Optimization method of spacecraft orbital engine installation parameters 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: 2018-01-05
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 scheme design itself is relatively large, and sometimes it is even close to the upper limit of the required range

Method used

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  • Optimization method of spacecraft orbital engine installation parameters based on Runge-Kutta algorithm
  • Optimization method of spacecraft orbital engine installation parameters based on Runge-Kutta algorithm
  • Optimization method of spacecraft orbital engine installation parameters based on Runge-Kutta algorithm

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Experimental program
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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 method for optimizing the installation parameters of spacecraft orbit-changing engines based on the Runge-Kutta algorithm firstly defines each coordinate system, and then establishes the mathematical model between the undetermined coefficients and the theoretical circle center A of the engine installation flange to the theoretical circle center C of the engine installation flange, Calculate the vector from the center A to the target point T, the vector from OS to the center A, the engine thrust vector FEB and the position vector of the action point, the vector from the center A to the target point T, the vector from the center A to the engine thrust vector action point P, and the engine thrust vector Thrust vector and the vector from the engine thrust vector action point P to the target point T, after solving the undetermined coefficient, obtain the installation angle and installation position, the present invention constructs the mathematical model of optimal design, and solves the engine under the premise of satisfying the constraint conditions. The optimal value of the installation parameters satisfies the requirements of the optimization of the installation parameters of the spacecraft orbit change engine to the greatest extent.

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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Patent Type & Authority Patents(China)
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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