Pose control distribution method of aircraft based on multiple execution mechanisms

A multi-actuator and attitude control technology, which is applied in the field of attitude control distribution of aircraft, can solve the problem of idealization of assumed conditions and achieve the effect of improving fault tolerance

Active Publication Date: 2018-01-09
BEIJING INST OF ELECTRONICS SYST ENG
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  • Abstract
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Problems solved by technology

[0006] The object of the present invention is to provide a kind of attitude control assignment method based on the aircraft o...

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  • Pose control distribution method of aircraft based on multiple execution mechanisms
  • Pose control distribution method of aircraft based on multiple execution mechanisms
  • Pose control distribution method of aircraft based on multiple execution mechanisms

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Embodiment Construction

[0060] In order to illustrate the present invention more clearly, the present invention will be further described below in conjunction with preferred embodiments and accompanying drawings. Similar parts in the figures are denoted by the same reference numerals. Those skilled in the art should understand that the content specifically described below is illustrative rather than restrictive, and should not limit the protection scope of the present invention.

[0061] Such as figure 1 As shown, the attitude control distribution method based on the multi-actuator aircraft (hereinafter referred to as the aircraft) provided by the present embodiment includes the following steps:

[0062] S1, establish the attitude kinematics equation of the aircraft;

[0063] S2. Determine the attitude angle of the aircraft through the attitude transformation matrix;

[0064] S3, establishing the attitude dynamic equation of the aircraft;

[0065] S4. Calculate the desired control moment of the a...

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Abstract

The invention discloses a pose control distribution method of an aircraft based on multiple execution mechanisms. The method comprises steps of S1, establishing a pose kinetics equation of the aircraft; S2, through a pose transmission matrix, determining a pose angle of the aircraft; S3, establishing a pose kinetics equation of the aircraft; S4, according a control principle, calculating an expected control torque of the aircraft; and S5, by use of a control distribution algorithm, acquiring a state combination of each execution mechanism of the aircraft at the present moment. According to theinvention, the method is suitable for rapid mechanical operaton and high-precision stable mechanical operation task requirements of large-angle poses of the aircraft.

Description

technical field [0001] The invention relates to the field of aircraft intelligent control. More specifically, it relates to a multi-actuator-based aircraft attitude control assignment method. Background technique [0002] The multi-actuator-based aircraft is a multi-purpose and multi-functional new sheet material combination based on intelligent materials, intelligent adaptive nonlinear control distribution technology, and micro-propulsion system. aircraft. The aircraft has a variable skin, which has the advantages of greatly improving the maneuverability of orbit change, achieving the best aerodynamic performance, improving the reusability, and greatly improving the reconfigurability. [0003] This type of aircraft needs to switch quickly between control modes such as attitude maneuvering and high-precision stability. Fast maneuvering buys more time for attacking enemy targets and avoiding enemy attacks, while fast, high-precision stability after maneuvering is to ensure ...

Claims

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Application Information

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IPC IPC(8): G05D1/08
Inventor 秦雷吴限德李君龙谢晓瑛张锐
Owner BEIJING INST OF ELECTRONICS SYST ENG
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