Pitot-static air data test system with automatic dependent surveillance-broadcast (ADS-B) verification

1. A system for verifying an instrumentation value issued by a transponder, the system comprising:

an Air Data Test Module (ADTM) configured to pneumatically simulate at least one instrumentation value based upon an applied pressure set-point, the pneumatically simulated instrumentation value corresponding to the applied pressure set point, the ADTM including a manifold including a plurality of channels, the plurality of channels including a first channel configured to pressurize a static port of an aircraft, a second channel configured to pressurize a pitot port of the aircraft, the pressurization of the static port and the pitot port occurring simultaneously;

a receiver module configured to receive the at least one pneumatically simulated instrumentation value transmitted the transponder, and

a signal processor operative to control the ADTM, command a prescribed instrumentation value to be simulated by the ADTM, compare the prescribed instrumentation value to the received instrumentation value, and issue a pass signal if the values match and a fail signal if the values do not match.

2. The system according to claim 1 , further comprising:

a graphical user interface operative to input the pressure set-points of the ADTM to generate the pneumatically-simulated instrumentation value, and to display the pass and fail signals of the signal processor.

3. The system according to claim 1 ,

wherein the at least one pneumatically-simulated instrumentation value includes an altitude value simulated on an altimeter and an airspeed value simulated by an airspeed indicator.

4. The system according to claim 1 ,

wherein the instrumentation includes both a first and a second instrumentation.

5. The system according to claim 1 ,

wherein the signal processor is configured to independently and collectively issue commanded air pressure signals indicative of airspeed and altitude values to each of the first and second pitot-static systems.

6. The system according to claim 1 ,

wherein the signal processor issues calibrated pressure offsets between first and second pitot-static systems to independently test the alarm systems thereof.

7. The system according to claim 1 ,

wherein the signal processor further comprises a master controller operative to control one of the pairs of impact and static ADTS ports and a slave controller operative to control the other of the pairs of impact and static ADTS ports and wherein the slave controller is synchronized with the master controller such that the commanded air pressure signals are simultaneously received by the first and second pitot-static systems.

8. The system according to claim 1 further comprising:

a graphical user interface operative to input the pressure set-points of the ADTM to generate the pneumatically-simulated instrumentation value and to output the pass and fail signals of the signal processor.

9. The system according to claim 8 ,

wherein the at least one instrumentation value includes an altitude value simulated on an aircraft altimeter and an airspeed value simulated by an airspeed indicator.

10. The system according to claim 8 ,

wherein the instrumentation includes both the first and second instrumentation.

11. The system according to claim 8 ,

wherein the signal processor is configured to independently and collectively issue commanded air pressure signals indicative of airspeed and altitude values to each of the first and second pitot-static systems.

12. The system according to claim 8 ,

wherein the signal processor issues calibrated pressure offsets between first and second pitot-static systems to independently test the alarm systems thereof.

13. The system according to claim 1 , wherein the pneumatically simulated instrumentation value is reported to a control computer for transmission by the transponder.

14. The system according to claim 1 , wherein the plurality of channels further includes a third channel configured to pressurize a second static port of the aircraft, the pressurization of the second static port occurring simultaneously with the pressurization of the static port and the pitot port.

15. A method for testing an Automatic Dependent Surveillance-Broadcast (ADS-B) system comprising the steps of:

calculating a pressure set point indicative of a prescribed instrumentation value;

pneumatically simultaneously pressurizing plurality of pitot-static systems by an Air Data Test Module (ADTM) to simulate at least one instrumentation value via the instrumentation undergoing an air data test;

receiving the simulated instrumentation value and comparing the same to the prescribed instrumentation value;

determining whether the simulated and prescribed instrumentation values are equal; and

providing a visual cue regarding the status of the instrumentation values to validate the operation of the pitot-static and the ADS-B systems.

16. The method according to claim 15 further comprising the steps of:

determining the GPS coordinates of the ADTM to determine the current altitude thereof;

reading the altitude value of an altimeter transmitted by a transponder;

comparing the altitude values of the ADTM GPS and the altimeter to validate the operation of the ADS-B system.

17. The method according to claim 15 ,

wherein the simulated instrumentation values are indicative of airspeed and altitude, and further comprising the step of:

issuing the simulated instrumentation values to each of a first and a second pitot-static systems through the ADTM.

18. The method according to claim 15 further comprising the step of:

issuing calibrated pressure offsets between first and second pitot-static systems to independently test the alarm systems thereof.

19. The method according to claim 15 further comprising the step of:

displaying the visual cue on a graphical user interface.

20. The method according to claim 15 ,

wherein input commands to the ADTM are made by a mobile input device.

21. The method according to claim 15 ,

wherein input commands to the ADTM are made by a monitor connected to the ADTM.

22. A system, comprising:

an Air Data Test Module (ADTM) including at least one pressure source, a manifold system pneumatically coupled to the at least one pressure source, and a signal processor operatively coupled to the at least one pressure source and the manifold system to pneumatically simulate at least one instrumentation value undergoing an air data test, the ADTM including a manifold including a plurality of channels, the plurality of channels including a first channel configured to pressurize a static port of an aircraft, a second channel configured to pressurize a pitot port of the aircraft, the pressurization of the static port and the pitot port occurring simultaneously;

a receiver module including a link operative to receive the at least one pneumatically-simulated instrumentation value transmitted by an transponder,

a global positioning system (GPS) module including a GPS receiver operative to receive the GPS coordinates of the ADTM and the at least one instrument undergoing the air data test; and

a signal processor controlling the ADTM, command a prescribed instrumentation value to be simulated by the ADTM, compare the prescribed instrumentation value to the received instrumentation value, issue a pass signal when the values match, and a fail signal when the values do not match.

23. The system according to claim 22 , wherein the pneumatically simulated instrumentation value corresponds to a pressure set point issued by the ADTM.

24. The system according to claim 22 , wherein the pneumatically simulated instrumentation value is reported to a control computer for transmission by the transponder.

25. The system according to claim 22 , wherein the plurality of channels further includes a third channel configured to pressurize a second static port of the aircraft, the pressurization of the second static port occurring simultaneously with the pressurization of the static port and the pitot port.

26. The system according to claim 14 , wherein the plurality of channels further includes a fourth channel configured to pressurize a second pitot port of the aircraft, the pressurization of the second pitot port occurring simultaneously with the pressurization of the static port, the pitot port, and the second static port.

27. The system according to claim 15 , wherein the plurality of channels further includes a fourth channel configured to pressurize a second pitot port of the aircraft, the pressurization of the second pitot port occurring simultaneously with the pressurization of the static port, the pitot port, and the second static port.