments of the present disclosure may be combined without departing from the scope of the present disclosure.

BRIEF DESCRIPTION OF THE DRAWINGS

Objects and features of the presently disclosed systems and methods will become apparent to those of ordinary skill in the art when descriptions of various embodiments are read with reference to the accompanying drawings, of which:

FIG. 1 shows an example electromagnetic navigation system, in accordance with the present disclosure;

FIG. 2 is a flowchart illustrating an example procedure for calibrating an electromagnetic navigation system, in accordance with the present disclosure;

FIG. 3A and FIG. 3B (collectively, FIG. 3) depict example frequency responses of in-phase and quadrature digital filters, in accordance with the present disclosure;

FIG. 4 illustrates example electromagnetic signals and the sine components and cosine components thereof, in accordance with the present disclosure;

FIG. 5A, FIG. 5B, and FIG. 5C (collectively, FIG. 5) illustrate an example frequency multiplexed electromagnetic signal, and results of applying a filter and a Fast Fourier Transform (FFT) to the signal in an example electromagnetic navigation system, in accordance with the present disclosure;

FIG. 6A, FIG. 6B, and FIG. 6C (collectively, FIG. 6) illustrate an example frequency multiplexed electromagnetic signal, and results of applying a filter and an FFT to the signal in a non-calibrated electromagnetic navigation system, in accordance with the present disclosure;

FIG. 7A, FIG. 7B, and FIG. 7C (collectively, FIG. 7) illustrate an example frequency multiplexed electromagnetic signal, and results of applying a filter and an FFT to the signal in a calibrated electromagnetic navigation system, in accordance with the present disclosure;

FIG. 8 shows a diagram of an example Helmholtz coil and corresponding example input and output voltage waveforms, in accordance with the present disclosure;

FIG. 9A, FIG. 9B, and FIG. 9C (collectively, FIG. 9) illustrate aspects of an example antenna assembly of a system for calibrating an electromagnetic navigation system, in accordance with an embodiment of the present disclosure;

FIG. 10 is a flowchart illustrating an example procedure for optimizing an electromagnetic navigation system, in accordance with the present disclosure;

FIG. 11A and FIG. 11B (collectively, FIG. 11) illustrate example electromagnetic signal waveforms before and after optimization, in accordance with the present disclosure;

FIG. 13 is a block diagram of an example computing device for use in various embodiments of the present disclosure.

DETAILED DESCRIPTION

The present disclosure is related to systems and methods for calibrating and/or optimizing an electromagnetic navigation system. The systems and methods herein may be employed to render electromagnetic navigation systems less susceptible to various sensor or antenna inductances, signal chain delays, and/or any delay from when the synchronization pulse occurs to when the acquisition or electromagnetic field generation actually begins, which may otherwise cause the sampled electromagnetic signal captured during the sampling window to not include a perfect cosine (or sine) waveform. The systems and methods herein also may be employed to render electromagnetic navigation systems less susceptible to variations in output current level(s) of transmitter channel(s) and/or in the gain(s) of receiver channel circuitry, which may otherwise cause the amplitude of the sampled electromagnetic signal captured at a particular location and orientation within the sensing volume relative to the field generating antenna assembly to vary from system to system.

Additionally, the systems and methods herein may be employed to calibrate an initial electromagnetic navigation system and multiple other systems to a common baseline, thereby facilitating the reuse, in the multiple other electromagnetic navigation systems, of a mapping of electromagnetic signal measurements at respective sensor locations in the sensing volume that was previously generated based on the initial electromagnetic navigation system.

FIG. 1 illustrates an example electromagnetic navigation (EMN) system 100 provided in accordance with the present disclosure. In general, the EMN system 100 is configured to identify a location and/or an orientation of a medical device being navigated toward a target location within the patient's body by using, among other things, an antenna assembly that generates one or more electromagnetic fields that are sensed by a sensor affixed to the medical device. In some cases, the EMN system 100 is further configured to augment computed tomography (CT) images, magnetic resonance imaging (MRI) images, and/or fluoroscopic images employed during navigation of the medical device through the patient's body toward a target of interest, such as a deceased portion in a luminal network of the patient's lung.

The EMN system 100 includes a catheter guide assembly 110, a bronchoscope 115, a computing device 120, a monitoring device 130, a patient platform 140 (which may be referred to as an EM board), a tracking device 160, and reference sensors 170 (three sensors of which are sometimes collectively referred to as a patient sensor triplet (PST)). The bronchoscope 115 is operatively coupled to the computing device 120 (by way of the tracking device 160) and the monitoring device 130 via respective wired connections (as shown in FIG. 1) or wireless connections (not shown in FIG. 1).

During a navigation phase of an EMN bronchoscopy procedure, the bronchoscope 115 is inserted into the oral cavity of a patient 150 and captures images of the luminal network of the lung. The catheter guide assembly 110 is inserted into the bronchoscope 115 to access the periphery of the luminal network of the lung of the patient 150. The catheter guide assembly 110 may include a catheter or extended working channel (EWC) 111 with an EM sensor 112 affixed to a portion (for example, a distal portion) of the EWC 111. A locatable guide catheter (LG) may be inserted into the EWC 111 with another EM sensor (not shown in FIG. 1) affixed to a portion (for example, a distal portion) of the LG. The EM sensor 112 affixed to the EWC 111 or the EM sensor affixed to the LG is configured to receive a signal based on an electromagnetic field radiated by the antenna assembly 145 (a field generating antenna assembly), and based upon the received signal, is used to determine a location and/or an orientation of the EWC 111 or the LG during navigation through the luminal network of the lung.

The computing device 120, such as a laptop, desktop, tablet, or other suitable computing device, includes a display 122, one or more processors 124, one or more memories 126, an AC current driver 127 for providing AC current signals to the antenna assembly 145, a network interface controller 128, and one or more input devices 129. The particular configuration of the computing device 120 illustrated in FIG. 1 is provided as an example, but other configurations of the components shown in FIG. 1 as being included in the computing device 120 are also contemplated. In particular, in some embodiments, one or more of the components (122, 124, 126, 127, 128, and/or 129) shown in FIG. 1 as being included in the computing device 120 may instead be separate from the computing device 120 and may be coupled to the computing device 120 and/or to any other component(s) of the system 100 by way of one or more respective wired or wireless path(s) to facilitate the transmission of power and/or data signals throughout the system 100. For example, although not shown in FIG. 1, the AC current driver 127 may, in some example aspects, be separate from the computing device 120 and may be coupled to the antenna assembly 145 and/or coupled to one or more components of the computing device 120, such as the processor 124 and the memory 126, by way of one or more corresponding paths.

In some aspects, the EMN system 100 may also include multiple computing devices 120, wherein the multiple computing devices 120 are employed for planning, treatment, visualization, or helping clinicians in a manner suitable for medical operations. The display 122 may be touch-sensitive and/or voice-activated, enabling the display 122 to serve as both an input device and an output device. The display 122 may display two-dimensional (2D) images or three-dimensional (3D) images, such as a 3D model of a lung, to enable a practitioner to locate and identify a portion of the lung that displays symptoms of lung diseases.

