Patent Application
20150185246
1. Field
This disclosure relates to the field of measuring air data parameters.
2. Background Art
Optical fiber amplifiers that receive coherent light of relatively low power from a seed laser and amplify that light with fiber laser amplifiers are known. When such systems are to be used for such applications as target marking, target ranging, imaging, and tracking, and LIDAR, among others, a primary objective has been to obtain a high power, single mode output, or output with relatively low multimode content. This is particularly difficult because of the necessity of controlling amplified spontaneous emission (ASE), controlling the excitation of unwanted modes, and reducing the effects of non-linearity. Beam wave front distortions also arise from a number of other causes including propagation through a medium such as the atmosphere or through a turbulent air mass. The performance characteristics of a LIDAR system depend on the degree to that beam characteristics (such as single-mode vs. multi-mode) and be controlled in an efficient manner.
Therefore, systems and methods of measuring air data parameters are needed that provide the ability to control the beam shape, propagation direction, multi-mode content, and other parameters of an output beam.
Systems and methods for laser based measurement of air parameters using intelligent optical devices are disclosed. An example system includes a coherent source of radiation, a transceiver, an optical mixer, and an intelligent optical device. The coherent source produces a coherent radiation beam that is then transmitted to a target region by the transceiver. The transceiver is further configured to receive a scattered radiation signal from the target region. The optical mixer is configured to receive the scattered radiation signal from the transceiver, receive a reference radiation beam from the coherent source, and to determine a difference between the scattered radiation signal and the reference radiation beam. In certain embodiments, the intelligent optical device is configured to steer, modulate, condition, etc., at least one of the coherent radiation beam, the scattered radiation signal, and the reference radiation beam.
In a further embodiment, a method for laser based determination of air parameters is disclosed. The method includes generating a coherent radiation beam, transmitting the coherent radiation beam to a target region, and receiving a scattered radiation signal from the target region. The method further includes receiving a reference radiation beam from the coherent source, and determining a difference between the scattered radiation signal and the reference radiation beam. In certain embodiments, the method further includes applying a control signal to an intelligent optical device so as to steer, modulate, condition, etc. at least one of the coherent radiation beam, the scattered radiation signal, and the reference radiation beam.
Further features and advantages of the present invention, as well as the structure and operation of various embodiments of the present invention, are described in detail below with reference to the accompanying drawings. It is noted that the present invention is not limited to the specific embodiments described herein. Such embodiments are presented herein for illustrative purposes only. Additional embodiments will be apparent to persons skilled in the relevant art(s) based on the teachings contained herein.
The accompanying drawings, that are incorporated herein and form part of the specification, illustrate the present invention and, together with the description, further serve to explain the principles of the present invention and to enable a person skilled in the relevant art(s) to make and use the present invention.
The features and advantages of the present invention will become more apparent from the detailed description set forth below when taken in conjunction with the drawings, in that like reference characters identify corresponding elements throughout. In the drawings, like reference numbers generally indicate identical, functionally similar, and/or structurally similar elements. The drawing in that an element first appears is indicated by the leftmost digit(s) in the corresponding reference number.
This specification discloses one or more embodiments that incorporate the features of this invention. The disclosed embodiment(s) merely exemplify the present invention. The scope of the present invention is not limited to the disclosed embodiment(s). The present invention is defined by the claims appended hereto.
The embodiment(s) described, and references in the specification to “one embodiment,” “an embodiment,” “an example embodiment,” etc., indicate that the embodiment(s) described may include a particular feature, structure, or characteristic, but every embodiment may not necessarily include the particular feature, structure, or characteristic. Moreover, such phrases are not necessarily referring to the same embodiment. Further, when a particular feature, structure, or characteristic is described in connection with an embodiment, it is understood that it is within the knowledge of one skilled in the art to affect such feature, structure, or characteristic in connection with other embodiments whether or not explicitly described.
Embodiments of the present invention may be implemented in hardware, firmware, software, or any combination thereof. Embodiments of the present invention may also be implemented as instructions stored on a machine-readable medium that may be read and executed by one or more processors. A machine-readable medium may include any mechanism for storing or transmitting information in a form readable by a machine (e.g., a computing device). For example, a machine-readable medium may include read only memory (ROM); random access memory (RAM); magnetic disk storage media; optical storage media; flash memory devices; electrical, optical, acoustical or other forms of propagated signals (e.g., carrier waves, infrared signals, digital signals, etc.), and others. Further, firmware, software, routines, instructions may be described herein as performing certain actions. However, it should be appreciated that such descriptions are merely for convenience and that such actions in fact result from computing devices, processors, controllers, or other devices executing the firmware, software, routines, instructions, etc.
