Patent Application
20160301439
Over time, the airspace in the United States has become more structured. Where once travel by private aircraft required no real need for aviation electronics (“avionics”), today's busy airspace demands more integration between ground controllers and aircraft. Current airspace around major airports often limits entry to those aircraft that can both communicate with air traffic control via a communications (COMM) radio and report their position to Air Traffic Control via a radar transponder. For example, a COMM radio is needed to communicate with Air Traffic Control (ATC) in order to enter Class B air space since all aircraft entering Class B airspace must obtain ATC clearance prior to entry. Similarly, aircraft entering a Mode C veil need to have an altitude reporting Mode C transponder in operation to enter that airspace.
For the reasons stated above and for other reasons stated below which will become apparent to those skilled in the art upon reading and understanding the specification, there is a need in the art for improved systems and methods for a combined COMM-transponder avionics radio unit.
The Embodiments of the present invention provide methods and systems for a combined COMM-transponder avionics radio unit and will be understood by reading and studying the following specification.
Combined communications-transponder avionics radio units are provided. In one embodiment, a communications-transponder avionics radio unit is provided. The unit comprises: a first component bay having a communications (COMM) radio unit; a second component bay having a transponder unit; a control display unit divided into a first control display interface area for a COMM radio control display in communication with the COMM radio unit, and a second control display interface area for a transponder radio control display in communication with the Transponder Unit; and an enclosure housing the first component bay, the second component bay and the control display unit.
Embodiments of the present invention can be more easily understood and further advantages and uses thereof more readily apparent, when considered in view of the description of the preferred embodiments and the following figures in which:
In accordance with common practice, the various described features are not drawn to scale but are drawn to emphasize features relevant to the present invention. Reference characters denote like elements throughout figures and text.
In the following detailed description, reference is made to the accompanying drawings that form a part hereof, and in which is shown by way of specific illustrative embodiments in which the invention may be practiced. These embodiments are described in sufficient detail to enable those skilled in the art to practice the invention, and it is to be understood that other embodiments may be utilized and that logical, mechanical and electrical changes may be made without departing from the scope of the present invention. The following detailed description is, therefore, not to be taken in a limiting sense.
Embodiments of the present invention provide a single radio package which can be installed inside the limited space available on a small aircraft, but provides the pilot with all the functionality needed to traverse all the airspace in the United States with a single piece of avionics. Embodiments of the present disclosure describe solutions to the above described problem by combining the COMM transceiver functionality with the Transponder functionality in such a way that they do not interfere with each other during operation. For example, this may be accomplished by packaging each radio section in a grounded enclosure while still maintaining their ability to be packaged in such a manner as to fit into a general aviation aircraft individually. The COMM radio section may be constructed either for the standard 118-136 MHz frequency range, or an extended 108-136 MHz frequency range which will include the Navigation (Nav) frequencies. Including extended Nav frequencies will allow the pilot to listen to information (such as weather and Flight Service) being broadcast over the Very High Frequency (VHF) Omnidirectional Range (VOR) transmitter system. Combining the COMM and transponder radio functions in the manner described herein give provides a combination COMM plus Transponder unit that takes up less panel space than the traditional implementations, is less expensive, and is easier for the pilot to use.
Enclosure 105 further includes an interface component 130 (which may comprise an electronics board, for example) which in some embodiments incorporates the electrical coupling device 150 and provides electrical connectivity between the COMM Radio Unit 110, the Transponder Unit 120, and the control display unit 140, and the at least one electrical coupling device 150. In some embodiments, interface component 130 also forms a physical barrier that separates the first component bay 106 from the second component bay 107. For example, for some implementations, the COMM Radio Unit 110 within the first component bay 106 and the Transponder Unit 120 within the second component bay 107 are each no more than 3 inches wide and no more than 1.3 inches tall, allowing the two units 110, 120 plus the interface component 130 to be placed side by side and fit within a standard 6.25″ wide radio rack. In one embodiment, COMM-transponder avionics radio unit 100 is implemented with a form factor of a dual sided line replaceable unit (LRU).
In the embodiment shown in
Transponder Unit 120 includes a Transponder Radio Module 122 and a DC/DC power supply 124. DC/DC Power Supply 124 is coupled to the Aircraft's DC power Bus 112 by a conductive path 135 provided by interface component 130 and through the mated electrical coupling device 150 and 160. DC/DC power supply 124 is also coupled to the Transponder radio module 122, providing it with the electrical power needed to perform its Transponder functionality. For example, in one embodiment, the transponder radio module 122 may respond to ATC interrogations from a ground station by transmitting radio frequency signals that send back information such as the aircraft's identification code, and/or altitude information. Providing separate power supplies 114 and 124 for each of the respective radio units 110, 120 eliminates a single point failure mechanism that could otherwise result in the simultaneous loss of both transponder and COMM functionality. That is, failure of a single power supply within COMM-transponder avionics radio unit 100 will not result in the loss of both the transponder and COMM functions. In order to receive interrogations and transmit responses, transponder radio module 122 is coupled to an aircraft mounted antenna 126 tuned for use with the transponder radio module's frequency range. More specifically, transponder radio module 122 is coupled to the aircraft mounted antenna 126 by a conductive path 134. In still other embodiments, interface component 130 may also include additional path for data, control, or power. For example, interface component 130 may provide one or more data buses for providing data in to or out from modules 112 and 122 via electrical coupling device 150, or similarly a dimmer control signal for controlling the brightness of the control display unit 140.
