AIRCRAFT STEERING ANGLE WARNING SYSTEM

• US 20090040072A1
• Filed: 02/23/2007
• Published: 02/12/2009
• Est. Priority Date: 03/27/2006
• Status: Active Grant

• Current Assignee: Airbus Operations Limited (Airbus SE)
• Original Assignee: Airbus UK Limited (Airbus SE)
• Inventors: Stinchcombe, David George, Read, Terry George, Piddock, Alex Robert, Yiasoumi, Andreas, Sadler, Andrew David
• Granted Patent: US 8,094,042 B2
• Time in Patent Office: Days
• US Class Current: 340/960
• CPC Class Codes: B64C 25/50 Steerable undercarriages; Shimmy-damping
• CPC Class Codes: B64F 1/22 for handling aircraft

Abstract

A steering angle warning system comprising a rotation-measuring unit located on an aircraft, and an alarm unit. The rotation-measuring unit is arranged to output a first signal dependent on the steering angle between a nose landing gear of the aircraft and the longitudinal axis of the aircraft fuselage. The alarm unit is arranged to generate an alarm, in dependence on the first signal, when the steering angle is greater than a predetermined value, for example, 60 degrees. The rotation-measuring unit may also be arranged to perform a function in relation to an aircraft steering system, for example to indicate the steering angle to the pilot during ground manoeuvres.

Claims

1. A steering angle warning system comprising a rotation-measuring unit located on an aircraft, the rotation-measuring unit being arranged to output a first signal dependent on the steering angle between a nose landing gear of the aircraft and the longitudinal axis of the aircraft fuselage, and an alarm unit arranged to generate an alarm, in dependence on the first signal, when the steering angle is greater than a predetermined value.

2. A steering angle warning system according to claim 1, wherein the rotation-measuring unit is part of an aircraft steering system, the rotation-measuring unit being arranged to output a second signal dependent on the steering angle and the aircraft steering system being arranged to provide, to the pilot, an indication of the steering angle in dependence on the second signal.

3. A steering angle warning system according to claim 1, wherein the rotation-measuring unit comprises a Rotary Variable Differential Transducer (RVDT) located on the aircraft nose landing gear.

4. A steering angle warning system according to claim 1 wherein the alarm unit comprises a strobe light.

5. A steering angle warning system according to claim 1, the alarm unit being located on the aircraft.

6. A steering angle warning system according to claim 1, the alarm unit being located on a towing vehicle, the towing vehicle being arranged to tow the aircraft.

7. A steering angle warning system according to claim 1 wherein the predetermined value is between 80% and 90% of the aircraft maximum allowable steering angle.

8. A steering angle warning system according to claim 1 wherein the predetermined value is between 55 and 65 degrees.

9. A steering angle warning system according to claim 1, further comprising a comparator unit, wherein the comparator unit is arranged to receive the first signal, to determine, in dependence on the first signal, whether the steering angle is greater than the predetermined value, and to output a control signal to the alarm unit in dependence on this determination, the alarm unit being arranged to receive the control signal and to generate the alarm in dependence on the control signal.

10. A steering angle warning system according to claim 9, wherein the comparator unit comprises an electronic circuit.

11. A steering angle warning system according to claim 9, wherein the comparator unit comprises a software module.

12. An aircraft comprising a nose landing gear and an aircraft steering system comprising a rotation-measuring unit, the rotation-measuring unit being arranged to output, during use, a first signal, dependent on the steering angle to an interface, the interface being so arranged to enable an alarm unit to receive from the interface a signal that enables the alarm unit, when so arranged, to generate during use an alarm when the steering angle is greater than a predetermined value.

13. An aircraft according to claim 12, wherein the rotation-measuring unit is further arranged to output, during use, a second signal also dependent on the steering angle to provide, to the pilot, an indication of the steering angle.

14. An aircraft according to claim 12, further comprising the alarm unit, the alarm unit being located on the nose landing gear.

15. An aircraft according to claim 12, further comprising a towing vehicle engaged with the nose landing gear, wherein the alarm unit is located on the towing vehicle.

16. An aircraft according to claim 12, wherein the interface comprises a connector to which, in use, the first signal is sent, the connector allowing a cable to be connected thereto to convey the signal to an alarm unit.

17. An aircraft according to claim 12, wherein the interface allows wireless communication of the first signal to the alarm unit.

18. An aircraft according to claim 12, wherein the rotation-measuring unit is arranged to output the first signal, via a comparator unit, the comparator unit being arranged to determine, in dependence on the first signal, whether the steering angle is greater than the predetermined value, and to output a control signal to the alarm unit in dependence on this determination, the alarm unit being arranged to receive the control signal and to generate the alarm in dependence on the control signal.

19. A method of warning against excessive steering angle on an aircraft, the method comprising the steps of:

(i) outputting, from a rotation-measuring unit located on the aircraft, a first signal dependent on the steering angle between a nose landing gear of the aircraft and the longitudinal axis of the aircraft fuselage,

(ii) determining, in dependence on the first signal, whether the steering angle is greater than a predetermined value, and if the steering angle is greater than the predetermined value,

iii) generating an alarm.

20. A method according to claim 19, wherein the step of determining whether the steering angle is greater than the predetermined value is performed by a comparator unit, the method further comprising the steps of outputting, from the comparator unit, a control signal in dependence on the determination, receiving the control signal at the alarm unit, and generating the alarm in dependence on the control signal.

21. A method according to claim 19, wherein the alarm is generated by an alarm unit located on the aircraft.

22. (canceled)

23. (canceled)

24. A towing vehicle for towing an aircraft, the towing vehicle comprising an alarm unit arranged to receive a first signal from a rotation-measuring device on the aircraft, the alarm unit being further arranged to generate an alarm in dependence on the first signal, when the aircraft steering angle is greater than a predetermined value.

25. (canceled)

26. (canceled)