- Document Number:
20120078450
- Appl. No:
12/891581
- Application Filed:
September 27, 2010
- Abstract:
Methods and systems are provided for executing a single continuous altitude change by an aircraft to cruise altitude using an electronic flight bag via a flight management system. The method comprises the determination of an altitude change in a flight plan during the cruise phase of the flight plan. Based on the altitude change and a mathematical model of the aircraft an optimum vertical trajectory profile or the aircraft is determined from which an angle of attack (AOA) and a thrust is derived to achieve the optimum vertical trajectory. From the AOA and the thrust, the required aircraft control variables are determined that may be applied to the engines and the control surface actuators of the aircraft.
- Inventors:
Marche, Stephane (Toulouse, FR); Krupansky, Petr (Veverska Bityska, CZ); Neuzil, Tomas (Brno, CZ); Papageorgiou, George (Toulouse, FR); Derouineau, Jean-Luc (Toulouse, FR)
- Assignees:
HONEYWELL INTERNATIONAL INC. (Morristown, NJ, US)
- Claim:
1. A method for executing a single continuous altitude change by an aircraft to a cruise altitude, comprising: determining an optimum vertical trajectory profile of the aircraft based at least in part on a mathematical model of the aircraft and the altitude change; generating aircraft control variables necessary in real time to execute the optimum vertical trajectory; applying the control variables to one or more aircraft components to effectuate the single continuous altitude change to the cruise altitude by the aircraft; and; repeating the generating and applying steps.
- Claim:
2. The method of claim 1, further comprising determining an angle-of-attack (AOA) and a thrust based at least in part on the vertical trajectory profile that will create sufficient lift to move the aircraft to the cruise altitude in a single continuous altitude change.
- Claim:
3. The method of claim 2, wherein the repeating the generating and applying steps also includes a step of determining the AOA and thrust based at least in part on the vertical trajectory profile that will create sufficient lift to move the aircraft to the cruise altitude in a single continuous altitude change.
- Claim:
4. The method of claim 2, wherein an aircraft pilot applies the control variables.
- Claim:
5. The method of claim 2, wherein the aircraft components are one of an engine and an air control surface.
- Claim:
6. The method of claim 5, wherein an electronic flight bag module applies the control variables.
- Claim:
7. The method of claim 5, wherein a flight management system (FMS) applies the control variables.
- Claim:
8. The method of claim 1, wherein the control variables comprise a rate of ascent and a change in speed.
- Claim:
9. The method of claim 1, wherein the repeating of the generating and applying steps is done iteratively and in real time.
- Claim:
10. A system for executing a single continuous altitude change by an aircraft to a cruise altitude, comprising: a memory device containing a mathematical model of the aircraft stored thereon; a first module configured to compute an optimal vertical profile based in part on the mathematical model and atmospheric conditions, iteratively and in real time; and a second module configured to generate one or more aircraft control variables based at least in part on the optimal vertical profile iteratively and in real time, wherein the one or more aircraft control variables drives one of an aircraft control surface and an aircraft engine.
- Claim:
11. The system of claim 10, wherein the optimal vertical profile comprises an optimal angle of attack (AOA) and an optimal thrust.
- Claim:
12. The system of claim 11, further comprising a third module configured to interface the one or more aircraft flight control variables to the one of an aircraft control surface and an aircraft engine.
- Claim:
13. The system of claim 12, wherein the third module translates the one or more flight control variables into graphical flight control actions for visual display to a pilot.
- Claim:
14. The subsystem of claim 13, wherein the third module is resident in an electronic flight bag.
- Claim:
15. The system of claim 13, wherein the flight control actions are communicated to the pilot audibly.
- Claim:
16. The system of claim 10, wherein the first module is configured to optimize the vertical profile by varying a ratio of aircraft drag to lift.
- Claim:
17. The system of claim 15, wherein the first module is configured to optimize the vertical profile by varying a thrust specific fuel consumption in determining thrust.
- Claim:
18. The system of claim 10, wherein the pilot applies the control variables.
- Claim:
19. The system of claim 17, the second modules determines the optimal AOA and T using the inverse of the closed loop aircraft dynamics.
- Claim:
20. A system for executing an single continuous altitude change by an aircraft to a cruise altitude, comprising: a mathematical model of the aircraft; a first means for computing an optimal vertical profile based in part on the mathematical model; a second means for generating one or more aircraft control variables based at least in part on the optimal vertical profile; and a third means for driving one of an aircraft control surface and an aircraft engine; based at least in part on the one or more aircraft control variables.
- Current U.S. Class:
701/6
- Current International Class:
05
- Accession Number:
edspap.20120078450
Processing Request
No Comments.