Spacecraft orbit maneuver motor installing parameter optimizing method based on Runge-Kutta algorithm

Abstract

The invention provides a spacecraft orbit maneuver motor installing parameter optimizing method based on a Runge-Kutta algorithm. According to the method, firstly, each coordinate system is defined; then, a mathematical model between undetermined coefficients and a vector from a theoretical circular center A of a motor installing flange to a theoretical circular center C of the motor installing flange is built; a vector from the circle center A to a target point T, a vector from O<s> to the circle center A, a motor thrust vector F<EB>, an acting point position vector, a vector from the circle center A to the target point T, a vector from the circle center A to the motor thrust vector acting point P, a motor thrust vector and a vector from the motor thrust vector acting point P to the target point T are sequentially calculated; and after the undetermined coefficients are solved, the installing angle and the installing position are obtained. The method has the advantages that the optimum design mathematical model is built; and on the premise that a solution meets the constraint condition, the optimum values of motor installing parameters meet the requirements of the spacecraft orbit maneuver motor installing parameter optimization to the maximum degree.

Description

technical field [0001] The invention relates to a method for optimizing the installation parameters of a spacecraft orbit-changing engine, in particular to a method for optimizing the installation parameters of a spacecraft orbit-changing engine based on the Runge-Kutta algorithm, which belongs to the field of spacecraft overall design. Background technique [0002] The calculation result of the disturbance moment of the orbit change engine of the spacecraft is an important basis for determining the layout of the spacecraft, and it is also a basis for checking whether the design indicators of the launch and control subsystems are met. Due to the deviation of the center of mass of the spacecraft, the deviation of the thrust vector of the engine, and the deviation of the assembly, a disturbance torque will be generated during the ignition of the engine. [0003] In the final assembly stage of the spacecraft, the overall spacecraft needs to propose engine installation requireme...

AI Technical Summary

Problems solved by technology

Through calculation, it is found that if the previous method is used, sometimes the disturbance moment of the scheme design itself is relatively large, and sometimes it is even close to the upper limit of the required range

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