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Aircraft attitude angle control method, control device and storage medium

A control method and aircraft technology, applied in the field of aerospace, can solve problems such as the orientation adjustment of the attitude of the rocket body, etc.

Active Publication Date: 2021-02-19
CHINA ACAD OF LAUNCH VEHICLE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The present invention proposes an aircraft attitude angle control method, a control device and a storage medium, aiming at solving the problem of adjusting the orientation of the arrow body attitude that has not occurred in the prior art. design method issues

Method used

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  • Aircraft attitude angle control method, control device and storage medium
  • Aircraft attitude angle control method, control device and storage medium

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Embodiment 1

[0026] figure 1 A flow chart of the steps of a method for controlling the attitude angle of an aircraft according to an embodiment of the present application is shown in FIG.

[0027] Such as figure 1 As shown, the aircraft attitude angle control method of the present embodiment specifically includes the following steps:

[0028] S101. Calculate the geocentric projection of the aircraft-target vector according to the geocentric coordinates of the target point and the geocentric coordinates of the aircraft.

[0029] S102. Obtain the launch inertial system projection of the aircraft-target vector according to the geocentric system projection of the aircraft-target vector.

[0030] S103, perform normalization according to the launch inertial system projection of the aircraft-target vector to obtain the aircraft attitude angle command input parameters.

[0031] S104. Obtain an aircraft attitude angle command according to the aircraft attitude angle command input parameter.

[...

Embodiment 2

[0087] figure 2 A schematic structural diagram of an aircraft attitude angle control device according to an embodiment of the present application is shown.

[0088] Such as figure 2 As shown, the aircraft attitude angle control device provided in this embodiment specifically includes:

[0089] The earth-centered system projection module 10 of aircraft-target vector is used for calculating the earth-centered system projection of aircraft-target vector according to the earth-centered system coordinates of target point and the earth-centered system coordinates of aircraft;

[0090] The launch inertial system projection module 20 of aircraft-target vector is used to obtain the launch inertial system projection of aircraft-target vector according to the geocentric projection of said aircraft-target vector;

[0091] Aircraft attitude angle instruction input parameter module 30, for carrying out normalization according to the launch inertial system projection of described aircraf...

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Abstract

The embodiment of the invention provides an aircraft attitude angle control method and device and a storage medium. The aircraft attitude angle control method comprises the following steps of calculating geocentric system projection of an aircraft-target vector according to geocentric system coordinates of a target point and geocentric system coordinates of an aircraft, according to the geocentricsystem projection of the aircraft-target vector, obtaining an emission inertial system projection of the aircraft-target vector, normalizing according to the launch inertial system projection of theaircraft-target vector to obtain aircraft attitude angle instruction input parameters, and finally obtaining an aircraft attitude angle instruction to control the aircraft attitude angle according tothe aircraft attitude angle instruction input parameter. The aircraft attitude angle constraint control is realized when a certain axis or any axis of an aircraft X, Y and Z points to a ground fixed position, and the problem that the certain axis of the aircraft is oriented due to aircraft attitude adjustment does not occur at present is solved.

Description

technical field [0001] The present application belongs to the field of aerospace technology, and in particular, relates to an aircraft attitude angle control method, a control device and a storage medium. Background technique [0002] In the guidance design of solid launch vehicles, the solid launch vehicle needs to meet specific attitude angle constraints at the moment of satellite release, so that a certain axis or any axis of the rocket body points to a fixed latitude, longitude, and elevation position on the ground. At present, there is no design method for adjusting the attitude of the rocket body so that a certain axis of the rocket body is oriented in the guidance of solid rockets, and there is no related theoretical research work. [0003] Therefore, there is an urgent need for a method for controlling the attitude angle of the aircraft when a certain axis of the aircraft is directed to a fixed position on the ground. Contents of the invention [0004] The present...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/08
CPCG05D1/0833
Inventor 吕瑞赵长见葛云鹏梁卓宋志国涂海峰严大卫陈喆姜春旺杜肖谭清科胡骁李浩张亚琳潘彦鹏王凯旋李迎博陈旭东薛晨琛杨立杰谭黎立李烨张雪婷丁禹赵楠陈铁凝郝仁杰丘岳诗孟文霞
Owner CHINA ACAD OF LAUNCH VEHICLE TECH
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