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Aircraft attitude control method, aircraft attitude control system and aircraft

An attitude control and aircraft technology, applied in the field of aircraft, can solve the problem that the anti-shock requirement and the minimum working time requirement cannot be fully considered.

Pending Publication Date: 2022-04-12
宁波天擎航天科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The embodiment of the present invention provides an aircraft attitude control method, which aims to solve the problem that the anti-shock requirement and the minimum working time requirement cannot be fully balanced

Method used

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  • Aircraft attitude control method, aircraft attitude control system and aircraft
  • Aircraft attitude control method, aircraft attitude control system and aircraft
  • Aircraft attitude control method, aircraft attitude control system and aircraft

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0089] In this embodiment, an aircraft attitude control method is provided, such as figure 1 As shown, the method includes:

[0090] Step 101, sampling switch control quantities corresponding to multiple target channels of the aircraft at preset intervals, wherein the switch control quantities are determined based on the angle deviation correction value of the target channel of the aircraft;

[0091] Step 102, obtaining the control quantity correction strategy of each target channel respectively, wherein the control quantity correction strategy includes the shortest working time strategy and the anti-shock strategy;

[0092] Step 103, according to the control amount correction strategy, calculate the control value of each target channel at the current sampling time through the target switch control amount at the current sampling time and multiple historical correction values ​​of the switch control amount before the current sampling time Quantity correction value;

[0093] S...

example 1

[0139] Set the pitch, yaw and roll channel initial switch control value p y0 ,p z0 and p x0 ,See image 3 , the output value p calculated by the minimum working time of the attitude control engine and the coupling design method of the anti-shock strategy y ,p z ,p x See Figure 4 .

example 2

[0141] Set the pitch, yaw and roll channel initial switch control value p y0 ,p z0 and p x0 ,See Figure 5 , the output value p calculated by the minimum working time of the attitude control engine and the coupling design method of the anti-shock strategy y ,p z ,p x See Image 6 .

[0142] According to the minimum working time of the attitude control engine and the anti-shock coupling design algorithm input p in verification example 1 and verification example 2 y0 ,p z0 ,p x0 and calculate the output p y ,p z ,p x As can be seen from the analysis results, based on the minimum working time of the attitude control engine proposed by the present invention and the anti-shock coupling design method, the p y ,p z ,p x Fully meet the minimum working time requirements of the attitude control engine and anti-shock requirements, and the algorithm logic is easy to implement without algebraic loops, and has the conditions for engineering applications.

[0143] Further, the...

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Abstract

The invention is suitable for the technical field of aircrafts, and provides an aircraft attitude control method, an aircraft attitude control system and an aircraft, according to a preset interval, switching control quantities corresponding to a plurality of target channels of the aircraft are sampled, and the switching control quantities are determined based on target channel angle deviation correction values of the aircraft; a control quantity correction strategy of each target channel is obtained, and the control quantity correction strategy comprises a shortest working time strategy and a water attack prevention strategy; according to the control quantity correction strategy, a control quantity correction value of each target channel at the current sampling moment is calculated through a plurality of historical correction values of a target switch control quantity at the current sampling moment and a switch control quantity before the current sampling moment; and respectively controlling the attitude control engine of each target channel by using the control quantity correction value. And the formation of a more complete shortest working time and water-attack-resistant requirement realization scheme is facilitated.

Description

technical field [0001] The invention belongs to the technical field of aircraft, and in particular relates to an aircraft attitude control method, an aircraft attitude control system and an aircraft. Background technique [0002] The liquid attitude control engine is often used as the actuator to control the pitch, yaw and roll channel attitude of the aircraft from the ground take-off to the space flight. When the high-thrust attitude control engine is working, there are usually restrictions on the minimum working time of the attitude control engine for a single start, so as to avoid the thrust being in an unstable working state when the turn-on command time is too short. At the same time, when multiple high-thrust attitude control engines work at the same time to provide positive and negative control torques for each channel respectively, after a certain attitude control engine is turned off, within a certain time interval, this road or any other attitude control engine is ...

Claims

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Application Information

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IPC IPC(8): G05D1/08
Inventor 鲍晓强郭一江陈明欣张骞李之强杨文俊冯小强周军丁攀何苗位陈
Owner 宁波天擎航天科技有限公司
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