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.
CN112379680AActive Publication Date: 2021-02-19CHINA ACAD OF LAUNCH VEHICLE TECH
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
CHINA ACAD OF LAUNCH VEHICLE TECH
Publication Date
2021-02-19

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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.
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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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