Method for determining mounting parameters of orbit control engines of satellites

Abstract

The invention discloses a method for determining mounting parameters of orbit control engines of satellites. The method includes determining a mounting position of each engine by the aid of included angles alpha<E>, beta <E> and gamma <E> among a normal line O<m>X<m> of an accurate measurement mirror of the engine and an axis O<sc>X<sc>, an axis O<sc>Y<sc> and an axis O<sc>Z<sc> of a mechanical coordinate system of the corresponding satellite and coordinates x<E>, y<E> and z<E> of the center O<m> of the accurate measurement mirror of the engine on the axis O<sc>X<sc>, the axis O<sc>Y<sc> and the axis O<sc>Z<sc> of the mechanical coordinate system of the satellite. The method has the advantages that change conditions of mass centers of the satellites and thrust vectoring thermal marking results of the engines are comprehensively considered, so that the mounting parameters of the engines can be optimally determined, disturbance torque generated in orbital transfer periods of the satellites can be reduced, satellite propellants can be saved, and the in-orbit lives of the satellites can be prolonged; thrust of each engine points to the average mass center of the corresponding satellite in the corresponding orbit transfer period, so that counterweights for the satellites can be reduced or can be omitted, and the effective load weight of each satellite can be increased.

Description

technical field [0001] The invention belongs to the field of overall design of satellites, and relates to an optimal design method of installation parameters of a satellite orbit control engine. Background technique [0002] The satellite orbit control engine is used to provide thrust for the satellite transfer and orbit change after the satellite and rocket are separated. Due to the deviation between the thrust vector of the engine and the center of mass of the satellite, there will be a disturbance torque during the ignition of the engine, and the disturbance torque will directly affect the attitude control of the satellite and the consumption of propellant for attitude control. [0003] At present, the installation of domestic satellite orbit control engines has undergone in-orbit verification of several Dongsan and Dongsi platform satellites, and the method is relatively mature. This current engine installation method only considers the thrust direction factor in the en...

AI Technical Summary

Problems solved by technology

This will lead to the fact that after the satellite orbit control engine is installed, its installation orientation is not optimal, and when the disturbance torque is large, additional counterweight is required to make the control disturbance torque meet the requirements

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