The one or more memories 126 store one or more programs and/or computer-executable instructions that, when executed by the one or more processors 124, cause the one or more processors 124 to perform various functions and/or procedures. For example, the processors 124 may calculate a location and/or an orientation of the EM sensor 112 based on the electromagnetic signal that is radiated by the antenna assembly 145 and received by the EM sensor 112. The processors 124 may also perform image-processing functions to cause the 3D model of the lung to be displayed on the display 122. The processors 124 may also generate one or more electromagnetic signals to be radiated by way of the antenna assembly 145. In some embodiments, the computing device 120 may further include a separate graphic accelerator (not shown in FIG. 1) that performs only the image-processing functions so that the one or more processors 124 may be available for other programs. The one or more memories 126 also store data, such as mapping data for EMN, image data, patients' medical record data, prescription data, and/or data regarding a history of the patient's diseases, and/or other types of data.

The mapping data may link multiple grid points, in a coordinate system of an EM volume in which a medical device (e.g., the EWC 111, the LG, treatment probe, or another surgical device) navigates, to the EM signal characteristics (for example, signal strength) that correspond to the grid points, respectively. In this manner, when the EM sensor 112 senses an EM signal having certain characteristics at a particular grid point, the one or more processors 124 may compare the sensed EM signal characteristics to the EM signal characteristics in the mapping data and determine the location and/or orientation of the EM sensor 112 within the EM volume based on a result of the comparison.

As shown in FIG. 1, the platform 140 is configured to provide a flat surface upon which the patient 150 lies during the EMN navigation procedure. The antenna assembly 145, which may also be referred to as an EM field generating device, is arranged upon the platform 140 or is included as a component of the platform 140. The antenna assembly 145 includes one or more antennas, such as planar loop antennas (not shown in FIG. 1). Example aspects of the antenna assembly 145 are described in further detail below.

With the patient 150 lying upon the platform 140, the one or more processors 124 (or another signal generator not shown in FIG. 1) generate and provide to the antenna(s) of the antenna assembly 145 by way of the AC current driver 127 one or more AC current signals that the antenna(s) convert into one or more respective EM signal(s) and radiate in a manner sufficient to surround a portion of the patient 150. In some aspects, the antenna assembly 145 includes a connector that has at least two terminals, and the trace of the antenna (not shown in FIG. 1) has two ends that are coupled to the two connector terminals, respectively, to form a signal communication path from the one or more processors 145 to the antenna.

Having described an example EMN system 100, reference will now be made to FIG. 2, which is a flowchart illustrating an example procedure 200 for calibrating an EMN system such as the EMN system 100, in accordance with the present disclosure. As described in further detail below, aspects of the procedure 200 may be implemented by utilizing the antenna assembly 145 described herein in connection with FIG. 1 and/or the example antenna assembly of a system for calibrating an electromagnetic navigation system described below in connection with FIG. 9. In one example embodiment, the procedure 200 is implemented at least in part by a processor executing instructions stored by a memory.

At S201, a signal having a first magnitude value and a first phase value is transmitted or radiated by way of a transmitting antenna. In various example embodiments, the signal may be a frequency multiplexed signal having multiple frequency components, a time multiplexed signal to share a common transmit and/or receive channel, and/or a combination of a frequency multiplexed signal and a time multiplexed signal. In one embodiment, for example without limitation, three parallel transmit and receive channels may each be employed to transmit and receive frequency multiplexed signals each having three frequency components, yielding a total of nine frequency components.

At S202, the signal transmitted at S201 is received by way of a receiving antenna. In one example embodiment, although not expressly shown in FIG. 2, the transmitting at S201 and the receiving at S202 are synchronized to one another to enable consistent measurements of electromagnetic signals from one sampling window to another.

At S203 the signal received at S202 is amplified, for example by way of one or more receive channel amplifiers, and at S204 the amplified signal is digitized by way of an analog-to-digital converter (ADC).

At S205, the signal digitized at S204 is filtered, for example by way of a digital filter. Example frequency responses of in-phase and quadrature digital filters are shown in FIG. 3A and FIG. 3B, respectively (collectively, FIG. 3). In particular, FIG. 3 shows example frequency responses of in-phase digital filters (FIG. 3A) and quadrature digital filters (FIG. 3B) configured as bandpass filters tuned to pass nine frequency channels of a frequency division multiplexed signal and to reject all other frequency signals. For clarity, the frequency responses of the bandpass filters are illustrated in FIG. 3A and FIG. 3B by way of lines having different colors, respectively. The number of frequency channels illustrated in FIG. 3 is provided by way of example and not limitation. Other numbers of frequency channels are contemplated within the scope of the present disclosure.

At S206, a magnitude and phase of the signal filtered at S205 are determined according to known techniques, such as by detecting a peak amplitude of the filtered signal and/or by measuring a phase of the filtered signal relative to a time of transmission of the signal or another temporal reference point.

At S207, a non-calibrated in-phase (I) component and a non-calibrated quadrature (Q) component of the signal are computed based on the magnitude value and the phase value determined at S206. FIG. 4 illustrates example electromagnetic signals and the in-phase components (e.g., cosine or signal component) and quadrature components (e.g., sine or noise components) thereof, in accordance with an aspect of the present disclosure. In particular, 400-A depicts an example sampled electromagnetic signal that includes a cosine waveform having a magnitude M and a phase offset of zero. 401-A is a graph illustrating that the in-phase component and quadrature component computed based on the waveform of 400-A have magnitudes of M and zero, respectively. 400-B depicts an example sampled electromagnetic signal that includes a sine waveform having a magnitude M and a phase offset of zero. 401-B is a graph illustrating that the in-phase component and quadrature component computed based on the waveform of 400-B have magnitudes of zero and M, respectively. 400-C depicts an example sampled electromagnetic signal that includes a cosine waveform having a magnitude M and having a phase offset of θ. 401-C is a graph illustrating that the in-phase component and quadrature component computed based on the waveform of 400-C have magnitudes of M cos(θ) and M sin(θ), respectively.

In one example, the non-calibrated in-phase component is computed by performing a lookup in cosine table based on the magnitude value and the phase value determined at S206. For example, the cosine table may indicate a cosine component (or a non-calibrated in-phase component) for each combination of a magnitude and a phase value. Similarly, the non-calibrated quadrature component, in one example, is computed by performing a lookup in sine table based on the magnitude value and the phase value determined at S206. For example, the sine table may indicate a sine component (or a non-calibrated quadrature component) for each combination of a magnitude and a phase value.

At S208, a calibrated phase value is computed based on the non-calibrated in-phase component and the non-calibrated quadrature component computed at S207. In one example, the calibrated phase value is computed according to the equation:

$\begin{matrix} θ_{cal} = \tan^{- 1} (\frac{Q_{n on - calibrated}}{I_{n on - calibrated}}) & (1) \end{matrix}$

where θ_calrepresents the calibrated phase value, and Q_{non-calibrated}and I_{non-calibrated}represent the non-calibrated quadrature component and the non-calibrated in-phase component, respectively, computed at S207.

