Flight path optimization using nonlinear programming
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
G06F-007/70
G06F-019/00
G08G-005/00
G05D-001/04
G06F-017/50
G06F-017/10
출원번호
US-0844892
(2015-09-03)
등록번호
US-9564056
(2017-02-07)
발명자
/ 주소
Ghaemi, Reza
Westervelt, Eric Richard
Darnell, Mark
출원인 / 주소
GENERAL ELECTRIC COMPANY
대리인 / 주소
Buckley, Maschoff & Talwalkar LLC
인용정보
피인용 횟수 :
0인용 특허 :
8
초록▼
A method, medium, and system to receive a mathematical model representation of performance characteristics for an aircraft and an engine combination; perform a projection based model order reduction on the mathematical model representation; eliminate, based on the projected model, fast dynamics comp
A method, medium, and system to receive a mathematical model representation of performance characteristics for an aircraft and an engine combination; perform a projection based model order reduction on the mathematical model representation; eliminate, based on the projected model, fast dynamics components of the mathematical model representation; determine a reduced order model, as a differential algebraic equation, wherein algebraic equations replace the fast dynamics; set a flight path angle and a throttle level angle as a control to minimize fuel consumption for the modeled aircraft and engine combination; discretize equations of motion for the modeled aircraft and engine combination and formulate optimization equations as a nonlinear programming problem; and determine an optimal open loop control that minimizes fuel consumption for the modeled aircraft and engine combination to climb to a prescribed cruise altitude and airspeed.
대표청구항▼
1. A method of optimizing an operational flight path for a particular aircraft using nonlinear programming, the method comprising: receiving a mathematical model representation of performance characteristics for a particular aircraft and an engine combination, the mathematical model being applicable
1. A method of optimizing an operational flight path for a particular aircraft using nonlinear programming, the method comprising: receiving a mathematical model representation of performance characteristics for a particular aircraft and an engine combination, the mathematical model being applicable to at least one prescribed operating scenario and a representation of performance characteristics for the particular aircraft and engine combination including at least one of engine degradation characteristics, fuel burn as a function of flight variables, a flight dynamics model, and combinations thereof;performing a projection based model order reduction on the mathematical model representation for the particular aircraft and an engine combination;eliminating, based on the projected model, fast dynamics components of the mathematical model representation;determining a reduced order model, as a differential algebraic equation, wherein algebraic equations replace the fast dynamics;setting a flight path angle and a throttle lever angle as a control to minimize fuel consumption for the modeled aircraft and engine combination;defining a climb terminal cost as a function of cruise altitude and an airspeed;discretizing equations of motion for the modeled aircraft and engine combination and formulating optimization equations as a nonlinear programming problem;determining an optimal open loop control that minimizes fuel consumption for the modeled aircraft and engine combination to climb to a prescribed cruise altitude and airspeed corresponding to the at least one prescribed operating scenario;generating a flight path based on the determined optimal open loop control; andnavigating, based on the generated flight path, the particular aircraft and an engine combination in one of the prescribed operating scenarios. 2. The method of claim 1, further comprising verifying the mathematical model representation of the performance characteristics for the aircraft and engine combination. 3. The method of claim 1, wherein the fast dynamics components of the mathematical model representation are eliminated by setting a pitch moment and vertical forces for the modeled aircraft and engine combination to equilibrium values. 4. The method of claim 1, further comprising determining a flight trajectory from the determined optimal open loop control and equations of motion for the modeled aircraft and engine. 5. The method of claim 1, wherein a climb speed (and thrust) for the modeled aircraft and engine combination to climb to the prescribed cruise altitude and airspeed is variable. 6. The method of claim 1, wherein the mathematical model representation of performance characteristics for the aircraft and engine combination comprises at least one of engine degradation characteristics, fuel burn as a function of flight variables, a flight dynamics model, and combinations thereof. 