Method and apparatus for minimizing dynamic structural loads of an aircraft

Patent metadata

Field	Value
Publication number	US-9446837-B2
Application number	US-201214235238-A
Country	US
Kind code	B2
Filing date	Jul 20, 2012
Priority date	Jul 28, 2011
Publication date	Sep 20, 2016
Grant date	Sep 20, 2016

Abstract

A method for dynamically alleviating loads generated on an aircraft by a disturbance of gust involves automatically detecting a disturbance due to gust on a flight of the aircraft. When a disturbance due to gust is detected, control commands for control surfaces are automatically generated and the control commands are applied to actuate the control surfaces. The method also involves dynamically actuating the control surfaces in a prescribed dynamic way in order to minimize not only a first load peak but also at least a second load peak.

First claim

The invention claimed is:

1. A method of dynamically alleviating loads generated on an aircraft by a disturbance of gust, the method comprising the steps of:
automatically detecting a disturbance due to gust on a flight of the aircraft;
automatically generating control commands for control surfaces when a disturbance due to gust is detected;
applying the control commands to actuate the control surfaces;
dynamically actuating the control surfaces in a prescribed dynamic way in order to minimize both a first load peak and a second load peak; and
generating control commands using a predetermined control command sequence that has been pre-determined in a previous control command sequence determining step,
wherein the control command sequence determining step comprises:
determining a load response of the aircraft in response to an actuation of the control surface according to a basis function H i ,
modelling the control command sequence as a linear combination of basis functions in the form of

H
=

∑

i
=
1

n

⁢

⁢

θ
i

·

H
i

wherein θ i represents the i th element of a vector of variable θ,
simulating a typical wind gust shape being alleviated by the control command sequence H, and

determining the vector of variable θ by optimization calculation such that the load response to the typical wind gust shape is minimized.

2. The method according to claim 1 , wherein the control command sequence determining step comprises:
determining an optimized control command sequence in a convex synthesis.

3. The method according to claim 1 , wherein the basis function is an impulse function and the load response is a load response in response to an impulse.

4. The method according to claim 1 , wherein the optimization calculation is performed over discrete time series, wherein H i represents the basis function for the discrete time t i of a series of discrete times t 1 . . . t i . . . t n .

5. The method according to claim 1 , further comprising:
storing the control command sequence determined in the control command sequence determining step in a memory device,
wherein the step of generating the control commands comprises reading out the memory device for generating the predetermined control command sequence.

6. The method according to claim 1 , wherein the control commands are chosen of the following group of control commands:
elevator control commands for actuating an elevator control surface,
spoiler control commands for deflecting spoiler control surfaces arranged on an upper and/or lower surface of a wing of the aircraft, and
aileron control commands for actuating an aileron control surface.

7. An apparatus for dynamically alleviating loads generated on an aircraft by a disturbance of gust, comprising:
a monitor configured to automatically detect a disturbance due to gust;
control command generator configured to automatically generate control commands for an actuating of control surfaces when said disturbance due to gust is detected, wherein the control command generator is configured to dynamically actuate the control surfaces in a prescribed dynamic way in order to minimize both a first load peak and a second load peak; and
a control command sequence determining device configured to determine a control command sequence to be used as the control commands, the control command sequence determining device comprising
a load response determiner configured to determine a load response of the aircraft in response to an actuation of the control surface according to a basis function H i ,
a modeller configured to model the control command sequence as a linear combination of basis functions in the form of

H
=

∑

i
=
1

n

⁢

⁢

θ
i

·

H
i

wherein θ i represents the i th element of a vector of variable θ,
a gust signal simulator configured to simulate a typical wind gust shape to be alleviated by the control command sequence H, and

a determiner configured determine the vector of variable θ by optimization calculation such that the load response to the typical wind gust shape is minimized.

8. The apparatus according to claim 7 , wherein the control command generator comprises a memory device containing a predetermined control command sequence.

9. The apparatus according to claim 7 , wherein the load response determiner is configured to use an impulse function as the basis function and is configured to determine a load response in response to an impulse.

10. The apparatus according to claim 7 , wherein the control command sequence determining device is configured to calculate the optimization over discrete time series, wherein H i represents the basis function for the discrete time t i of a series of discrete times t 1 . . . t i . . . t n .

Assignees

• Wildschek Andreas
• Hanis Tomas
• Eads Deutschland Gmbh

Inventors

• Wildschek Andreas
• Hanis Tomas

Classifications

• B64D45/00

  Aircraft indicators or protectors not otherwise provided for · CPC title

• G05D1/00

  Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots (drive control systems specially adapted for autonomous road vehicles B60W60/00) · CPC title

• G05D1/0066 Primary

  for limitation of acceleration or stress · CPC title

• G05D1/0623

  by acting on the pitch · CPC title

• B64C13/16 Primary

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