At S209, a calibrated in-phase component is computed based on the calibrated phase value computed at S208 and the non-calibrated in-phase component and the non-calibrated quadrature component computed at S207. In one example, the calibrated in-phase component is computed according to the equation:

I_calibrated=I_{non-calibrated}×cos(θ_cal)+Q_{non-calibrated}×sin(θ_cal) (2)

where I_calibratedrepresents the calibrated in-phase component, θ_calrepresents the calibrated phase value computed at S208, and I_{non-calibrated}and Q_{non-calibrated}represent the non-calibrated in-phase component the non-calibrated quadrature component computed at S207.

At S210, a calibrated quadrature component is computed based on the calibrated phase value computed at S208 and the non-calibrated in-phase component and non-calibrated quadrature component computed at S207. In one example, the calibrated quadrature component is computed according to the equation:

Q_calibrated=−I_{non-calibrated}×sin(θ_cal)+Q_{non-calibrated}×cos(θ_cal) (3)

where Q_calibratedrepresents the calibrated quadrature component, θ_calrepresents the calibrated phase value computed at S208, and I_{non-calibrated}and Q_{non-calibrated}represent the non-calibrated in-phase component and the non-calibrated quadrature component, respectively, computed at S207.

At S211, a calibrated magnitude value is computed based on the calibrated in-phase component computed at S209. In one example the calibrated magnitude value is computed according to the equation:

$\begin{matrix} M_{cal} = \frac{1}{I_{calibrated}} & (4) \end{matrix}$

where M_calrepresents the calibrated magnitude value and I_calibratedrepresents the calibrated in-phase component computed at S209.

In some example embodiments, a determination is made as to whether the calibrated magnitude value computed at S211 is less than zero, and, in response to a determination that the calibrated magnitude value is less than zero a second calibrated phase value is computed, and the calibrated magnitude value, the calibrated in-phase component, and the calibrated quadrature component are recomputed based on the second calibrated phase value.

For instance, at S212, a determination is made as to whether the calibrated magnitude value computed at S211 is less than zero and whether the calibrated phase value computed at S208 is less than or equal to zero. If it is determined at S212 that the calibrated magnitude value is less than zero and the calibrated phase value is less than or equal to zero, then at S213 a second calibrated phase value is computed according to the equation:

θ_cal′=θ_cal+π (5)

where θ_cal′ represents the second calibrated phase value, and Kcal represents the calibrated phase value computed at S208. For convenience, the phase values and equations herein are described in terms of radians, although one of skill in the art would appreciate how to describe the phase values and equations herein in terms of degrees instead of radians. The procedures of S207 through S211 are then repeated (for example, the calibrated in-phase component, and the calibrated quadrature component are recomputed) based on the second calibrated phase value computed at S213.

At S214, a determination is made as to whether the calibrated magnitude value computed at S211 is less than zero and whether the calibrated phase value computed at S208 is greater than zero. If it is determined at S214 that the calibrated magnitude value is less than zero and the calibrated phase value is greater than zero, then at S215 a second calibrated phase value is computed according to the equation:

θ_cal′=θ_cal−π (6)

where θ_cal′ represents the second calibrated phase value and Kcal represents the calibrated phase value. The procedures of S207 through S212 are then repeated (for example, the calibrated magnitude value, the calibrated in-phase component, and the calibrated quadrature component are recomputed) based on the second calibrated phase value computed at S215.

At S216, the calibrated phase value computed at S208 and the calibrated magnitude value computed at S211 are stored in association with one another in a table (for example, in a memory) for use during an electromagnetic navigation procedure. Table 1 below illustrates an example of a table that may be populated with calibrated phase values and calibrated magnitude values computed at S208 and S211, respectively, and stored at S216, for an example system having 9 frequencies or channels.

TABLE 1

Frequency/Channel

θ_cal

Index
M_cal
(radians or degrees)

1
M_cal1
θ_cal1

2
M_cal2
θ_cal2

3
M_cal3
θ_cal3

4
M_cal4
θ_cal4

5
M_cal5
θ_cal5

6
M_cal6
θ_cal6

7
M_cal7
θ_cal7

8
M_cal8
θ_cal8

9
M_cal9
θ_cal9

At S217, a determination is made as to whether steps of the calibration procedure 200 are to be repeated for an additional frequency (for instance, another frequency component of a frequency division multiplexed signal) and/or an additional channel (for instance, an additional parallel channel of a multiple channel antenna assembly system). If it is determined at S217 that steps of the calibration procedure 200 are to be repeated for an additional frequency and/or channel, then at S218 a frequency index and/or a channel index is incremented, and the procedures of S201 through S217 are repeated for an additional frequency and/or channel.

At S219, the calibrated phase value and the calibrated magnitude value stored at S216 are utilized in an electromagnetic navigation procedure. For instance, in one example, during the electromagnetic navigation procedure, a second signal having a second magnitude value and a second phase value is generated, transmitted and received in the manner described above in connection with S201 and S202. A second non-calibrated in-phase component and a second non-calibrated quadrature component are computed based on the second magnitude value and the second phase value. A corrected in-phase component and a corrected quadrature component are then computed based on the computed calibrated phase value, calibrated magnitude value, second non-calibrated in-phase component, and second non-calibrated quadrature component. In one example, the corrected in-phase component is computed according to the equation:

I_c=M_cal×((I_non-cal2)×cos(θ_cal)+(Q_non-cal2)×sin(θ_cal)) (7)

and the corrected quadrature component is computed according to the equation:

Q_c=M_cal×(−(I_non-cal2)×sin(θ_cal)+(Q_non-cal2)×cos(θ_cal)) (8)

where I_crepresents the corrected in-phase component, M_calrepresents the calibrated magnitude value, I_non-cal2represents the second non-calibrated in-phase component, θ_calrepresents the calibrated phase value, Q_non-cal2represents the second non-calibrated quadrature component, and Q_crepresents the corrected quadrature component.

As can be appreciated in view of the present disclosure, the calibration procedure 200 described herein can be employed to calibrate an electromagnetic navigation system, for instance, (1) to reduce the sensitivity of the electromagnetic navigation system to sources of inconsistency, such as sensor or antenna inductances, signal chain delays, and/or delays from when the synchronization pulse occurs to when the acquisition or electromagnetic field generation actually begins—that may otherwise cause a sampled electromagnetic signal captured during the sampling to not include a perfect cosine (or sine) waveform. Also, the calibration procedure 200 can also be employed to calibrate an electromagnetic navigation system to reduce its sensitivity to variations in the output current level(s) of transmitter channel(s) and/or in the gain(s) of receiver channel circuitry, which may otherwise cause the amplitude of the sampled electromagnetic signal captured at a particular location and orientation within the sensing volume relative to the field generating antenna assembly to vary from system to system. Additionally, the calibration procedure 200 may be employed to calibrate multiple electromagnetic navigation systems (for instance, being based on similar or substantially identical field generating antenna assembly 145 designs) to be calibrated to a common baseline, thereby enabling reuse in multiple electromagnetic navigation systems of a mapping that was previously generated based on an initial electromagnetic navigation system, avoiding the need to generate new mappings of electromagnetic signal measurements at respective sensor locations in the sensing volume for each electromagnetic navigation system.

