Energy-angular momentum diagnostic method for launch vehicle performance
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
G01C-023/00
G05D-001/00
G05D-003/00
G06F-007/00
출원번호
US-0746307
(2013-01-22)
등록번호
US-8676407
(2014-03-18)
발명자
/ 주소
Patera, Russell Paul
출원인 / 주소
The Aerospace Corporation
대리인 / 주소
LeonardPatel PC
인용정보
피인용 횟수 :
1인용 특허 :
5
초록▼
Novel diagnostic methods for performance of a launch vehicle are disclosed. A method may include computing energy for a pre-flight trajectory of a vehicle using angular momentum of the vehicle, and comparing a difference in energy between the energy for the pre-flight trajectory of the vehicle and e
Novel diagnostic methods for performance of a launch vehicle are disclosed. A method may include computing energy for a pre-flight trajectory of a vehicle using angular momentum of the vehicle, and comparing a difference in energy between the energy for the pre-flight trajectory of the vehicle and energy for a flight trajectory of the vehicle.
대표청구항▼
1. A computer-implemented method, comprising: computing, by a processor, energy for a pre-flight trajectory of a vehicle using angular momentum of the vehicle; andcomparing, by the processor, a difference in energy between the energy for the pre-flight trajectory of the vehicle and energy for a flig
1. A computer-implemented method, comprising: computing, by a processor, energy for a pre-flight trajectory of a vehicle using angular momentum of the vehicle; andcomparing, by the processor, a difference in energy between the energy for the pre-flight trajectory of the vehicle and energy for a flight trajectory of the vehicle to detect anomalous vehicle behavior for correction of future launches, whereinthe energy for the flight trajectory of the vehicle is computed based on position and velocity vectors received from an inertial navigation unit after completion of the flight. 2. The computer-implemented method of claim 1, further comprising: computing, by the processor, the angular momentum of the vehicle using an Earth-centered inertial position and velocity of the vehicle. 3. The computer-implemented method of claim 2, further comprising: computing, by the processor, a magnitude of the angular momentum of the vehicle. 4. The computer-implemented method of claim 3, further comprising: computing, by the processor, the energy for the pre-flight trajectory of the vehicle using Earth-centered inertial position, velocity, a universal gravitational constant, and a mass of Earth. 5. The computer-implemented method of claim 3, further comprising: computing, by the processor, the energy for the flight trajectory of the vehicle using Earth-centered inertial position and velocity, a universal gravitational constant, and a mass of Earth. 6. The computer-implemented method of claim 1, further comprising: computing, by the processor, the energy difference between the pre-flight trajectory of the vehicle and the flight trajectory of the vehicle using a magnitude of the angular momentum of the vehicle. 7. The computer-implemented method of claim 1, further comprising: computing, by the processor, the energy difference as a function of flight trajectory time between the pre-flight trajectory of the vehicle and the flight trajectory of the vehicle using a magnitude of the angular momentum of the vehicle. 8. The computer-implemented method of claim 1, further comprising: computing, by the processor, a difference in inclination between the pre-flight trajectory of the vehicle and the flight trajectory of the vehicle using a magnitude of the angular momentum of the vehicle. 9. A computer-implemented method, comprising: computing, by a processor, pre-flight trajectory energy values that correspond to flight trajectory angular momentum values of a vehicle; andcomparing, by the processor, a difference in energy values between the pre-flight trajectory energy values and flight trajectory energy values of the vehicle to detect anomalous vehicle behavior for correction of future launches, whereinthe flight trajectory energy values of the vehicle are computed based on position and velocity vectors received from an inertial navigation unit after completion of the flight. 10. The computer-implemented method of claim 9, further comprising: receiving, by the processor, telemetry data comprising inertial navigation unit based inertial position and velocity; andcomputing, by the processor, the flight trajectory angular momentum values of the vehicle. 11. The computer-implemented method of claim 10, further comprising: computing, by the processor, the flight trajectory energy values that correspond to the flight trajectory angular momentum values of the vehicle. 12. The computer-implemented method of claim 9, further comprising: dividing, by the processor, the pre-flight trajectory of the vehicle into a plurality of segments, whereineach of the plurality of segments is represented with a low order polynomial of energy as a function of angular momentum. 13. The computer-implemented method of claim 12, further comprising: computing, by the processor, the energy values of the pre-flight trajectory using each of the plurality of segments with an associated low order polynomial. 14. The computer-implemented method of claim 9, further comprising: searching for two sequential angular momentum values of the pre-flight trajectory such that flight trajectory angular momentum value is between the two sequential angular momentum values; andcomputing, by the processor, the energy of the pre-flight trajectory using the two sequential angular momentum values and the flight trajectory angular momentum value. 15. The computer-implemented method of claim 9, further comprising: computing, by the processor, pre-flight trajectory inclination values that correspond to flight trajectory angular momentum values of a vehicle; andcomparing, by the processor, a difference in inclination values between the pre-flight trajectory inclination values and the flight trajectory inclination values of the vehicle. 16. An apparatus, comprising: at least one processor; andmemory comprising computer program code, whereinthe computer program code, together with the at least one processor, are configured to cause the apparatus to compute pre-flight trajectory energy values that correspond to flight trajectory angular momentum values of a vehicle; andcompare a difference in energy values between the pre-flight trajectory energy values and flight trajectory energy values of the vehicle to detect anomalous vehicle behavior for correction of future launches, whereinthe flight trajectory energy values of the vehicle are computed based on position and velocity vectors received from an inertial navigation unit after completion of the flight. 17. The apparatus of claim 16, wherein the computer program code, together with the at least one processor, are further configured to cause the apparatus to receive telemetry data comprising inertial navigation unit based inertial position and velocity, and compute the flight trajectory angular momentum values of the vehicle. 18. The apparatus of claim 17, wherein the computer program code, together with the at least one processor, are further configured to cause the apparatus to compute the flight trajectory energy values that correspond to the flight trajectory angular momentum values of the vehicle. 19. The apparatus of claim 16, wherein the computer program code, together with the at least one processor, are further configured to cause the apparatus to: divide the pre-flight trajectory of the vehicle into a plurality of segments, whereineach of the plurality of segments is represented by a low order polynomial of energy as a function of angular momentum. 20. The apparatus of claim 19, wherein the computer program code, together with the at least one processor, are further configured to cause the apparatus to compute the energy values of the pre-flight trajectory using each of the plurality of segments with an associated low order polynomial. 21. The apparatus of claim 16, wherein the computer program code, together with the at least one processor, are further configured to cause the apparatus to search for two sequential angular momentum values of the pre-flight trajectory such that flight trajectory angular momentum value is between the two sequential angular momentum values, and compute the energy of the pre-flight trajectory using the two sequential angular momentum values and the flight trajectory angular momentum value. 22. The apparatus of claim 16, wherein the computer program code, together with the at least one processor, are further configured to cause the apparatus to compute pre-flight trajectory inclination values that correspond to flight trajectory angular momentum values of a vehicle; andcompare a difference in inclination values between the pre-flight trajectory inclination values and the flight trajectory inclination values of the vehicle.
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이 특허에 인용된 특허 (5)
Surauer Michael (Chieming DEX) Porte Francois (Munich DEX) Bittner Helmut (Munich DEX), Apparatus for controlling the attitude of and stabilizing an elastic body.
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