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

An optimization method and a technology of installation parameters, which are applied in the directions of instruments, calculations, electrical digital data processing, etc., can solve the problem of large interference torque in the design of the solution

Active Publication Date: 2015-11-18
CHINA ACADEMY OF SPACE TECHNOLOGY
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Problems solved by technology

Through calculation, it is found that if the previous method is used, sometimes the disturbance moment of the s

Method used

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

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Experimental program
Comparison scheme
Effect test

Embodiment

[0171] Input conditions (known conditions)

[0172] Engine heat label data (thrust vector and action point position vector), as shown in Table 1:

[0173] Table 1

[0174]

[0175]

[0176] The mechanical dimensions of the engine (the distance from the theoretical center of the engine nozzle to the theoretical center of the mounting flange) are shown in Table 2:

[0177] Table 2

[0178]

[0179] The position of the engine bracket is shown in Table 3:

[0180] table 3

[0181]

[0182]

[0183] Spacecraft centroid coordinate data As shown in Table 4:

[0184] Table 4

[0185]

[0186] (2) According to the requirements of the overall design of the spacecraft, the objective function of the optimal design of the engine installation parameters is constructed. The vector of the engine thrust pointing to the target point T is shown in Table 5:

[0187] table 5

[0188]

[0189] (3) Specific solution:

[0190] (a) According to step (2), calculate the v...

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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...

Claims

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Application Information

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IPC IPC(8): G06F19/00
Inventor 郑建东牟永强李峰李朝阳裴林徐春生
Owner CHINA ACADEMY OF SPACE TECHNOLOGY
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