A Model Point Transformation Method of Spacecraft Thrust Vector Adjustment Mechanism

Abstract

A spacecraft thrust vector adjustment mechanism model point conversion method, which can quickly convert the telemetry angle of the vector adjustment mechanism into the coordinates of the center point of the thruster exit and the cosine parameter of the thrust vector direction in the spacecraft mechanical coordinate system, through multiple coordinate system conversions , transforming the basic thruster exit coordinate system into the spacecraft mechanical coordinate system after each coordinate transformation involves only one rotation of the coordinate axis, and at the same time, different transformations in different coordinate systems are proposed for the model parameter points selected for the first time method, the coordinates of the thrust action point and the cosine of the thrust direction in the ideal state of the thruster system are substituted into the coordinate transformation formula, the calculation is simple and the method flow is clear.

Description

technical field [0001] The invention relates to a model point conversion method of a spacecraft thrust vector adjustment mechanism, which belongs to the technical field of spacecraft on-orbit applications. Background technique [0002] The spacecraft is equipped with a thrust vector adjustment mechanism. By controlling the rotation angle of the rotation axis of the thrust vector adjustment mechanism, the action point and direction of the thrust of the thruster are adjusted relative to the position of the spacecraft body, so as to achieve the control of the attitude or orbit of the spacecraft. Purpose. The telemetry angle signal output by the thrust vector adjustment mechanism is defined in the coordinate system of the thrust vector adjustment mechanism body, and the telemetry angle cannot directly indicate the relative position relationship between the thrust point and direction and the spacecraft body. The engineering parameters that the spacecraft needs to use in the proc...

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Problems solved by technology

[0003] The technical problem solved by the present invention is: in the current prior art, it is difficult to directly calculate the conversion coordinates of the selected parameter model points in the spacecraft mechanical system through a single basic coordinate system thruster outlet coordinate system, in order to obtain the thrust vector Adjusting the functional relationship between the telemetry angle of the mechanism and the coordinates of the center point of the thruster exit and the cosine parameter of the thrust vector direction in the mechanical coordinate system of the spacecraft, it is convenient to realize the attitude and orbit control of the spacecraft from the ground, and a spacecraft thrust Vector adjustment mechanism model point conversion method for ground remote control of spacecraft

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