Anti-flip landing gear for aircraft
A system for controlling landing gear of an aircraft is disclosed. The apparatus includes a sensor for sensing water, wherein the sensor is coupled to the landing gear and a retracting device for retracting the landing gear when the sensor senses a body of water. In one alternative, the aircraft is an amphibious aircraft and the sensor senses electrical conductivity. In another alternative, the retracting device comprises a hydraulic system for deploying and retracting the landing gear, wherein the hydraulic system retracts the landing gear when the sensor senses a body of water. In yet another alternative, the retracting device comprises a locking mechanism that locks the landing gear to the aircraft, wherein the locking mechanism unlocks the landing gear so as to detach it from the aircraft when the sensor senses a body of water.
1. A system for controlling landing gear of an aircraft, comprising:
landing gear including a retracting device for retracting the landing gear;
an electrical conductivity water sensor coupled to the landing gear, wherein the sensor transmits a signal when water is sensed; and
a microprocessor configured for automatically initiating retraction of the landing gear when the signal is received from the water sensor.
2. The system of claim 1 , wherein the aircraft is an amphibious aircraft.
3. The system of claim 2 , wherein the signal is an electrical signal transmitted through a conductor.
4. The system of claim 2 , wherein the retracting device receives a signal from the microprocessor initiating retraction of the landing gear.
5. The system of claim 4 , wherein the retracting device is a mechanical device.
6. The system of claim 4 , wherein the retracting device can further detach the landing gear.
7. The system of claim 4 ,
wherein the retracting device is a hydraulic system for deploying and retracting the landing gear.
8. The system of claim 4 ,
wherein the retracting device is an electrical system for deploying and retracting the landing gear.
9. The system of claim 4 , further comprising:
a locking mechanism that locks the landing gear to the aircraft, wherein the locking mechanism unlocks the landing gear so as to detach it from the aircraft when initiated by the microprocessor.
10. The system of claim 2
wherein the microprocessor is further configured for considering additional sensor data before sending a signal to the landing gear so as to initiate retraction when the signal is received from the water sensor.
11. The system of claim 10 ,
wherein the retracting device is a hydraulic system for deploying and retracting the landing gear.
12. The system of claim 10 ,
wherein the retracting device is an electrical system for deploying and retracting the landing gear.
13. The system of claim 10 , further comprising:
a locking mechanism that locks the landing gear to the aircraft, wherein the locking mechanism receives a signal from the processor to unlock the landing gear so as to detach it from the aircraft.
14. The system of claim 13 , wherein the locking mechanism comprises a pneumatic cylinder and a pneumatic relief valve that releases pressure within the pneumatic cylinder when the locking mechanism receives a signal from the processor to unlock the landing gear so as to detach it from the aircraft.
15. The system of claim 13 , wherein the locking mechanism comprises a mechanical lock that unlocks when the locking mechanism receives a signal from the processor to unlock the landing gear so as to detach it from the aircraft.
16. A system for controlling landing gear of an aircraft, comprising:
landing gear including a retracting device for retracting the landing gear;
at least one accelerometer for sensing forward rotation of the aircraft, wherein the at least one accelerometer transmits a signal when forward rotation of the aircraft is sensed;
a microprocessor configured for automatically initiating retraction of the landing gear when the signal is received from the at least one accelerometer.