Before describing such embodiments in more detail, however, it is instructive to present an example environment in that embodiments of the present invention may be implemented.
An air speed LDV 10 is illustrated in
The LDV 10 includes a source 20 of coherent light that may, if desired, be polarized. The source 20 projects a first coherent beam of light 30 into a modulator 40. The modulator 40 expands and collimates the beam 30 after that beam 30 enters a transceiver 60. The transceiver 60 projects the beam 30 in nearly collimated form into the target region 45.
The collimated beam strikes airborne scatterers (or air molecules) in the target region 45, resulting in a back-reflected or scattered beam 50. A portion of the scattered beam 50 is collected by the same transceiver 60 that transmitted the beam 30, or to an adjacent receiver (not shown). The case where the same transceiver transmits and receives the light is known as a monostatic configuration, while the case of separate transmitters and receivers is known as a bistatic configuration. Monostatic configurations call only receive scattered light. Bistatic configurations can be arranged to receive light that is substantially scattered or at any other angle relative to the transmitted beam 30.
The light 50 collected by transceiver 60 is then combined with a separate reference beam of light 70 in an optical mixer 80. An ideal optical mixer combines the two beams in such a way that they have the same polarization and occupy the same space, and directs the result onto a photo detector with a bandwidth sufficient to detect the measured Doppler frequency shift. The photo detector produces an electrical current 85 that includes a component whose frequency is the mathematical difference between the frequency of the reference beam 70 and the scattered beam 50. The electrical current 85 is then analyzed by a signal processor 90 (e.g., electrical spectrum analyzer or a frequency counter) to determine the frequency difference and calculate the relative velocity component along the axis of the transceiver 60 between the LDV 10 and the target region 45.
Ambiguities regarding whether the measured relative frequency is either positive or negative can be resolved by using the “in-phase and quadrature” detection method, as is known in the art. Another approach to resolving these ambiguities is to apply a stable, constant frequency shift either to the transmitted beam 30 or to the reference beam 70 (e.g., by using an acousto-optic cell). This creates an alternating current component in the electrical signal 85 with a frequency that is the sum of the constant frequency shift and the Doppler frequency shift, removing the directional ambiguity. An LDV wherein the frequency of the transmitted beam 30 and the frequency of the reference beam 70 are identical is said to use homodyne detection. Heterodyne detection is used when the frequencies of the transmitted beam 30 and reference beam 70 are different.
The reference beam 70 is selected to have a well-defined and stable optical frequency that bears a constant phase relationship with the transmitted beam 30. This is known as coherence. The requirement for coherence is easily achieved by using a laser as the source 20 and tapping the source 20 to create the reference beam 70 by means of an optical splitter (not shown).
Source 20 can be either a CO2, Nd:YAG, or Argon ion laser (preferably lasing in the fundamental transverse mode and in a single longitudinal mode). However, air-speed targets (aerosols and/or molecules) generate very weak return signals compared to solid objects. Thus air-speed LDV's incorporating these laser sources that work over a range of thousands or even tens of meters require large amounts of laser power and are thus too large, bulky, heavy, fragile and possibly dangerous to be used in many desirable applications like air-speed determination for helicopters.
However, source 20 can also be a lightweight, low-cost, highly efficient, rare-earth-doped glass fiber (referred to hereafter as a fiber laser). Fiber lasers have several enormous advantages over other laser sources. Fiber lasers can be efficiently pumped by laser diodes whose emission wavelengths have been optimized for excitation of the rare-earth dopant. This makes the fiber lasers very energy efficient and compact, eliminating the need for cooling systems, flash lamps, and high current electrical sources. Moreover the glass fiber serves as a flexible waveguide for the light, eliminating the need for bulky optical components like mirrors and lenses that require rigid mechanical mounts in straight lines with stringent alignment tolerances. Fiber lasers are also more adaptable than solid-state lasers: the pulse repetition frequency (“PRF”) and pulse width in fiber lasers may be changed “on the fly,” while the PRF and pulse width in solid-state lasers are bound to narrow ranges or are even fixed. Source 20 can also be comprised of a laser diode coupled to an optical fiber.
Despite advances in conventional LASER Doppler Velocimeters (LDV's), improvements are still necessary. Sometimes it is desirable to locate the source laser 20 at a different, more accessible location than the transceiver 60. For example, in a wind turbine generator (“WTG”) application the telescope can be located on the turbine, while its source laser and control electronics are best located in the nacelle or at the base of the tower that supports the WTG for ease of maintenance. In sailing applications the source is preferably located within the hull of the ship where it is protected from exposure to the elements.