In one embodiment, COMM-transponder avionics radio unit 100 may include a Ferriday cage around the COMM radio unit 110 (shown at 115), around the Transponder unit 120 (shown at 125), or both, in order to shield components within unit 110 from induced Radio Frequency (RF) noise.
As illustrated by
Example 1 includes a communications-transponder avionics radio unit, the unit comprising: a first component bay having a communications (COMM) radio unit; a second component bay having a transponder unit; a control display unit divided into a first control display interface area for a COMM radio control display in communication with the COMM radio unit, and a second control display interface area for a transponder radio control display in communication with the Transponder Unit; and an enclosure housing the first component bay, the second component bay and the control display unit.
Example 2 includes the unit of example 1, further comprising: an interface component comprising at least one electrical coupling device configured to mate with an electrical coupling device external to the enclosure; wherein the interface component provides within the enclosure electrical connectivity between the COMM radio unit, the transponder unit, the control display unit, and the at least one electrical coupling device.
Example 3 includes the unit of example 2, wherein the interface component forms a physical barrier that separates the first component bay from the second component bay.
Example 4 includes the unit of any of examples 2-3, wherein the COMM radio unit includes a COMM radio module configured to couple to an aircraft mounted antenna.
Example 5 includes the unit of any of examples 2-4, the COMM radio unit further comprising: a DC/DC Power Supply coupled to a COMM radio module; wherein the DC/DC Power Supply is configured to couple to a DC power bus via the at least one electrical coupling device by a conductive path provided by the interface component.
Example 6 includes the unit of any of examples 2-5, wherein the transponder unit includes a transponder radio module configured to couple to an aircraft mounted antenna.
Example 7 includes the unit of any of examples 2-6, the transponder radio unit further comprising: a DC/DC power supply coupled to a transponder radio module; wherein the DC/DC power supply is configured to couple to a DC power bus via the at least one electrical coupling device by a conductive path provided by the interface component.
Example 8 includes the unit of any of examples 1-7, wherein the interface component include further comprises: one or more data bus paths; one of more control signal paths
Example 9 includes the unit of any of examples 1-8, wherein the enclosure further includes one or both of: a first Ferriday cage around the COMM radio unit; and a second Ferriday cage around the transponder radio unit.
Example 10 includes the unit of any of examples 1-9, wherein the control display unit provides a common control and display interface mounted across a front of the unit.
Example 11 includes the unit of example 10, wherein the control display unit includes a power interface coupled to a DC power bus via the at least one electrical coupling device by a conductive path provided by the interface component.
Example 12 includes the unit of any of examples 1-11, wherein the COMM radio control display is generated by the COMM radio unit; and the transponder radio control display is generated by the transponder radio unit and provides an interface where the pilot may adjust various transponder settings.
Example 13 includes the unit of any of examples 1-12, wherein the enclosure is implemented with a form factor conforming to a dual sided line replaceable unit (LRU).
Example 14 includes the unit of any of examples 1-13, wherein the enclosure is installed into a radio rack of an aircraft.
Example 15 includes the unit of example 14, wherein the enclosure is configured to mount within a 6.25″ wide radio rack.
Example 16 includes a communications-transponder avionics radio unit, the unit comprising: an enclosure comprising a communications (COMM) radio unit, a transponder unit, at least one electrical coupling device on a back side of the enclosure, and a control display unit on a front side of the enclosure; wherein the control display comprises a first control display interface area associated with the communications radio unit, and a second display area control display interface area associated with the transponder unit; and wherein the at least one electrical coupling device is configured to distribute power to the COMM radio unit, a transponder unit, at least one electrical coupling device.
Example 17 includes the unit of example 16 further comprising: an interface component internal to the enclosure, wherein the communications radio unit, the transponder unit, and the control display unit are each coupled to the at least one electrical coupling device by the interface component.
Example 18 includes the unit of any of examples 16-17, the communications radio unit further comprising: a first DC/DC power supply internal to the enclosure, where the first DC/DC power supply provides power to a COMM radio module and is provided power from the at least one electrical coupling device.
Example 19 includes the unit of example 18, the transponder radio unit further comprising: a second DC/DC power supply internal to the enclosure, where the second DC/DC power supply provides power to a transponder radio module and is provided power from the at least one electrical coupling device.
Example 20 includes the unit of any of examples 16-19, wherein the enclosure is configure to install into a standard a standard 6.25″ wide avionics radio rack.
Although specific embodiments have been illustrated and described herein, it will be appreciated by those of ordinary skill in the art that any arrangement, which is calculated to achieve the same purpose, may be substituted for the specific embodiment shown. This application is intended to cover any adaptations or variations of the present invention. Therefore, it is manifestly intended that this invention be limited only by the claims and the equivalents thereof.