7. A non-transitory medium storing processor-executable program instructions, the medium comprising program instructions executable by a computer to: receive a mathematical model representation of performance characteristics for a particular aircraft and an engine combination, the mathematical model being applicable to at least one prescribed operating scenario and a representation of performance characteristics for the particular aircraft and engine combination including at least one of engine degradation characteristics, fuel burn as a function of flight variables, a flight dynamics model, and combinations thereof;perform a projection based model order reduction on the mathematical model representation;eliminate, based on the projected model, fast dynamics components of the mathematical model representation;determine a reduced order model, as a differential algebraic equation, wherein algebraic equations replace the fast dynamics;set a flight path angle and a throttle lever angle as a control to minimize fuel consumption for the modeled aircraft and engine combination;define a climb terminal cost as a function of cruise altitude and an airspeed;discretize equations of motion for the modeled aircraft and engine combination and formulate optimization equations as a nonlinear programming problem;determine an optimal open loop control that minimizes fuel consumption for the modeled aircraft and engine combination to climb to a prescribed cruise altitude and airspeed corresponding to the at least one prescribed operating scenario;generate a flight path based on the determined optimal open loop control; andnavigate, based on the generated flight path, the particular aircraft and an engine combination in one of the prescribed operating scenarios. 8. The medium of claim 7, further comprising program instructions executable by a computer to verify the mathematical model representation of the performance characteristics for the aircraft and engine combination. 9. The medium of claim 7, wherein the fast dynamics components of the mathematical model representation are eliminated by setting a pitch moment and vertical forces for the modeled aircraft and engine combination to equilibrium values. 10. The medium of claim 7, further comprising program instructions executable by a computer to determine a flight trajectory from the determined optimal open loop control and equations of motion for the modeled aircraft and engine. 11. The medium of claim 7, wherein a climb speed (and thrust) for the modeled aircraft and engine combination to climb to the prescribed cruise altitude and airspeed is variable. 12. The medium of claim 7, wherein the mathematical model representation of performance characteristics for the aircraft and engine combination comprises at least one of engine degradation characteristics, fuel burn as a function of flight variables, a flight dynamics model, and combinations thereof. 13. A system comprising: a computing device comprising: a memory storing processor-executable program instructions; anda processor to execute the processor-executable program instructions to cause the computing device to:receive a mathematical model representation of performance characteristics for a particular aircraft and an engine combination, the mathematical model being applicable to at least one prescribed operating scenario and a representation of performance characteristics for the particular aircraft and engine combination including at least one of engine degradation characteristics, fuel burn as a function of flight variables, a flight dynamics model, and combinations thereof;perform a projection based model order reduction on the mathematical model representation;eliminate, based on the projected model, fast dynamics components of the mathematical model representation;determine a reduced order model, as a differential algebraic equation, wherein algebraic equations replace the fast dynamics;set a flight path angle and a throttle level angle as a control to minimize fuel consumption for the modeled aircraft and engine combination;define a climb terminal cost as a function of cruise altitude and an airspeed;discretize equations of motion for the modeled aircraft and engine combination and formulate optimization equations as a nonlinear programming problem; anddetermine an optimal open loop control that minimizes fuel consumption for the modeled aircraft and engine combination to climb to a prescribed cruise altitude and airspeed corresponding to the at least one prescribed operating scenario;generate a flight path based on the determined optimal open loop control; andnavigate, based on the generated flight path, the particular aircraft and an engine combination in one of the prescribed operating scenarios. 14. The system of claim 13, further comprising verifying the mathematical model representation of the performance characteristics for the aircraft and engine combination. 15. The system of claim 13, wherein the fast dynamics components of the mathematical model representation are eliminated by setting a pitch moment and vertical forces for the modeled aircraft and engine combination to equilibrium values. 16. The system of claim 13, further comprising determining a flight trajectory from the determined optimal open loop control and equations of motion for the modeled aircraft and engine. 17. The system of claim 13, wherein a climb speed (and thrust) for the modeled aircraft and engine combination to climb to the prescribed cruise altitude and airspeed is variable. 18. The system of claim 13, wherein the mathematical model representation of performance characteristics for the aircraft and engine combination comprises at least one of engine degradation characteristics, fuel burn as a function of flight variables, a flight dynamics model, and combinations thereof.
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이 특허에 인용된 특허 (8)
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Covington, Charles Eric; Tucker, Brian E.; Priest, Thomas B.; Platz, David A.; McCollough, James M., System and method for economic usage of an aircraft.
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