These remote configurations can be made conveniently by using optical fiber to connect the source laser 20 and the transceiver 60. Problems have occurred, however, in that the large optical power required for air speed measurements becomes limited by a non-linear effect that occurs in fiber optical known as stimulated Brillouin scattering (“SBS”). In fact, the longer a fiber optic is, the lower this limit becomes. The SBS power limit depends on other factors known to those skilled in the art, but it is a fundamental physical property of light traveling through transparent media and cannot be ignored.
Embodiments of the present invention provide a velocimetry system for an LDV with no moving parts and that is lightweight enough to be used for many different applications that were, up to this point, not practical for LDVs. The disclosed LDV includes an active lasing medium, such as e.g., an erbium-doped glass fiber amplifier for generating and amplifying a beam of coherent optical energy and an optical system coupled to the beam for directing the beam a predetermined distance to a scatterer of radiant energy. The scattered beam is mixed with a reference portion of the beam for determining the velocity of the scatterer.
In using this device to measure wind velocity in the transceiver focal volume, the velocity component that is measured is that component along the axis of the transceiver. Therefore, for measurement of the “n” components of velocity, n independent measurements must be made along n non-collinear axes (where n is an integer). To accomplish this task n duplicate transceivers are disclosed, each carrying either a continuous wave (“CW”) beam or are simultaneously pulsed with a common seed laser source. Simultaneous pulsing and transmission through the n transceivers has the advantage that the velocity measurements each arise from the same moment in time, instead of from sequential moments in time. Thus, the resulting velocity determinations are more accurate as a result of simultaneous pulsing and transmission instead of sequential transmission.
By using optical fiber for both generation of the laser energy as well as wave guiding of the energy, the present disclosure provides a single, mechanically flexible conduit for light. This configuration allows the system to be more robust to vibration and temperature variation than a corresponding system comprising free space optical components. The only point at that light leaves the optical fiber system is for projection from the respective transceivers. Each of the optical fibers that transmits light is also the same fiber used to receive scattered light and thus the aerosol-scattered return beam is automatically aligned with the respective transceiver-fiber optic collection systems.
The use of fiber lasers such as e.g., erbium-doped optical fiber also has advantages in terms of the overall energy efficiency of the system. Because diode lasers are now available at the optimal pump wavelength of erbium doped glass, the erbium wave guide can be efficiently pumped by launching pump radiation down this wave guide. Thus, the system has greatly reduced cooling requirements and can operate off of a low voltage battery supply.
The disclosed velocimeter system is also eye-safe, light-weight, and easily scaled to high energy per pulse or CW operation. As described above, the velocimeter has “n” lines of sight. Thus, in order to determine an object's velocity or the wind velocity in one or more target regions, n transceivers are used, each simultaneously projecting a beam of light along a different axis. To determine three-dimensional velocity, as with wind velocity, three transceivers are used. To determine two- or one-dimensional velocity, e.g., for a car or boat moving on a plane or in a line, fewer transceivers may be used. The laser beams projected from the n transceivers are each pumped simultaneously and arise from a single laser source. The source may be co-located with the n transceivers, or may be located remotely with respect to the n transceivers. If the laser source is remotely located, fiber optic cables are used to carry the generated light beams to each transceiver. As described below in greater detail, a seed laser from the source is amplified and, if desired, pulsed and frequency offset, and then split into n source beams. The n source beams are each delivered to an amplifier assembly that is located within the n transceiver modules, where each of the n transceiver modules also includes an optical system such as a telescope. Amplification of the n source beams occurs at the transceiver modules, just before the n beams are transmitted through the optical system to one or more target regions. Thus, when the n source beams are conveyed through connecting fibers from the laser source to each of the n transceivers, the power of each of the source beams is low enough so as not to introduce non-linear behaviors from the optical fibers. Instead, power amplification occurs in the transceiver module, just before transmission from the optical system. Consequently, fiber non-linear effects are not introduced into the system.
The placement of the power amplifier within the transceiver modules just before laser beam projection through a lens reduces the effect of nonlinear fiber behavior that is normally observed when there is a greater propagation distance between the power amplifier and the lens. In this way, the disclosed velocimeter is able to use a single seed laser and amplifier assembly that is remote from the power amplifier. The seed laser generates a beam that may be amplified, pulsed, and frequency shifted before the beam is split, if necessary, and directed to the remote power amplifiers. Power amplification only occurs just before transmission of the source beam through the lenses. Thus, as long as the amplified result is still within the linear operating region of the fiber to the remote amplifier, the disclosed velocimeter avoids the problems associated with non-linear fiber operation.
