Aircraft disturbance control method, system and device

A technology for aircraft and control quantities, which is applied in the field of aircraft and can solve problems such as slow system response
CN112650293APending Publication Date: 2021-04-13BEIJING INSTITUTE OF TECHNOLOGYGY +1
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Patent Information

Authority / Receiving Office
CN Β· China
Current Assignee / Owner
BEIJING INSTITUTE OF TECHNOLOGYGY
Publication Date
2021-04-13

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Abstract

The invention discloses an aircraft disturbance control method, system and device. The method comprises the steps of: acquiring the current acceleration value of an aircraft; comparing the current acceleration value with an acceleration given value, and judging whether a comparison result meets a preset comparison condition or not; and under the condition that the comparison result does not meet the preset comparison condition, controlling the aircraft. According to the control method, the current acceleration value of the aircraft is acquired, and the aircraft is controlled under the condition that the current acceleration value is different from the acceleration given value. As the acceleration is direct measurement of the force, the control method has the characteristics of short period and high frequency response speed, and the response speed of the system is greatly increased.
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Description

technical field

[0001] The present invention relates to the technical field of aircraft, in particular to an aircraft disturbance control method, system and device. Background technique

[0002] The traditional aircraft control device design mostly adopts the design of attitude loop and position loop. The aircraft starts to move under the action of force, and the attitude changes. The sensor detects the attitude change, obtains the attitude difference, and outputs the corresponding control command through calculation. Overload control, the acceleration sensor directly measures the change of force, which is a direct control of force

[0003] In the above-mentioned control device, after the aircraft is subjected to an external force, a change in attitude is required to have a corresponding control output, and the system responds slowly. Contents of the invention

[0004] In view of this, the present invention provides an aircraft disturbance control method, system and devic...

Claims

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