Having described an example procedure 200 for calibrating an electromagnetic navigation system, reference will now be made to FIGS. 5 through 7, which illustrate an example frequency multiplexed electromagnetic signal, and results of applying a filter and an FFT to the signal in various example electromagnetic navigation systems, in accordance with aspects of the present disclosure. In particular, graph 500 of FIG. 5A shows a captured sample of an example frequency division multiplexed (FDM) electromagnetic signal that includes nine cosine functions each having a different frequency (frequency components) and each having an amplitude of 1. In addition to magnitude values, graph 501 of FIG. 5B illustrates the in-phase (I) components and quadrature (Q) components that are computed, in a model electromagnetic navigation system, based on the signal shown in graph 500 after the signal has been filtered, for example, by way of in-phase and quadrature digital filters having the example frequency responses shown in FIG. 3. Graph 502 in FIG. 5C illustrates a result of applying an FFT to the signal shown in graph 500 in the model electromagnetic navigation system. As can be seen in graph 501, each of the nine frequency components has magnitude and in-phase component values of 1 and a quadrature component value of zero.

Graph 600 of FIG. 6A and graph 700 of FIG. 7A each show a captured sample of an example frequency division multiplexed (FDM) electromagnetic signal that includes nine cosine functions that are each intended to have a different frequency (frequency components) and an amplitude of 1, but due to variations and imperfections in the system, may have variations in amplitude and phase offset. In addition to magnitude values, graph 601 of FIG. 6B illustrates the in-phase (I) components and quadrature (Q) components that are computed, in a non-calibrated electromagnetic navigation system (e.g., a system that has not been calibrated based on the calibration procedure 200), based on the signal shown in graph 600A after the signal has been filtered. Graph 602 in FIG. 6C illustrates a result of applying an FFT to the signal shown in graph 600 in the non-calibrated electromagnetic navigation system. As can be seen in graph 601, the nine frequency components each have a magnitude value of 1 but have varying in-phase and quadrature component values, due to the variations or imperfections in the captured signal.

In addition to magnitude values, graph 701 of FIG. 7B illustrates the in-phase (I) components and quadrature (Q) components that are computed, in a calibrated electromagnetic navigation system (e.g., a system that has been calibrated based on the calibration procedure 200), based on the signal shown in graph 600 after the signal has been filtered. Graph 702 in FIG. 7C illustrates a result of applying an FFT to the signal shown in graph 600 in the calibrated electromagnetic navigation system. As can be seen in graph 701, each of the nine frequency components has magnitude and in-phase component values of 1 and a quadrature component value of zero, despite the imperfections in the captured signal.

Reference will now be made to FIG. 8 and FIG. 9, which illustrate aspects of an example system for calibrating electromagnetic navigation systems, in accordance with the present disclosure. In particular, FIG. 8 shows a diagram of an example circuit 800 that includes a pair of transmitting coils 801-A and 801-B (collectively 801) (which may be, in some examples, a Helmholtz pair) coupled to an input terminal 802 (which in this example includes two conductors, but may in some embodiments include any number of conductors), a corresponding receive coil 803 coupled to an output terminal 804 (which in this example includes two conductors, but may in some embodiments include any number of conductors). Although the circuit 800 of FIG. 8 includes a single receive coil 803, this is merely provided as an example. As described in further detail below, other example embodiments are contemplated in which the circuit 800 includes multiple receive coils per receive channel, for example, multiple receive coils or receive coil pairs coupled to one another in a series circuit. The graph 805 illustrates an example input voltage signal (or waveform) that may be applied to the pair of transmit coils 801 by way of the input terminal 802, thereby causing the transmit coils 801 to radiate an electromagnetic field. In the example of graph 805, the input voltage signal is a sine waveform. The graph 806 illustrates an example output voltage signal (or waveform) that the radiated electromagnetic field may induce in the output terminal 804 by way of the receive coil 803. In the example of graph 806, the output voltage signal, which is induced based on the input sine waveform, is a cosine waveform. As described in further detail below, one or more circuits such as the circuit 800 may be included in an antenna assembly for calibrating an electromagnetic navigation system, in accordance with aspects of the present disclosure.

FIG. 9A, FIG. 9B, and FIG. 9C (collectively, FIG. 9) illustrate aspects of an example antenna assembly 903 that may be included in a system for calibrating an electromagnetic navigation system, such as the electromagnetic navigation system 100, in accordance with the present disclosure. Although not shown in FIG. 9, in some embodiments, the system for calibrating the electromagnetic navigation system includes several of the components that are described above in connection with FIG. 1, such as for example the computing device 120, the tracking module 160, the patient platform 140, and/or other components. In some embodiments, the system for calibrating an electromagnetic navigation system may employ the field generating antenna assembly 145 and the EM sensor 112 to calibrate one or more transmit and receive channel(s) of the electromagnetic navigation system 100, for instance according to the procedure 200 described herein. In other embodiments, in lieu of the field generating antenna assembly 145 and the EM sensor 112, the system for calibrating the electromagnetic navigation system includes the antenna assembly 903 of FIG. 9C, which includes one or more circuits, such as the circuit 800 of FIG. 8, each configured to be employed to calibrate a corresponding transmit and/or receive channel of the electromagnetic navigation system 100, for instance according to the procedure 200 described herein. In some examples, the computing device 120 is coupled to the antenna assembly 903 by way of transmit and receive channels thereof, and is configured to transmit and receive signals by way of the transmit and receive channels, respectively, to calibrate each transmit and receive channel.

With reference to FIG. 9C, a top view of the example antenna assembly 903 as fully fabricated is shown. In some embodiments, the antenna assembly 903 includes a substrate having multiple layers. FIG. 9A shows an exploded view 901 of the antenna assembly 903 that illustrates an example arrangement of the multiple layers of the substrate of the antenna assembly 903 (which arrangement may be referred to as a printed circuit board (PCB) stackup). The arrangement of the multiple layers of the substrate of the antenna assembly 903 that is shown in view 901 is provided as one example PCB stackup, but other PCB stackups are contemplated, for instance, with channels having single-receive-coil configurations and/or channels having multiple-receive-coil configurations, as described in further detail below.

FIG. 9B shows a plan view 902 of a single layer of the antenna assembly 903. The antenna assembly 903 includes multiple pairs of transmit coils and multiple receive coils (and/or receive coil pairs, not explicitly shown in FIG. 9), with each pair of transmit coils corresponding to a respective one of the receive coils (or receive coil pairs). In one embodiment, each set of a pair of transmit coils and a corresponding receive coil (or receive coil pair) corresponds to a particular transmit and receive channel (or a particular transmit and receive frequency) of the electromagnetic navigation system being calibrated. For instance, for an electromagnetic navigation system that includes N transmit channels and N receive channels, the antenna assembly 903 includes N pairs of transmit coils and N corresponding receive coils and/or receive coil pairs, respectively.