By using the disclosed velocimeter, object or wind velocities may be measured with a high degree of accuracy. Because the source laser is split into n beams, the measurements taken along all of the n axes are simultaneous. Additionally, splitting the source beam into n beams does not necessarily require that the source laser transmit a laser with n times the necessary transmit power, because each of the n beams are subsequently power amplified before transmission. The n beams may each be directed towards the same target region or may be directed to multiple target regions. A single beam may be used to simultaneously measure velocities at multiple points or span along a single axis. Additionally, the disclosed velocimeter has no moving parts, and is thus of reduced size and improved durability. As explained below, the disclosed velocimeter may be used with a platform motion sensing device such as e.g., an inertial measurement unit (“IMU”) or global positioning satellite (“GPS”) unit so that the motion of the velocimeter platform may be compensated during calculation of the measured velocities. Thus, because of the light-weight and non-bulky nature of the velocimeter, and because of the velocimeter's ability to compensate for platform motion, the disclosed LDV may be mounted on any moving platform (e.g., a helicopter, a boat, etc.) and still obtain highly accurate readings.
An exemplary LDV system is as disclosed in U.S. Pat. No. 5,272,513, the disclosure of that is incorporated herein by reference in its entirety. Additional exemplary systems are taught in co-owned U.S. application Ser. No. 12/988,248 and PCT Appl. No. WO 2009/134221 that are both incorporated by reference herein in their entireties.
The radiation source module 200 is illustrated in
Each of these components of the radiation source module 200 are coupled together and are described in greater detail below.
The laser source 210 and associated drivers and controllers provide the initial laser energy that may be feed into optical amplifier (see
A frequency shifter (such as an acousto-optic modulator (“AOM”)) (as a possible component of the optical modulator 230) and associated RF drivers may provide a radio-frequency (“RF”) offset to the laser source output. This offset facilitates the later determination by a signal processor of the direction of any detected motion. The offset is provided by utilizing the acousto-optic effect, i.e., the modification of a refractive index by the oscillating mechanical pressure of a sound wave. In an AOM, the input laser beam is passed through a transparent crystal or glass. A piezoelectric transducer attached to the crystal is used to excite a high-frequency sound wave (with a frequency in the RF domain). The input light experiences Bragg diffraction at the periodic refractive index grating generated by the sound wave. The scattered beam has a slightly modified optical frequency (increased or decreased by the frequency of the sound wave). The frequency of the scattered beam can be controlled via the frequency of the sound wave, while the acoustic power is the control for the optical powers. In this way, a frequency shifter may be used to provide a frequency offset to the laser source output. An AOM may also be used as an optical modulator 230 to modulate laser signals from the source laser 210 in order to obtain pulsed LIDAR measurements.
Additional modulation of the seed laser output may be provided using an optical modulator 230 (such as e.g., semiconductor optical amplifier (“SOA”)). Although the SOA is not necessary for the system 100 to function, SOA-induced pulsing may be used to optimize the extinction ratio in the pulses. The SOA is capable of providing primary as well as secondary modulation of the seed laser source. The SOA may also be used to provide optical amplification to the laser source signal. The laser source 210 can also be modulated electronically.
An optical amplifier (feature 330 in
Once filtered, the amplified light is passed through an optical splitter 270. The optical splitter 270 splits the light amongst the different transceiver modules 300. As explained below, the light from the radiation source module 200 is transmitted to optical amplifiers 330 located within each individual transceiver module 300. The use of an optical splitter instead of a switch or multiplexer allows the radiation source module 200 to be designed without any moving parts. In other words, no motors or switches need be used.
Light output from the optical splitter 270 and hence the radiation source module 200 is directed to the n transceiver modules 300 by way of n connecting fibers 125. The connecting fibers 125 allow the radiation source module 200 to be remotely located if desired) from the n transceiver modules 300. As described above, the lasers carried by the connecting fiber bundle 125 are each at a sufficiently low power to avoid introducing the non-linear effects of the fiber. The fiber bundle 125 consists of multiple fibers of varying core sizes to carry different optical signals between the radiation source module 200 and the n transceiver modules 300. These optical signals include the amplified source laser signal, as well as a multimode pump laser signal from a pump laser 240 for the pumping of amplifiers at each of the n transceiver modules 300. Furthermore, optical signals including optical monitor signals from the transceiver modules 300 are carried back to the radiation source module 200. The optical monitor signals can trigger the shutdown of the radiation source module 200 in the event of a malfunction or error at the transceiver modules 300.
