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Aircraft attitude control method based on self-adaptive sliding mode

An adaptive sliding mode and attitude control technology, applied in attitude control and other directions, can solve problems such as vibration

Inactive Publication Date: 2014-06-11
湖北蔚蓝通用航空科技股份有限公司
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Although sliding mode control has excellent robustness properties, pure sliding mode control also has disadvantages, such as requiring large control forces and controlling chattering phenomena

Method used

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  • Aircraft attitude control method based on self-adaptive sliding mode
  • Aircraft attitude control method based on self-adaptive sliding mode
  • Aircraft attitude control method based on self-adaptive sliding mode

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Embodiment Construction

[0077] The invention discloses an aircraft attitude control method based on an adaptive sliding mode, comprising the following steps:

[0078] 1) Establish the translational motion equation of the center of mass of the aircraft;

[0079] 2) Consider the influence of the earth's rotation on the attitude control, and obtain the corresponding rotation equation around the center of mass according to the translation motion equation of the center of mass of the aircraft. This equation determines the angle of rotation of the aircraft around the center of mass and its angular rate, which is mainly used to realize the attitude control of the aircraft;

[0080] 3) The reference aerodynamic model is given;

[0081] 4) Adaptive controller design based on Terminal sliding mode (terminal sliding mode), including slow loop controller design and fast loop controller design.

[0082] The translational motion equation of the aircraft center of mass in the aforementioned step 1) is obtained ba...

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Abstract

The invention discloses an aircraft attitude control method based on a self-adaptive sliding mode. The method includes the following steps that firstly, a translational motion equation of the center of mass of an aircraft is built; secondly, the influence of earth rotation on attitude control is taken into consideration, and a corresponding rotation around center of pass equation is obtained according to the translational motion equation of the center of mass of the aircraft, wherein the rotation around center of pass equation determines the rotating angle around the center of mass of the aircraft and the angular rate of the aircraft and is mainly used for achieving attitude control of the aircraft; thirdly, a referenced aerodynamic model is given; fourthly, a self-adaptive controller based on a Terminal sliding mode is designed, wherein a slow loop controller and a quick loop controller are designed.

Description

technical field [0001] The invention relates to the technical field of hypersonic aircraft attitude control, in particular to an aircraft attitude control method based on an adaptive sliding mode. Background technique [0002] The attitude control of the aircraft is mainly used to meet the strict ignition working conditions of the air-breathing ramjet. During the attitude adjustment process, the aircraft also needs to complete actions such as opening the air inlet, injecting fuel, and igniting the engine. Hypersonic vehicles are more and more widely used in various applications at present, and their power coefficients vary greatly with the different working conditions of the engine, which makes the controlled object have strong uncertainty. Due to the hypersonic flow characteristics of the aircraft, its aerodynamic characteristics are strongly coupled with the attitude angle, and the aerodynamic modeling is complex, which is difficult to be directly used in system analysis ...

Claims

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Application Information

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IPC IPC(8): G05D1/08
Inventor 宋谨韩松张庆
Owner 湖北蔚蓝通用航空科技股份有限公司
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