Although not explicitly shown in the view 901, in some example embodiments, each set of a pair of transmit coils and a corresponding receive coil of the antenna assembly 903 (for instance the pair of transmit coils 801-A₁, 801-B₁and the corresponding receive coil 803₁shown in view 901) is formed as the pair of transmitting coils 801 (which may be, in some examples, a Helmholtz pair) and the corresponding receive coil 803 shown in FIG. 8. More particularly, with reference to the view 901, the pair of transmit coils 801-A₁and 801-B₁corresponds to the receive coil 803₁, the pair of transmit coils 801-A_Nand 801-B_Ncorresponds to the receive coil 803_N, and so forth. Each pair of transmitting coils 801 is coupled, via printed circuit board pads, traces, and/or vias for example (not explicitly shown in FIG. 9), to a corresponding input terminal 802₁through 802_N, respectively, and each receive coil (or, in some examples, each receive coil pair) 803₁through 803_Nis coupled, via printed circuit board pads, traces, and/or vias for example (not explicitly shown in FIG. 9), to a corresponding output terminal 804₁through 804_N, respectively. In this way, the computing device 120 can be coupled to particular coils of the transmit coils 801 and the receive coils 803 by way of respective terminals of the input terminals 802 and the output terminals 804.

As noted above, in various example embodiments, the antenna assembly 903 may include a single receive coil per channel (which is referred to as a single-receive-coil configuration) or multiple receive coils per channel (which is referred to as a multiple-receive-coil configuration). The example arrangement of the multiple layers of the substrate of the antenna assembly 903 shown in the view 901 illustrates a single-receive-coil configuration, where each channel has a single receive coil 803₁through 803_N, respectively. As indicated in the view 901, each of the transmit coils (transmit coil 801-A₁through transmit coil 801-A_Nand transmit coil 801-B₁through transmit coil 801-B_N) is deposited on a respective one of the layers of the substrate, and each of the receive coils (receive coil 803₁through receive coil 803_N) is deposited on a respective one of the layers of the substrate. In the example arrangement of view 901, each of the receive coils 803₁through 803_Nis arranged on a respective one of the substrate layers located in between (though not necessarily immediately adjacent to) the pair of substrate layers upon which the corresponding pair of transmit coils 801 are respectively deposited. For instance, in the single-receive-coil configuration, the receive coil 803₁is arranged on a substrate layer located in between the pair of substrate layers upon which the corresponding pair of transmit coils 801-A₁and 801-B₁are respectively deposited; and the receive coil 803_Nis arranged on a substrate layer that is located in between the pair of substrate layers upon which the corresponding pair of transmit coils 801-A_Nand 801-B_Nare respectively deposited.

Alternatively, although not explicitly shown in FIG. 8 or FIG. 9, in a multiple-receive-coil configuration example embodiment, each channel includes multiple (for example, a pair of) receive coils. For instance, a first channel includes a pair of series-connected receive coils arranged on a pair of substrate layers, respectively, both of which are located between the pair of substrate layers upon which the corresponding pair of transmit coils are respectively deposited, and so forth for other channels. In this example, the pair of receive coils which are deposited on different layers of the substrate, are coupled to one another in a series circuit by way of printed circuit board traces and a via that traverses the layers of the substrate, for instance. The antenna assembly 903, in some embodiments, is an impedance-controlled antenna assembly, for instance including outer layers 904 and 905 that each include traces and/or components configured to control an impedance of the antenna assembly.

As mentioned above, in various example embodiments, each receive coil 803 is implemented as a single receive coil or as a set of multiple receive coils, such as a pair of two receive coils coupled to one another in a series circuit topology. In some examples, different receive coil configurations are used to calibrate receive channels configured for different types of sensors, respectively. For instance, a receive coil configuration that includes a single receive coil (a single-receive-coil configuration) is used to calibrate a receive channel or port that, after calibration, is intended to be coupled to an EWC that includes a single coil. Alternatively, a receive coil configuration that includes multiple receive coils (a multiple-receive-coil configuration) is used to calibrate a receive channel or port that, after calibration, is intended to be coupled to a sensor, such as an LG or a PST, that includes multiple-coil assemblies, such as a pair of series-connected coils. In some example embodiments, at least one of the connectors 804 (for example, 804₁) is coupled to one of the receive coils 803₁through 803_Nand is useable for single-receive-coil calibration, and at least another one of the connectors 804 (for example, 804_N) is coupled to a set of multiple receive coils (for instance, a series-connected pair of receive coils each deposited on a respective one of the layers of the substrate, not shown in FIG. 9) and is usable for multiple-receive-coil calibration. Thus, by way of the different connectors 804₁through 804_N, the antenna assembly 903 facilitates calibration of receive channels that employ different receive coil configurations.

In some example aspects, the system for calibrating the electromagnetic navigation system includes a computing device, such as the computing device 120 and/or the computing device 1300 described herein, which in turn includes a processor (for example processor 124 or 1304) and a memory (for example, memory 126 or 1302) coupled to the plurality of pairs of transmit coils 801 by way of the plurality of input terminals 802, respectively, and coupled to the plurality of receive coils 803 by way of the plurality of output terminals 804, respectively. The memory may include instructions (for example, including the data 1314 and/or the application 1316) that, when executed by the processor, cause the processor to perform the calibration procedure 200 described herein. The memory may further includes instructions that, when executed by the processor, cause the processor to synchronously transmit and receive one or more electromagnetic signal(s).

FIG. 10 is a flowchart illustrating an example procedure 1000 for optimizing an electromagnetic navigation system, in accordance with the present disclosure. In general, as described in further detail below, the procedure 1000 may be employed to determine, for a particular frequency division multiplexed signal having multiple frequency components, a combination of respective phase offsets for the frequency components (which may be referred to as an optimized combination of phase offsets) that, when the frequency components are superimposed, would yield a peak amplitude that is lower than an amplitude that would result without utilizing such phase offsets. Employing, in an electromagnetic navigation system, the phase offset combination identified by way of the procedure 1000 mitigates saturation of the ADC(s) of the system, and further enables transmit and/or receive channel gains to be increased, thereby increasing signal-to-noise ratio (SNR) and/or maximizing utilization of the dynamic range available from the ADC(s). As described below, in some example embodiments the procedure 1000 includes generating test signals and radiating or transmitting those test signals by way of an antenna, such as the antenna assembly 145 or the antenna assembly 903, and receiving and measuring samples of the transmitted test signals to determine optimal phase offsets. In other example embodiments, in lieu of radiating phase shifted waveforms using an antenna, one or more steps of the procedure 1000 are implemented by a computer (for example, by retrieving, via a processor, instructions stored in a memory and executing those instructions) to generate simulated waveforms with various phase offsets, thereby reducing the time required to determine optimal phase offsets.