One of the n transceiver modules 300 is illustrated in
Amplified source laser signals from the radiation source module 200 transmitted via optical fibers 125 to each of the transceiver modules 300 are further amplified within each of the transceiver modules 300 via the optical amplifier 330. The optical amplifier 330 includes a rare earth doped fiber (such as e.g., Er:Yb double clad fiber). Pump light can be introduced into the rare earth doped fiber via a tapered fiber bundle (“TFB”) in a co-propagating or counter-propagating manner relative to the seed laser signal from the radiation source module 200. The source laser signal is thus further amplified within the transceiver module 300. The output of the optical amplifier 330 is then directed towards an optical switch 340 via TFBs or WDMs.
The optical switch 340 (such as e.g., a fiber optic direction switch) allows a single lens 360 to be used to transmit and receive light, thus allowing the sensor to operate in a monostatic geometry. In the case where multiple lenses are used (at least one for transmitting a light beam and at least one for receiving a scattered light beam, e.g., a bistatic geometry), the optical switch 340 may not be necessary. The optical switch 340 may also be used in conjunction with an amplified spontaneous emission filter. Such a filter might be bulk optic or an FBG based filter. Such a filter may be installed to maintain laser eye safety, as necessary. It is often the case that these filters divert the amplified spontaneous emission (“ASE”) to another fiber optic. This diverted laser can be used to monitor the operation of the optical amplifier 330 to adjust the amplifier's power, or as a safety feature in remotely pumped applications. As a safety feature, a measurable drop in the diverted ASE could mean that the fiber cable has been severed and that the pump should be shut down immediately. Alternatively, to reduce ASE in pulsed applications, the pump lasers themselves may be pulsed in synchronization. Pulsing the pump lasers also reduces power consumption, thus facilitating the use of battery operated systems.
Source light that reaches the transceiver lens 360 is projected onto a target object or region 45 (of
The optical mixer 400 is explained in greater detail with reference to
An optical coupler such as 420 (e.g., a 3 dB fiber optic coupler) generally produces two output beams 425, 426 of opposite phase. Beam 425 is the combined signal, as explained above. Beam 426 may also be used and applied to a second electro-optic receiver to create a balanced receiver, as described in U.S. Pat. No. 4,718,121, the disclosure of that is incorporated herein by reference. Balanced receivers are preferably used because they use all of the mixed signal, and result in the cancellation of intensity noise in the reference laser beam 255.
Effective optical mixing also requires matching the polarizations of the received signal 405 and the reference laser signal 255. Mitigating the loss of mixing efficiency due to uncontrolled polarization may require a more complicated optical mixing circuit than the one shown in
The signal processor 440 receives the signal from the digitizer 450 and converts the signal into frequency space, calculates line-of-sight speeds from the Doppler shifts along each line-of-sight (i.e., from each of the n transceivers 300), and combines these speeds to determine a single velocity for the target object or region measured. Additionally, the signal processor 440 may use input from a motion sensor (preferably an attitude heading reference system or an IMU and a GPS or ground speed detection device) to determine if the platform upon that the transceivers 300 are mounted is moving. Any platform motion is detected and used to adjust or correct the measured velocity, as described in connection with
Although not all applications of the disclosed LDV 100 require platform motion compensation, the disclosed LDV 100 (or at least the transceiver module 300 of the LDV 100) is portable and may easily be located on a moving platform such as a boat, ground vehicle or aircraft. As discussed above, the LDV 100 directly measures the relative motion of air scatterers with respect to the transceiver module 300 by detecting the Doppler frequency shift. If the LDV 100 is fixed to the around, then its measurement is the wind speed and direction. However, an LDV 100 undergoing linear motion measures the relative wind speed and direction. If the linear speed and direction of the moving platform is known, then the wind speed can be extracted from the relative wind measurement. Additionally, the LDV 100 may undergo both linear and rotational motion as encountered on floating platforms. The rotational motion introduces an additional frequency shift since the optical focal volumes are moving rapidly through the air. This frequency shifts yields a speed measurement that is not necessarily useful to (1) meteorologists since it does not represent wind or (2) navigators since it does not represent relative wind. This rotational component must be isolated and compensated for in order to report useful wind data.
Referring to
{right arrow over (v)}
fi
={right arrow over (v)}
c.m.
