A Genetic Algorithm-Based Method for Optimizing the Installation of Satellite Orbital Control Engines

A technology of rail-controlled engine and optimization method, applied in computing, genetic model, special data processing applications, etc., can solve the problems of large interference torque, engine interference torque is not the minimum, installation parameters are not optimal, etc., to achieve the effect of small interference torque

Active Publication Date: 2017-05-31
CHINA ACADEMY OF SPACE TECHNOLOGY
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Problems solved by technology

The influence of the center of mass of the satellite on the disturbance torque has not been considered, so there may be problems that the engine disturbance torque is not the minimum, the installation parameters are not optimal, and there may even be a problem that the disturbance torque after the adjustment of the engine angle is greater than that before the adjustment

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  • A Genetic Algorithm-Based Method for Optimizing the Installation of Satellite Orbital Control Engines
  • A Genetic Algorithm-Based Method for Optimizing the Installation of Satellite Orbital Control Engines
  • A Genetic Algorithm-Based Method for Optimizing the Installation of Satellite Orbital Control Engines

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Embodiment Construction

[0069] The present invention will be described in detail below in conjunction with the accompanying drawings and embodiments.

[0070] like figure 1 As shown in , it is a schematic diagram of the engine body coordinate system and the satellite mechanical coordinate system. figure 1 Among them, 1 is the engine, and 2 is the engine bracket.

[0071] The satellite mechanical coordinate system is defined as follows:

[0072] The origin of the coordinate system Osc—is located in the mechanical separation plane between the lower end frame of the satellite and the launch vehicle, and coincides with the center of the theoretical circle formed by the pins on the satellite interface;

[0073] OscXsc axis—consistent with the theoretical normal direction of the east plate of the satellite, and the positive direction is consistent with the normal direction outside the east plate;

[0074] OscYsc axis—consistent with the theoretical normal direction of the satellite south plate, and the ...

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Abstract

The invention provides a satellite orbit control engine installation optimization method based on a genetic algorithm. The method comprises the following steps that (1) an objective function of the engine installation optimization is determined according to the requirement of a control system on the satellite layout; (2) according to the engine geometrical parameters and the installation requirements, a constraint function of the engine installation optimization is determined; (3) an AMTLB genetic algorithm toolkit is used for carrying out engine installation parameter optimization. The satellite orbit control engine installation optimization method has the advantages that the interference moment in the orbital transfer period is further reduced, so the satellite fuel is saved, and the satellite on-orbit life is prolonged.

Description

technical field [0001] The invention relates to a method for optimizing the installation of a satellite orbit control engine, in particular to a method for optimizing the installation of a satellite orbit control engine based on a genetic algorithm. Background technique [0002] The satellite's orbit control engine is the main equipment for its orbit change strategy. The engine is installed on the engine bracket connected with the satellite center bearing cylinder. Due to the influence of factors such as thrust vector deviation and the lateral deviation between the center of mass of the satellite and the center of the mechanical coordinate system, the engine has a thrust deflection characteristic, and an interference moment to the satellite will be generated during engine ignition. In the satellite assembly stage, the overall satellite needs to put forward the installation requirements for the engine according to the heat label data of the engine development unit. The goal...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50G06N3/12
Inventor 徐春生
Owner CHINA ACADEMY OF SPACE TECHNOLOGY
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