Referring now to FIG. 10, at S1001, various parameters, such as for example a frequency index, a channel index, and/or other parameters, are initialized. In one example, the initialization of parameters at S1001 facilitates repetition of steps of the procedure 1000 for multiple frequencies, channels, and/or combinations of phase offset values. For instance, at S1001 a frequency index may be initialized to an initial value (e.g., 1) and a phase offset combination may be initialized to an initial value (e.g., corresponding to a phase offset combination where each phase offset equals zero).

At S1002, a frequency multiplexed electromagnetic test signal is generated, including multiple frequency components that are superimposed and that have respective phase offset values of the phase offset combination initialized at S1001. The test signal is transmitted (or radiated) by way of a transmitting antenna, such as the antenna assembly 145 or the antenna assembly 903, or is generated within a simulation environment as described above.

At S1003, the test signal radiated at S1002 is received by way of a receiving antenna, and a sample of the received test signal is captured during a sampling window. As described in further detail below, FIG. 11 illustrates example electromagnetic signal waveforms that may be captured at S1003.

At S1004, a peak signal amplitude of the captured sample is measured. At S1005, the peak signal amplitude measured at S1004 is stored in a table in association with the respective combination of phase offset values used at S1002 to generate the signal.

At S1006, a determination is made as to whether steps of the procedure 1000 are to be repeated for an additional phase offset combination for the frequency components. In one example, steps of the procedure 1000 are repeated for each possible combination of phase offset values ranging from zero to a maximum value (e.g., 2π a radians or 360°) in increments of a phase offset step size. In such an example, the determination at S1006 of whether steps of the procedure 1000 are to be repeated is made based on whether the table populated at S1005 includes peak signal amplitude values for all possible combinations of phase offset values for the frequency components of the signal generated at S1002 given the particular phase offset step size. If the table populated at S1005 does not include peak signal amplitude values for all possible combinations of phase offset values for the frequency components of the signal generated at S1002 given the particular phase offset step size, then it is determined at S1006 that steps of the procedure 1000 are to be repeated for an additional phase offset combination (“YES” at S1006).

At S1007, the additional phase offset combination is set and the procedures of S1002 through S1006 are repeated based on the additional phase offset combination. In this manner, the table may be populated at S1005 for each possible combination of phase offset values for the frequency components, respectively, given the phase offset step size. In one example, the set of possible combinations of phase offset values is generated based on the frequency components of the signal and the phase offset step size. In particular, each of the combinations of phase offset values includes a respective set of phase offset values that correspond to the frequency components, respectively. Each of the phase offset values may have a value in a range from zero to a maximum value (e.g., a radians or 360°), in increments of the phase offset step size. For example, if the phase offset step size were 90°, the possible phase offset values for each frequency component would be 0°, 90°, 180°, and 270°. In this example, the number of possible phase offset values N_θ for a particular frequency component would be 4. Thus, for a frequency multiplexed signal having a particular number of frequencies components N_F, with each frequency component having a number of possible phase offset values N_θ, the total number of possible combinations of phase offsets N_Cis computed according to the equation:

N_C=N_θ^N^F (9)

If, on the other hand, the table populated at S1005 includes peak signal amplitude values for all possible combinations of phase offset values for the frequency components of the signal generated at S1002 given the particular phase offset step size, then it is determined at S1006 that steps of the procedure 1000 are not to be repeated for an additional phase offset combination (“NO at S1006”).

At S1008, a minimum value among the peak signal amplitudes stored at S1005 in the completed table is identified. At S1009, based on the table, a determination is made as to which one of the plurality of combinations of phase offset values in the table is associated with the minimum value of the stored peak signal amplitudes identified at S1008.

At S1010, the combination of phase offset values determined at S1009 is stored in a table, for example in a memory, for use during an electromagnetic navigation procedure in generating an electromagnetic signal that includes the plurality of frequency components having the determined combination of phase offset values, respectively. Table 2 below illustrates an example of a table that may be populated with the combination of phase offset values θ_offfor the frequency components stored at S1010, for an example system having 9 frequencies or channels.

TABLE 2

Frequency/Channel
Frequency
θ_off

Index
(Hz)
(radians or degrees)

1
F₁
θ_off1

2
F₂
θ_off2

3
F₃
θ_off3

4
F₄
θ_off4

5
F₅
θ_off5

6
F₆
θ_off6

7
F₇
θ_off7

8
F₈
θ_off8

9
F₉
θ_off9

At S1011, gain values of one or more transmit and/or receive amplifiers in the electromagnetic navigation system may be increased. during the electromagnetic navigation procedure: generating a second signal including the plurality of frequency components having the determined combination of phase offset values, respectively; amplifying the second signal so as to have a magnitude greater than a magnitude of the test signal; and transmitting the second signal. 23. The method of claim 20, further comprising: during the electromagnetic navigation procedure: receiving a second signal that includes the plurality of frequency components having the determined combination of phase offset values, respectively; and amplifying the second signal so as to have a magnitude greater than a magnitude of the test signal.

FIG. 11A and FIG. 11B (collectively, FIG. 11) illustrate example electromagnetic signal waveforms before and after optimization according to the procedure 1000, in accordance with the present disclosure. In particular, the signal waveform 1101 of FIG. 11A shows multiple separate frequency components that may be generated at S1002 without employing the combination of phase offset values determined at S1009 (for example, employing phase offset values of zero for each of the frequency components). The signal waveform 1102 of FIG. 11A represents a combination of the multiple frequency components of the waveform 1101 superimposed upon one another. The superimposed waveform 1102 has a relatively high peak amplitude that may saturate an ADC and/or make limited use of the dynamic range available from an ADC.

The signal waveform 1103 of FIG. 11B shows multiple separate frequency components that may be generated at S1002 employing the combination of phase offset values determined at S1009. The signal waveform 1104 of FIG. 11B represents a combination of the multiple frequency components of the waveform 1103 superimposed upon one another. The superimposed waveform 1104 has a peak amplitude that is lower than that of the superimposed waveform 1102, and may thus mitigate or avoid saturation of the ADC and/or make more effective use of the dynamic range available from an ADC, for example, by enabling one or more gains of the transmit and/or receive channel to be increased as described above in connection with S1011.

FIG. 12A, FIG. 12B, and FIG. 12C (collectively, FIG. 12) illustrate an example frequency multiplexed electromagnetic signal, and results of applying a filter and an FFT to the signal in an optimized electromagnetic navigation system (for instance an electromagnetic navigation system optimized according to the procedure 1000 herein), in accordance with the present disclosure. In particular, the waveform 1201 of FIG. 12A is generated using the same frequency components used to generate the waveform 600 of FIG. 6, except using the combination of phase offsets determined at S1009. Graph 1202 of FIG. 12B illustrates the in-phase (I) components and quadrature (Q) components that are computed based on the signal shown in graph 1201 after the signal has been filtered. Graph 1203 of FIG. 12C illustrates a result of applying an FFT to the signal shown in graph 1201. The in-phase (I) components and quadrature (Q) components that are computed based on the signal shown in graph 1201 after the signal has been filtered are the same as those in the graph 701 of FIG. 7, illustrating that, in one example embodiment, advantages of calibration and optimization may both be realized in a system that has been both calibrated according to the procedure 200 and optimized according to the procedure 1000.