+{right arrow over (ω)}×{right arrow over (r)}
i, Eq. 1.
where {right arrow over (v)}c.m. is the linear velocity of the center of mass 2 of the platform 1 (and thus the LDV 100), {right arrow over (ω)} is the angular velocity of the platform 1, and {right arrow over (r)}i is the displacement vector from the center of mass 2 of the platform 1 to the ith focal volume or target region 45. The displacement vector is {right arrow over (r)}i=rc.m.+{right arrow over (L)}i, where {right arrow over (r)}c.m. is a vector from the center of mass 2 of the platform 1 to the transceiver modules 300 and {right arrow over (L)}i=f{circumflex over (L)}i and is a vector from the ith transceiver module 300 to the ith focal volume or target region 45. The magnitude factor f is either the focal length in a focused system or the range in a range-gated system. The Doppler frequency shift created by this velocity is proportional to its component (δi) along the laser line of sight {circumflex over (L)}i: The ith Doppler frequency shift is equal to 2δi/λ, where λ is the laser wavelength and:
δi={right arrow over (v)}fi·{right arrow over (L)}i={right arrow over (v)}c.m.·{circumflex over (L)}i+({right arrow over (ω)}×{right arrow over (r)}i)·{circumflex over (L)}i. Eq. 2.
The first term of Equation 2 (i.e., {right arrow over (v)}c.m.·{circumflex over (L)}i) is the desired shift due to the relative linear motion between the ith target region 45 and the moving platform 1. The second term of Equation 2 (i.e., ({right arrow over (ω)}×{right arrow over (L)}i)·{circumflex over (L)}) represents the rotational motion and can be written as ({right arrow over (r)}c.m.×{circumflex over (L)})·{right arrow over (ω)} using the rules of cross products with the fact that ({right arrow over (ω)}×{right arrow over (L)}i)·{circumflex over (L)}i=0. The procedure for motion compensation in a three-dimensional system is to measure the three raw Doppler shifts and the angular velocity with an IMU, then subtract off ({right arrow over (r)}c.m.×{circumflex over (L)}i)·{right arrow over (ω)}. This corrected frequency shift is used to compute the three-dimensional relative wind at the ith target region 45.
The angular velocity and attitude (pitch/roll angle) of a moving platform may change rapidly with time. It is important to measure the Doppler shift in a short amount of time so as to allow an assumption that the state motion is frozen (thus allowing the assignment of one value of angular velocity and attitude to each measured Doppler frequency shift). Accordingly, the laser pulse repetition frequency (“PRF”) and the number of pulses Nacc are chosen so that the total time of data collection (i.e., Nacc/PRF) is less than 200 milliseconds, for example. The angular velocity is measured before and after the Nacc pulses are collected and the average value is used in the compensation calculations for {right arrow over (ω)}.
Although LDV 100 has been described in reference to the system and module architectures depicted in
The disclosed LDV embodiments have been explained in the context of fiber-optic-connected modules in a way that allows the transceiver modules 300, 730, and 830 and optical amplifiers 330, 732, and 832 to be remotely located from the radiation source modules 200, 720, and 820. The transceiver modules 300, 730, and 830 need not include any electronics and can be purely optical modules. Motion compensation, laser sources, and signal processing occurs at the radiation source modules 200, 720, and 820 and optical mixers 400, 740, and 840. Thus, the operation of the transceivers 300, 730, and 830 is significantly improved due to less noise from the radiation source modules 200, 720, and 820 and receiver modules 400, 740, and 840, greater mounting stability and easier maintenance. It is to be understood, however, that the foregoing descriptions of LDVs 100, 700, and 800 are purely exemplary and are not intended to be limiting.
In one example, source 920 is coupled to optical mixers 986-1-1 to 986-n-m via respective paths 930-1-1 to 930-n-m, transceivers 960-1 to 960-n are coupled to optical mixers 980-1 to 980-n via respective paths 950-1 to 950-n, and optical mixers 980-1 to 980-n are coupled to signal processor 990 via respective paths 985-1 to 985-n.
In one example, source 920 comprises a coherent radiation source 922, e.g., as a laser. In an example, laser 922 can be a fiber optic laser. In another example, laser 922 can be a rare-earth-doped fiber laser. In another example, laser 922 can be an erbium-doped fiber laser.
In one example, modulator 940 includes one or more modulators 942-1 to 942-n, n being a positive integer. In one example, first modulator 942-1 can operate to introduce a temporal amplitude modulation. In an example, the temporal amplitude modulation induced by modulator 942-1 can be of the form of a pulse. In an example, the temporal amplitude modulation can be of the form of a square wave pulse. In an example, the temporal amplitude modulation can be of the form of a sequence of pulses. In an example, the temporal amplitude modulation can be of the form of a sequence of pulses each with fixed duration of a first time duration separated by a second time duration. In an example, the temporal modulation can be of the form of an arbitrary sequence of pulses of arbitrary shape and duration separated by arbitrary delays. In an example, the temporal amplitude modulation can be of the form of a sequence of square wave pulses.
