IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0469976
(2009-05-21)
|
등록번호 |
US-8180504
(2012-05-15)
|
발명자
/ 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
10 인용 특허 :
19 |
초록
▼
A system for use in monitoring, measuring, computing and displaying the rate of compression of aircraft landing gear struts, experienced while aircraft are executing either normal or hard landing events. Further by measuring the vertical compression rate of the landing gear strut, thus with aircraft
A system for use in monitoring, measuring, computing and displaying the rate of compression of aircraft landing gear struts, experienced while aircraft are executing either normal or hard landing events. Further by measuring the vertical compression rate of the landing gear strut, thus with aircraft hull angle correction to horizontal, determining the vertical sink-rate of the aircraft, as it comes into initial contact with the ground. Accelerometers are attached to opposing sides of a compressible landing gear strut, monitoring and measuring parallel data streams; then identifying differential acceleration data streams, which computed through mathematical algorithms measure the collapse rate of the landing gear strut. Pressure sensors are attached to the working pressure within the landing gear strut, so to monitor in-flight landing gear strut pre-charge pressure, until such time as the pre-charge pressure suddenly increases, to detect the aircraft has come into initial contact with the ground. A method of operating an aircraft at an increased maximum landing weight limitation.
대표청구항
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1. A method of monitoring landing gear on an aircraft at initial contact of the landing gear with the ground, each landing gear comprising a telescopic strut which is capable of extension and compression, the landing gear strut comprising a hull portion, which remains fixed to a hull of the aircraft
1. A method of monitoring landing gear on an aircraft at initial contact of the landing gear with the ground, each landing gear comprising a telescopic strut which is capable of extension and compression, the landing gear strut comprising a hull portion, which remains fixed to a hull of the aircraft when the landing gear is deployed for landing, and a tire portion, which is capable of moving at a different velocity, with respect to the hull portion, comprising the steps of: a) providing a first accelerometer on the hull of the aircraft;b) providing a second accelerometer on the tire portion of the strut;c) measuring the acceleration of the hull of the aircraft with the first accelerometer as the aircraft lands;d) measuring the acceleration of the tire portion of the strut with the second accelerometer as the aircraft lands;e) comparing the acceleration of the hull of the aircraft with the acceleration of the tire portion of the strut;f) determining the initial contact of the landing gear from the comparison. 2. The method of claim 1 wherein the step of providing a first accelerometer on the hull of the aircraft further comprises the step of providing the accelerometer on the hull portion of the strut. 3. The method of claim 1 further comprising the step of determining the rate of compression of the landing gear strut. 4. The method of claim 1 further comprising the step of determining the descent velocity of the strut at initial contact. 5. The method of claim 4 wherein the step of determining the descent velocity of the strut at initial contact further comprises the step of determining the descent velocity of the hull portion of the strut. 6. The method of claim 5, further comprising the steps of: a) determining if the descent velocity at initial contact exceeds a predetermined threshold;b) providing an indication if the descent velocity at initial contact exceeds the predetermined threshold. 7. The method of claim 4 wherein the step of determining the descent velocity of the strut at initial contact further comprises the step of determining the descent velocity of the tire portion of the strut. 8. The method of claim 1, further comprising the steps of a) measuring the pressure inside of the strut;b) determining from the pressure and accelerations when the initial contact of the landing gear has occurred. 9. The method of claim 8, further comprising the step of determining the descent velocity of the hull portion of the strut. 10. An apparatus for monitoring landing gear of an aircraft during initial landing gear contact with the ground, each landing gear comprising a telescopic strut with a compressible fluid, the landing gear strut comprising a hull portion which remains fixed to a hull of the aircraft when the landing gear is deployed for landing, and a tire portion, which is capable of moving at a different velocity, with respect to the hull portion, comprising: a) a first accelerometer mounted to the hull of the aircraft;b) a second accelerometer mounted to the tire portion of the strut;c) a processor having a first input connected to the first accelerometer and a second input connected to the second accelerometer, the processor recording the acceleration of the hull portion of the strut as measured by the first accelerometer and the acceleration of the tire portion of the strut is measured by the second accelerometer, the processor comparing the acceleration of the hull portion with the acceleration of the tire portion, the processor determining the initial contact of the landing gear from the comparison. 11. The apparatus of claim 10 wherein the first accelerometer is mounted on the hull portion of the aircraft strut. 12. The apparatus of claim 10 wherein the processor determines the descent velocity of the hull portion of the strut at initial contact. 