A Model Point Transformation Method of Spacecraft Thrust Vector Adjustment Mechanism

Abstract

The invention relates to a spacecraft thrust vector adjusting mechanism model point conversion method. The telemetering angle of a vector adjusting mechanism can be quickly converted into thruster outlet center point coordinates and a thrust vector direction cosine parameter under a spacecraft mechanical coordinate system, and through multiple times of coordinate system conversion, finally the fundamental thruster outlet coordinate system is converted into the spacecraft mechanical coordinate system, wherein only one-time rotation of a coordinate axis is involved in each-time coordinate conversion; and meanwhile, for the model parameter points selected for the first time, different conversion methods in different coordinate systems are proposed, the thrust action point coordinates and thethrust direction cosine in a thruster body system in an ideal state are substituted into a coordinate conversion formula, the calculation is simple and convenient, and the method is clear in procedures.

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...

AI Technical Summary

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 ang

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