In an example, modulator 942-1 can be a semiconductor optical amplifier (SOA). In another example, modulator 942-1 can operate to induce a frequency modulation so as to shift the frequency of the source radiation to a higher or lower frequency. In an example, modulator 942-1 can be an acousto-optic modulator (AOM).
In an example, modulator 942-2 can operate to introduce a polarization modulation. In an example, the polarization modulation can be a rotation of the linear polarization of the source radiation. In an example, the polarization modulation can be such as to change a linear polarization of the source radiation into elliptical polarization. In an example, the polarization modulation can change an elliptical polarization of the source radiation into a linear polarization. In an example, modulator 942-2 can be a birefringent crystal. In an example, modulator 942-2 can be coupled to a Faraday rotator 946. In an example, modulator 942-2 can be any device known in the art that operates to introduce a polarization modulation to the source radiation.
In one example, the use of first and second modulators 942-1 and 942-2 in series allows for a pulse amplitude modulation, such as a smaller pulse window (shorter duration and amplitude) within a larger pulse.
In an example, modulator 940 may also contain one or more optical isolators 944-m, where only isolator 944-1 is shown in
In an example, transceiver 960 includes one or more transceiver modules 960-1 to 960-n. Each transceiver module 960-1 can include a splitter 964-1, one or more transceivers 966-1-1 to 966-1-m, m being a positive integer, and an optional delay 968-1. Splitter 964-1 can be a 1×m splitter, splitting a beam received from modulator 940 into m beams, one for each transceiver 966-1 to 966-m. Each of the transceivers 966-1-1 to 966-1-m can comprise similar features and function similarly to transceivers 300 as shown in
In one example, delays 968-1 to 968-n are used to adjust the relative phases of the radiation input to transceivers 966-1-1 to 966-n-m to account for differing path lengths between the various transceivers and source 920.
In one example, optical mixer 980 includes one or more mixer modules 980-1 to 980-n. For example, corresponding transceiver modules 960-1 to 960-n are coupled via respective paths 950-1 to 950-n to corresponding optical mixers 980-1 to 980-n. In one example, each mixer module 980-1 to 980-n includes an optional delay 982-n along path 930-n coupled to source 920, a splitter 984-n, one or more mixers 986-1-1 to 986-1-m, and optional delays 988-1-1 to 988-1-n coupled along paths 950-n to respective transceivers 966-1-1 to 966-1-m in respective transceiver modules 960-1 to 960-n.
In one example, delays 982-1 to 982-n can be used to adjust the relative phases of the radiation input to mixers 980-1 to 980-n to account for differing path lengths between the source and mixer modules 980-1 to 980-n
In one example, delays 988-1-1 to 988-n-m can be used to adjust the relative phases of the radiation input to the various mixers 986-1-1 to 986-n-m from the respective transceivers 966-1-1 to 966-n-m to account for differing path lengths between the respective mixers and transceivers.
In one example, splitter 984-1 can split a beam from source 920 into m beams that travel to corresponding mixers 986-1-1 to 986-1-m along respective paths 930-1-1 to 930-1-m. As discussed above, the optical mixers can measure a Doppler shift associated with radiation received by each transceiver 960 or 966 scattered from the target regions relative to that of the source 920. Thus, the function of the beam splitters 984-n is to provide reference signals from the source 920 to each of the mixers 986 that are needed in order to compare with the scattered radiation signal so as to measure a Doppler shift.
In one example, signals from each of the mixers 980-1 to 980-n are received via paths 985-1 to 985-n at signal processor 990. These signals can be the digitized form of the respective Doppler shifts calculated by the various mixers as described above with reference to
In one embodiment, a LIDAR system can further include an intelligent optical device. The intelligent optical device can be used to reduce the cost, weight, complexity, power, size, etc. of required optics used in a transceiver. Thus, many different optical devices may be replaced with an intelligent optical device.
For example, the intelligent optical device can be used to steer, modulate, condition, shape, correct turbulence, adjust focus, scan, etc. one or more beams passing through the LIDAR system. In one example, the intelligent optical device can be used in optical systems to reduce wave front distortions, to modulate a beam, or to provide other beam conditioning, such as converting a multi-mode beam into a single mode beam. In another example, the intelligent optical device can be used to remove distortions in a beam resulting from propagation though a medium, such as through the atmosphere or through a turbulent air mass, or distortions arising from amplification of a beam.