13. The apparatus of claim 12 wherein the processor determines if the descent velocity exceeds a predetermined threshold, and if so, provides an indication that the descent velocity exceeds the predetermined threshold. 14. The apparatus of claim 10, further comprising: a) a pressure sensor located so as to measure the pressure inside the strut;b) the processor has an input that is connected to the pressure sensor, the processor determines from the pressure and the accelerations when the initial contact of the landing gear occurs. 15. The apparatus of claim 14 wherein the processor determines the descent velocity of the hull portion of the strut as compared to the acceleration of the tire portion of the strut. 16. A method of operating an aircraft, the aircraft having a first maximum landing weight based upon a first assumed maximum descent velocity, the aircraft has landing gear, each landing gear comprising a telescopic strut which is capable of extension and compression, the landing gear strut comprising a hull portion, which remains fixed to a hull of the aircraft when the landing gear is deployed for landing, and a tire portion, which is capable of moving at a different velocity with respect to the hull portion, comprising the steps of: a) obtaining vertical velocities of the aircraft at initial contact of the aircraft with the ground during landing events by measuring and recording the descent velocities of the aircraft at initial contact of the aircraft with the ground, comprising the steps of; i) providing a first accelerometer on the hull portion of the strut;ii) providing a second accelerometer on the tire portion of the strut;iii) measuring the acceleration of the hull portion with the first accelerometer as the aircraft lands;iv) measuring the acceleration of the tire portion with the second accelerometer as the aircraft lands;v) comparing the acceleration of the hull portion with the acceleration of the tire portion;vi) determining the descent velocity of the hull portion of the strut, at initial contact with the ground;b) based upon the obtained vertical velocities of the aircraft at initial contact with the ground, operating the aircraft at a second assumed maximum descent velocity while measuring and recording the vertical velocities of the aircraft at initial contact of the aircraft with the ground during landing events, the second assumed maximum descent velocity being less than the first assumed maximum descent velocity;c) operating the aircraft at a second maximum landing weight based upon the second assumed maximum descent velocity. 17. The method of claim 16 wherein the second maximum landing weight is greater than the first maximum landing weight. 18. The method of claim 16 wherein the first assumed maximum descent velocity is 10 fps. 19. The method of claim 18 wherein the step of operating the aircraft at a second maximum descent velocity that is less than 10 fps further comprises the step of operating the aircraft at or below a second maximum descent velocity of 9.8 fps. 20. The method of claim 18 wherein the step of operating the aircraft at a second maximum descent velocity that is less than 10 fps further comprises the step of operating the aircraft at or below a second maximum descent velocity of 9.6 fps. 21. The method of claim 18 wherein the step of operating the aircraft at a second maximum descent velocity that is less than 10 fps further comprises the steps of: a) measuring and recording the vertical velocity of the aircraft at initial contact of the aircraft with the ground during a landing event;b) determining if the vertical velocity exceeds a predetermined threshold;c) if the vertical velocity exceeds a predetermined threshold, then inspecting the aircraft before resuming flight operations. 22. A method of operating an aircraft, the aircraft having a maximum landing weight based upon a first assumed maximum descent velocity, the aircraft has landing gear, each landing gear comprising a telescopic strut which is capable of extension and compression, the landing gear strut comprising a hull portion, which remains fixed to a hull of the aircraft when the landing gear is deployed for landing, and a tire portion, which is capable of moving at a different velocity with respect to the hull portion, comprising the steps of: a) measuring and recording the descent velocities of the aircraft at initial contact of the aircraft with the ground, during landing events further comprising the steps of; i) providing a first accelerometer on the hull portion of the strut;ii) providing a second accelerometer on the tire portion of the strut;iii) measuring the acceleration of the hull portion with the first accelerometer as the aircraft lands;iv) measuring the acceleration of the tire portion with the second accelerometer as the aircraft lands;v) comparing the acceleration of the hull portion with the acceleration of the tire portion;vi) determining the descent velocity of the hull portion of the strut, at initial contact with the ground;b) determining if a measured descent velocity of the aircraft at initial contact with the ground exceeds a predetermined threshold;c) inspecting the aircraft, upon determining if the measured descent velocity exceeds the predetermined threshold;d) operating the aircraft at a second assumed maximum descent velocity that is less than the first assumed maximum descent velocity;e) operating the aircraft at a second maximum landing weight that is greater than the first maximum landing weight, based upon the second assumed maximum descent velocity.
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