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Spacecraft orbit maneuver motor installation parameter optimization method

An optimization method and technology of installation parameters, applied in the direction of instruments, electrical digital data processing, special data processing applications, etc., can solve the problem of large interference torque in the design of the solution

Inactive Publication Date: 2016-09-07
CHINA ACADEMY OF SPACE TECHNOLOGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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

Method used

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  • Spacecraft orbit maneuver motor installation parameter optimization method
  • Spacecraft orbit maneuver motor installation parameter optimization method
  • Spacecraft orbit maneuver motor installation parameter optimization method

Examples

Experimental program
Comparison scheme
Effect test

Embodiment

[0140] Input conditions (known conditions)

[0141] Engine heat label data (thrust vector and action point position vector), as shown in Table 1:

[0142] Table 1

[0143]

[0144] 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:

[0145] Table 2

[0146]

[0147]

[0148] The position of the engine bracket is shown in Table 3:

[0149] table 3

[0150]

[0151] Spacecraft centroid coordinate data As shown in Table 4:

[0152] Table 4

[0153]

[0154]

[0155] (2) Specific solution:

[0156] (a) The solution program was written in Matlab software, including the main program and post-processing program. The main program includes parameter input subroutines and iteration subroutines. In order to improve the solution accuracy, the program provides four optimization algorithms: simulated annealing algorithm, genetic algorithm, m...

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Abstract

The present invention provides a spacecraft orbit maneuver motor installation parameter optimization method. The method comprises the steps of: firstly, defining each coordinate system, and establishing a relation among a motor thrust vector, an acting point position vector and an undetermined coefficient; then calculating a relation between a disturbance torque value during each ignition; and with an optimization goal of making a maximum and a minimum of a disturbance torque component during each ignition equal in numerical value but opposite in sign, solving the undetermined coefficient, so as to obtain an installation angle of a spacecraft orbit maneuver motor and an installation position of a motor nozzle. According to the method provided by the present invention, an optimally designed mathematical equation is constructed, and the demand for optimization of the installation parameter of the spacecraft orbit maneuver motor is satisfied to the largest extent.

Description

technical field [0001] The invention relates to a method for optimizing installation parameters of an orbit-changing engine of a spacecraft, which belongs to the field of overall design of spacecraft. 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 requirements based on the thermal data provided by the engine development unit. Generally, the smaller the disturbance moment during the track cha...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/17
Inventor 郑建东林骁雄
Owner CHINA ACADEMY OF SPACE TECHNOLOGY
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