Turning now to FIG. 13, there is shown a block diagram of a computing device 1300, which can be used as the EMN system 100, the computing device 120, the tracking device 160, and/or a computer performing any of the procedures herein, such as for example the procedures 200 and/or 1000 described herein in connection with FIG. 2 and/or FIG. 10, respectively. The computing device 1300 may include one or more of each of the following components: a memory 1302, a processor 1304, a display 1306, a network interface controller 1308, an input device 1310, and/or an output module 1312.

The memory 1302 includes any non-transitory computer-readable storage media for storing data and/or software that is executable by the processor 1304 and which controls the operation of the computing device 1300. In an embodiment, the memory 1302 may include one or more solid-state storage devices such as flash memory chips. Alternatively, or in addition to the one or more solid-state storage devices, the memory 1302 may include one or more mass storage devices connected to the processor 1304 through a mass storage controller (not shown in FIG. 13) and a communications bus (not shown in FIG. 13). Although the description of computer-readable media contained herein refers to a solid-state storage, it should be appreciated by those skilled in the art that computer-readable storage media can be any available media that can be accessed by the processor 1304. That is, computer readable storage media include non-transitory, volatile and non-volatile, removable and non-removable media implemented in any method or technology for storage of information such as computer-readable instructions, data structures, program modules or other data. For example, computer-readable storage media include RAM, ROM, EPROM, EEPROM, flash memory or other solid state memory technology, CD-ROM, DVD, Blu-Ray or other optical storage, magnetic cassettes, magnetic tape, magnetic disk storage or other magnetic storage devices, or any other medium which can be used to store the desired information and which can be accessed by the computing device 1300.

The memory 1302 may store application 1316 and/or data 1314. The application 1316 may, when executed by the processor 1304, cause the display 1306 to present user interface 1318 on the display 1306.

The processor 1304 may be a general purpose processor, a specialized graphic processing unit (GPU) configured to perform specific graphics processing tasks while freeing up the general purpose processor to perform other tasks, a programmable logic device such as a field programmable gate array (FPGA) or complex programmable logic device (CPLD), and/or any number or combination of such processors or devices configured to work independently or cooperatively.

The display 1306 may be touch-sensitive and/or voice-activated, enabling the display 1306 to serve as both an input and output device. Alternatively, a keyboard (not shown), mouse (not shown), or other data input devices may be employed.

The network interface 1308 may be configured to connect to a network, such as a local area network (LAN) including a wired network and/or a wireless network, a wide area network (WAN), a wireless mobile network, a Bluetooth network, and/or the Internet. The computing device 1300 may receive updates to its software, for example, application 1316, via the network interface controller 1308. The computing device 1300 may also display notifications on the display 1306 that a software update is available.

In another aspect, the computing device 1300 may receive computed tomographic (CT) image data of a patient from a server, for example, a hospital server, Internet server, or other similar servers, for use during surgical planning. Patient CT image data may also be provided to the computing device 1300 via a removable memory (not shown in FIG. 13).

Input device 1310 may be any device by means of which a user may interact with the computing device 1300, such as, for example, a mouse, keyboard, foot pedal, touch screen, and/or voice interface.

Output module 1312 may include any connectivity port or bus, such as, for example, parallel ports, serial ports, universal serial busses (USB), or any other similar connectivity port known to those skilled in the art.

The application 1316 may be one or more software programs stored in the memory 1302 and executed by the processor 1304 of the computing device 1300. One or more software programs in the application 1316 may be loaded from the memory 1302 and executed by the processor 1304 to perform any of the procedures herein, such as for example the procedures 200 and/or 1000 described herein in connection with FIG. 2 and/or FIG. 10, respectively.

The application 1316 may be installed directly on the computing device 1300, or may be installed on another computer, for example a central server, and opened on the computing device 1300 via the network interface 1308. Application 1316 may run natively on the computing device 1300, as a web-based application, or any other format known to those skilled in the art. In some embodiments, the application 1316 will be a single software program having all of the features and functionality described in the present disclosure. In other embodiments, the application 1316 may be two or more distinct software programs providing various parts of these features and functionality. For example, the application 1316 may include one software program for automatically designing loop antennas, another one for converting the design into a CAD file, and a third program for PCB layout software program. In such instances, the various software programs forming part of the application 1316 may be enabled to communicate with each other and/or import and export various data including settings and parameters relating to the design of the loop antennas. For example, a design of a loop antenna generated by one software program may be stored and exported to be used by a second software program to convert into a CAD file, and the converted file may be also stored and exported to be used by a PCB layout software program to complete a blueprint of the loop antenna.

The application 1316 may communicate with a user interface 1318 which generates a user interface for presenting visual interactive features to a user, for example, on the display 1306 and for receiving input, for example, via a user input device. For example, user interface 1318 may generate a graphical user interface (GUI) and output the GUI to the display 1306 for viewing by a user.

In a case where the computing device 1300 is used as the EMN system 100, the computing device 120, or the tracking device 160, the computing device 1300 may be linked to the monitoring device 130, thus enabling the computing device 1300 to control the output on the monitoring device 130 along with the output on the display 1306. The computing device 1300 may control the monitoring device 130 to display output which is the same as or similar to the output displayed on the display 1306. For example, the output on the display 1306 may be mirrored on the monitoring device 130. Alternatively, the computing device 1300 may control the monitoring device 130 to display different output from that displayed on the display 1306. For example, the monitoring device 130 may be controlled to display guidance images and information during the surgical procedure, while the display 1306 is controlled to display other output, such as configuration or status information of an electrosurgical generator (not shown in FIG. 1).

The application 1316 may include one software program for use during the planning phase, a second software program for use during the navigation or procedural phase, and/or other application(s) for other phases, such as a calibration phase, an optimization phase, and/or or the like. In such instances, the various software programs forming part of application 1316 may be enabled to communicate with each other and/or import and export various settings and parameters relating to the navigation and treatment and/or the patient to share information. For example, a treatment plan and any of its components generated by one software program during the planning phase may be stored and exported to be used by a second software program during the procedure phase.

Although embodiments have been described in detail with reference to the accompanying drawings for the purpose of illustration and description, it is to be understood that the inventive processes and apparatus are not to be construed as limited. It will be apparent to those of ordinary skill in the art that various modifications to the foregoing embodiments may be made without departing from the scope of the disclosure. For example, various steps of the procedures described herein may be implemented concurrently and/or in an order different from the example order(s) described herein.

