Flight control system for aircraft having multi-functional flight control surface

Patent metadata

Field	Value
Publication number	US-11059569-B1
Application number	US-201816231385-A
Country	US
Kind code	B1
Filing date	Dec 21, 2018
Priority date	Dec 29, 2017
Publication date	Jul 13, 2021
Grant date	Jul 13, 2021

Abstract

A flight control system for an aircraft having a multi-functional flight control surface. The aircraft has at least one multi-functional flight control surface formed by a sequence of flaps. The shape of each multi-functional flight control surface may be configured by a flight control to simultaneously adjust a trajectory of the aircraft in two or more of a pitch direction, a roll direction, and a yaw direction. The flight control for operating said the multi-functional flight control surface responds to both pilot commands and machine-generated commands. The machine-generated commands configure the shape of the surface of each multi-functional flight control surface in real-time based, at least in part, upon a set of flight objectives comprising: (a) minimizing drag of the aircraft, (b) aeroelastic modal suppression for the aircraft, and (c) maneuver load alleviation in the aircraft.

First claim

What is claimed is:

1. A flight control system for instructing an aircraft, the aircraft comprising at least one multi-functional flight control surface, wherein said at least one multi-functional flight control surface comprises a sequence of flaps, wherein a shape of each surface, of said at least one multi-functional flight control surface, may be configured by the flight control to adjust a trajectory of the aircraft in two or more of a pitch direction, a roll direction, and a yaw direction, the flight control system comprising:
one or more processors; and
one or more non-transitory computer-readable storage mediums storing one or
more sequences of instructions, which when executed by one or more processors, cause:
the flight control system to operate said at least one multi-functional flight control surface, wherein said flight control system responds to both pilot commands and machine-generated commands, and wherein said machine-generated commands configure the shape of said each surface of said at least one multi-functional flight control surface in real-time based, at least in part, upon a set of flight objectives comprising: (a) minimizing drag of said aircraft, (b) aeroelastic modal suppression for said aircraft, and (c) maneuver load alleviation in said aircraft,

wherein said flight control system adjusts the shape of said at least one multi-functional flight control surface to minimize the maneuver load upon the aircraft using a least-square adaptive control method.

2. The flight control system of claim 1 , wherein said flight control system determines, in real-time, a set of multiple competing requirements for each of said set of flight objectives to determine how to instruct said at least one multi-functional flight control surface in a manner that possess the best compromise for said set of multiple competing requirements.

3. The flight control system of claim 1 , wherein said flight control system specifies deflection commands for said at least one multi-functional flight control surface to change a lift distribution that results in a reduction in a wing root bending moment of an aircraft wing by shifting a lift distribution toward the inboard of the aircraft wing.

4. The flight control system of claim 1 , wherein execution of the one or more sequences of instructions further cause the flight control system to:
upon determining that the aircraft is experiencing a gust, prioritize the maneuver load alleviation flight objective over the drag minimization flight objective to reduce a structural load placed upon the aircraft.

5. The flight control of claim 1 , wherein execution of the one or more sequences of instructions further cause the flight control system to:
upon determining that the aircraft is no longer experiencing a gust, increase a priority applied to the drag minimization flight objective, and decrease the priority applied to the maneuver load alleviation flight objective, to enable the aircraft to operate in a fuel economy mode.

6. The flight control system of claim 1 , wherein said at least one multi-functional flight control surface comprises one or more accelerometers, and wherein said set of flight objectives further includes minimizing a gust load upon the aircraft.

7. The flight control system of claim 6 , wherein said flight control system adjusts the shape of said at least one multi-functional flight control surface to minimize the gust load upon the aircraft by estimating the gust load upon the aircraft using measurements taken by said one or more accelerometers and a least-squares gradient.

8. A non-transitory computer readable storage medium storing one or more sequences of instructions for a flight control system for instructing an aircraft, the aircraft comprising: at least one multi-functional flight control surface, wherein said at least one multi-functional flight control surface comprises a sequence of flaps, wherein a shape of each surface, of said at least one multi-functional flight control surface, may be configured by a flight control to adjust a trajectory of the aircraft in two or more of a pitch direction, a roll direction, and a yaw direction, and wherein execution of the one or more sequences of instructions cause:
the flight control system to operate said at least one multi-functional flight control surface, wherein said flight control system responds to both pilot commands and machine-generated commands, and wherein said machine-generated commands configure the shape of said each surface of said at least one multi-functional flight control surface in real-time based, at least in part, upon a set of flight objectives comprising: (a) minimizing drag of said aircraft, (b) aeroelastic modal suppression for said aircraft, and (c) maneuver load alleviation in said aircraft,

wherein said flight control system adjusts the shape of said at least one multi-functional flight control surface to minimize the maneuver load upon the aircraft using a least-square adaptive control method.

9. The non-transitory computer readable storage medium of claim 8 , wherein said flight control system determines, in real-time, a set of multiple competing requirements for each of said set of flight objectives to determine how to instruct said at least one multi-functional flight control surface in a manner that possess the best compromise for said set of multiple competing requirements.

10. The non-transitory computer readable storage medium of claim 8 , wherein said flight control system specifies deflection commands for said at least one multi-functional flight control surface to change a lift distribution that results in a reduction in a wing root bending moment of an aircraft wing by shifting a lift distribution toward the inboard of the aircraft wing.

11. The non-transitory computer readable storage medium of claim 8 , wherein execution of the one or more sequences of instructions further cause:
upon determining that the aircraft is experiencing a gust, prioritizing the maneuver load alleviation flight objective over the drag minimization flight objective to reduce a structural load placed upon the aircraft.

12. The non-transitory computer readable storage medium of claim 8 , wherein execution of the one or more sequences of instructions further cause:
upon determining that the aircraft is no longer experiencing a gust, increasing a priority applied to the drag minimization flight objective, and decreasing the priority applied to the maneuver load alleviation flight objective, to enable the aircraft to operate in a fuel economy mode.

13. The non-transitory computer readable storage medium of claim 8 , wherein said at least one multi-functional flight control surface comprises one or more accelerometers, and wherein said set of flight objectives further includes minimizing a gust load upon the aircraft.

14. The non-transitory computer readable storage medium of claim 13 , wherein said flight control system adjusts the shape of said at least one multi-functional flight control surface to minimize the gust load upon the aircraft by estimating the gust load upon the aircraft using measurements taken by said one or more accelerometers and a least-squares gradient.

15. A method for instructing an aircraft, the aircraft comprising at least one multi-functional flight control surface, wherein said at least one multi-functional flight control surface comprises a sequence of flaps, wherein a shape of each surface, of said at least one multi-functional flight control surface, may be configured by a flight control system to adjust a trajectory of the aircraft in two or more of a pitch direction,

Assignees

• Us Administrator Of The Nasa
• Nasa

Inventors

• Nguyen Nhan Thanh
• Hashemi Kelley Elizabeth

Classifications

• Y02T50/40

  Weight reduction · CPC title

• Y02T50/10

  Drag reduction · CPC title

• B64C2009/005

  Ailerons · CPC title

• B64C2003/445

  by changing shape according to the speed, e.g. by morphing · CPC title

• B64C13/16

  actuated automatically, e.g. responsive to gust detectors · CPC title