In various examples, the intelligent optical device can include acousto-optic modulators, electro-optic modulators, magneto-optic modulators, etc. These modulators change an index of refraction of light in various parts of the intelligent optical device along a light path to adjust characteristics of the light as it travels along the light path in the system. In one example, a modulator includes a layer of liquid crystals. A voltage may be applied to change the orientation of the liquid crystals and cause a change to the index of refraction of the material through which the light propagates. Due to their large electro-optic response, liquid crystals can yield substantial changes to the index of refraction for a low applied voltage. Through these adjustments of the index of refraction, the intelligent optical device can be used to steer a single beam and/or to change the shape or modal characteristics of a single beam. In another example, the intelligent optical device can also be used to steer, modulate, or condition a plurality of input beams to generate a plurality of output beams such that the direction, shape, and modal characteristics of respective ones of the plurality of output beams are determined in response to an input signal applied to the intelligent optical device. In various embodiments, intelligent optical devices can be used to control one or more transmitted, received, and/or transmitted and received beams. In general, an intelligent optical device is any active or passive optical device that can perform one or more functions on a light beam.
Intelligent optics works by measuring the distortions in a wave front and compensating for them with a device that corrects those distortions such as a deformable mirror, liquid crystal array, or the like. As an example, an intelligent optics device having a deformable mirror tries to correct distortions, using a wave front sensor (detector) which takes some incident light, a deformable mirror that lies in an optical path, and a computer that receives input from the detector. The wave front sensor measures the distortions on a timescale of a few milliseconds; the computer calculates the optimal mirror shape to correct the distortions and the surface of the deformable mirror is reshaped accordingly. The distortions and irregularities of a beam can result from a variety of sources. For example, an originally clean single-mode beam may acquire distortions as a result of propagation through a medium, e.g., the atmosphere or turbulent air mass. In another example, the distortions may result from amplification of the beam.
In this example, a control signal 1306 is applied to intelligent optical device 1300 to impart a known distortion 1320 on a clean, single-mode input beam 1302 before beam 1302 passes through a medium, e.g., atmosphere 1322, free space 1324, fiber optic 1326, etc. Each of these mediums can cause distortions to beam 1302. However, based on knowing what distortions the mediums individually and collectively will cause, a compensation distortion 1320 can be applied to beam 1302. Thus, after propagating through the various media, a clean undistorted, single-mode beam 1328 emerges even with distortions imposed by the various media beam 1302 may encounter.
Intelligent optical devices, as described above with reference to
It is to be appreciated that the Detailed Description section, and not the Summary and Abstract sections, is intended to be used to interpret the claims. The Summary and Abstract sections may set forth one or more but not all exemplary embodiments of the present invention as contemplated by the inventor(s), and thus, are not intended to limit the present invention and the appended claims in any way.
The present invention has been described above with the aid of functional building blocks illustrating the implementation of specified functions and relationships thereof. The boundaries of these functional building blocks have been arbitrarily defined herein for the convenience of the description. Alternate boundaries can be defined so long as the specified functions and relationships thereof are appropriately performed.
The foregoing description of the specific embodiments will so fully reveal the general nature of the present invention that others can, by applying knowledge within the skill of the art, readily modify and/or adapt for various applications such specific embodiments, without undue experimentation, without departing from the general concept of the present invention. Therefore, such adaptations and modifications are intended to be within the meaning and range of equivalents of the disclosed embodiments, based on the teaching and guidance presented herein. It is to be understood that the phraseology or terminology herein is for the purpose of description and not of limitation, such that the terminology or phraseology of the present specification is to be interpreted by the skilled artisan in light of the teachings and guidance.
The breadth and scope of the present invention should not be limited by any of the above-described exemplary embodiments, but should be defined only in accordance with the following claims and their equivalents.
The claims in the instant application are different than those of the parent application or other related applications. The Applicant therefore rescinds any disclaimer of claim scope made in the parent application or any predecessor application in relation to the instant application. The Examiner is therefore advised that any such previous disclaimer and the cited references that it was made to avoid, may need to be revisited. Further, the Examiner is also reminded that any disclaimer made in the instant application should not be read into or against the parent application.
This application claims benefit under 35 U.S.C. §119(e) to U.S. Provisional Patent Application No. 61/580,045, filed on Dec. 23, 2011, which is incorporated by reference herein in its entirety.
| Number | Date | Country | |
|---|---|---|---|
| 61580045 | Dec 2011 | US |