Claims

1. A system for calibrating an electromagnetic navigation system, comprising: an antenna assembly, including: a pair of transmit coils; anda receive coil configured to receive signals transmitted from the pair of transmit coils; anda memory including instructions that, when executed by a processor, cause the processor to: measure a non-calibrated in-phase component of the received signals and a non-calibrated quadrature component of the received signals based on a first magnitude value and a first phase value of the received signals;compute a calibrated phase value based on the non-calibrated in-phase component and the non-calibrated quadrature component; andcompute a calibrated magnitude value based on the calibrated phase value, the non-calibrated in-phase component, and the non-calibrated quadrature component.
2. The system according to claim 1, further comprising a substrate including a plurality of layers, wherein each transmit coil of the pair of transmit coils is deposited on a respective one of the plurality of layers.
3. The system according to claim 2, wherein the receive coil is disposed on one of the plurality of layers that is located in between the layers on which the pair of transmit coils are respectively deposited.
4. The system according to claim 1, wherein the pair of transmit coils forms a Helmholtz pair.
5. The system according to claim 1, wherein the antenna assembly is an impedance-controlled antenna assembly.
6. The system according to claim 1, wherein the memory stores instructions that, when executed by the processor, cause the processor to: compute a calibrated in-phase component based on the calibrated phase value, the non-calibrated in-phase component, and the non-calibrated quadrature component; andcompute a calibrated quadrature component based on the calibrated phase value, the non-calibrated in-phase component, and the non-calibrated quadrature component.
7. The system according to claim 6, wherein the memory stores further instructions that, when executed by the processor, cause the processor to compute the calibrated in-phase component according to the equation: Icalibrated=Inon-calibrated×cos(θcal)+Qnon-calibrated×sin(θcal),where Icalibrated represents the calibrated in-phase component, Inon-calibrated represents the non-calibrated in-phase component, θcal represents the calibrated phase value, and Qnon-calibrated represents the non-calibrated quadrature component.
8. The system according to claim 6, wherein the memory stores further instructions that, when executed by the processor, cause the processor to compute the calibrated quadrature component according to the equation: Qcalibrated=−Inon-calibrated×sin(θcal)+Qnon-calibrated×cos(θcal),where Qcalibrated represents the calibrated quadrature component, Inon-calibrated represents the non-calibrated in-phase component, θcal represents the calibrated phase value, and Qnon-calibrated represents the non-calibrated quadrature component.
9. The system according to claim 6, wherein the memory stores further instructions that, when executed by the processor, cause the processor to compute the calibrated magnitude value according to the equation:
10. The system according to claim 6, wherein the memory stores further instructions that, when executed by the processor, cause the processor to: determine whether the calibrated magnitude value is less than zero; andin response to a determination that the calibrated magnitude value is less than zero: compute a second calibrated phase value, andrecompute the calibrated magnitude value, the calibrated in-phase component, and the calibrated quadrature component based on the second calibrated phase value.
11. The system according to claim 6, wherein the memory stores further instructions that, when executed by the processor, cause the processor to: determine whether the calibrated magnitude value is less than zero and whether the calibrated phase value is less than or equal to zero; andin response to a determination that the calibrated magnitude value is less than zero and the calibrated phase value is less than or equal to zero: compute a second calibrated phase value according to the equation: θcal′=θcal+π,where θcal′ represents the second calibrated phase value and θcal represents the calibrated phase value; andrecompute the calibrated magnitude value, the calibrated in-phase component, and the calibrated quadrature component based on the second calibrated phase value.
12. The system according to claim 6, wherein the memory stores further instructions that, when executed by the processor, cause the processor to: determine whether the calibrated magnitude value is less than zero and whether the calibrated phase value is greater than zero; andin response to a determination that the calibrated magnitude value is less than zero and the calibrated phase value is greater than zero: compute a second calibrated phase value according to the equation: θcal′=θcal−π,where θcal′ represents the second calibrated phase value and θcal represents the calibrated phase value; andrecompute the calibrated magnitude value, the calibrated in-phase component, and the calibrated quadrature component based on the second calibrated phase value.
13. The system according to claim 6, wherein the memory stores further instructions that, when executed by the processor, cause the processor to: receive a second signal having a second magnitude value and a second phase value;compute a second non-calibrated in-phase component and a second non-calibrated quadrature component based on the second magnitude value and the second phase value; andcompute a corrected in-phase component and a corrected quadrature component based on the calibrated phase value, the calibrated magnitude value, the second non-calibrated in-phase component, and the second non-calibrated quadrature component.
14. The system according to claim 13, wherein the memory stores further instructions that, when executed by the processor, cause the processor to compute the corrected in-phase component according to the equation: Ic=Mcal×((Inon-cal2)×cos(θcal)+(Qnon-cal2)×sin(θcal)),
15. The system according to claim 13, wherein the memory stores further instructions that, when executed by the processor, cause the processor to compute the corrected quadrature component according to the equation: Qc=Mcal×(−(Inon-cal2)×sin(θcal)+(Qnon-cal2)×cos(θcal)),
16. The system according to claim 1, wherein the memory stores further instructions that, when executed by the processor, cause the processor to: perform a lookup in at least one of a sine table or a cosine table based on the first magnitude value and the first phase value, wherein the computing of at least one of the non-calibrated in-phase component or the non-calibrated quadrature component is further based on a result of the performing of the lookup.
17. The system according to claim 1, wherein the memory stores further instructions that, when executed by the processor, cause the processor to compute the calibrated phase value according to the equation:
18. A system for calibrating an electromagnetic navigation system, comprising: a substrate including a plurality of layers;a plurality of pairs of transmit coils, each of the transmit coils being deposited on a respective one of the plurality of layers;a plurality of pairs of receive coils configured to receive signals transmitted from the plurality of pairs of transmit coils, each of the receive coils being deposited on a respective one of the plurality of layers; anda memory including instructions that, when executed by a processor, cause the processor to:measure a non-calibrated in-phase component of the received signals and a non-calibrated quadrature component of the received signals based on a first magnitude value and a first phase value of the received signals;compute a calibrated phase value based on the non-calibrated in-phase component and the non-calibrated quadrature component; andcompute a calibrated magnitude value based on the calibrated in-phase component.
19. The system according to claim 18, wherein the memory stores further instructions that, when executed by the processor, cause the processor to: compute a calibrated in-phase component based on the calibrated phase value, the non-calibrated in-phase component, and the non-calibrated quadrature component;compute a calibrated quadrature component based on the calibrated phase value, the non-calibrated in-phase component, and the non-calibrated quadrature component.
20. A system for calibrating an electromagnetic navigation system, comprising: a pair of transmit coils;a receive coil configured to receive signals transmitted from the pair of transmit coils; anda memory including instructions that, when executed by a processor, cause the processor to: measure an in-phase component of the received signals and a quadrature component of the received signals based on a first magnitude value and a first phase value of the received signals;compute a calibrated phase value based on the in-phase component and the quadrature component; andcompute a calibrated magnitude value based on the calibrated phase value, the in-phase component, and the quadrature component.

CROSS-REFERENCE TO RELATED APPLICATIONS

This application is a continuation of U.S. patent application Ser. No. 15/337,150, filed on Oct. 28, 2016.

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Related Publications (1)

	Number	Date	Country
	20210000550 A1	Jan 2021	US

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	Number	Date	Country
Parent	15337150	Oct 2016	US
Child	17023640		US

System for calibrating an electromagnetic navigation system

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