Systems and methods for alleviating aircraft loads with plasma actuators

Patent metadata

Field	Value
Publication number	US-9446840-B2
Application number	US-16619908-A
Country	US
Kind code	B2
Filing date	Jul 1, 2008
Priority date	Jul 1, 2008
Publication date	Sep 20, 2016
Grant date	Sep 20, 2016

Abstract

Systems and methods for alleviating aircraft loads with plasma actuators are disclosed. A method for operating an aircraft in accordance with a particular embodiment includes receiving an input corresponding to an aircraft component structural response to an aerodynamic load. The method can further include, based at least in part on the input corresponding to the aircraft component's structural response, reducing the structural response to the aerodynamic load by activating at least one plasma actuator carried by the aircraft, in accordance with one or more activation parameters.

First claim

We claim:

1. A method for establishing operational parameters for an aircraft, comprising:
receiving a baseline structural response profile corresponding to expected total flight time of the aircraft as a function of flight condition, the profile including an expected structural response level at a first corresponding total flight time value;
selecting activation parameters for one or more plasma actuators carried by the aircraft based on an effect of the parameters to shift the total flight time value at which the expected structural response level occurs from the first corresponding total flight time value to a second corresponding total flight time value less than the first; and
programming a controller coupled to the one or more plasma actuators in accordance with the selected activation parameters.

2. The method of claim 1 wherein receiving a baseline structural response profile includes receiving an input that in turn includes an amplitude, frequency and phase of an aircraft component structural response, and selecting activation parameters includes selecting activation parameters that alter the amplitude of the aircraft component structural response by generating an effect in a flowfield adjacent to the one or more plasma actuators.

3. The method of claim 1 wherein selecting activation parameters includes selecting activation parameters that, when implemented, increase a fatigue life of a component of the aircraft.

4. The method of claim 1 wherein selecting activation parameters includes selecting activation parameters that, when implemented, directly reduce an aerodynamic load on the aircraft.

5. The method of claim 1 wherein selecting activation parameters includes selecting activation parameters that, when implemented, control a location at which a shock is formed in a flow adjacent to a surface of the aircraft.

6. The method of claim 1 wherein selecting activation parameters includes selecting activation parameters that, when implemented, control a location at which a boundary layer transition occurs in a flow adjacent to a surface of the aircraft.

7. The method of claim 1 wherein selecting activation parameters includes selecting activation parameters that, when implemented, shift a location at which the aerodynamic load is positioned, relative to an elastic axis of a component of the aircraft.

8. The method of claim 7 wherein the activation parameters, when implemented, reduce a moment on a component of the aircraft resulting from the aerodynamic load by moving the location closer to the elastic axis.

9. The method of claim 1 wherein the structural response level has a representative response frequency and response phase and wherein selecting activation parameters includes selecting an activation frequency and an activation phase, the activation phase being approximately 90 degrees offset from the response phase.

10. The method of claim 1 wherein the expected structural response level is a peak structural response level.

11. The method of claim 1 , further comprising reducing the structural response level by 10% or more.

12. The method of claim 1 , further comprising reducing the structural response level.

13. The method of claim 1 wherein the flight condition includes Mach number.

14. The method of claim 1 wherein the flight condition includes angle of attack.

15. The method of claim 1 wherein the flight condition includes dynamic pressure.

Assignees

• Drouin Jr Donald V
• Schwimley Scott Lee
• Boeing Co

Inventors

• Drouin Jr Donald V
• Schwimley Scott Lee

Classifications

• H05H1/2439

  Surface discharges, e.g. air flow control · CPC title

• Y02T50/166

  Cross-Sectional Technologies · mapped topic

• H05H1/2406

  using dielectric barrier discharges, i.e. with a dielectric interposed between the electrodes · CPC title

• B64C2230/12

  by using electromagnetic tiles, fluid ionizers, static charges or plasma · CPC title

• B64C23/005 Primary

  by other means not covered by groups B64C23/02 - B64C23/08, e.g. by electric charges, magnetic panels, piezoelectric elements, static charges or ultrasounds · CPC title