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Layout design method based on satellite launch weight and zero counterweight

A technology for layout design and satellite launch, applied in design optimization/simulation, special data processing applications, etc., can solve problems such as poor predictability of counterweight weight distribution, counterweight design process and time lag, and single form of counterweight installation. Achieve the effect of saving satellite launch weight, more margin, and saving satellite fuel

Active Publication Date: 2021-04-13
CHINA ACADEMY OF SPACE TECHNOLOGY
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  • Application Information

AI Technical Summary

Problems solved by technology

[0020] (1) Counterweight design lags behind in process and time;
[0021] (2) In view of the relatively single installation form of the counterweight, the effect of the counterweight is limited;
[0022] (3) The weight distribution of the counterweight is poorly predictable;
[0023] (4) Occupying the entire star and launching a lot of weight, it will eventually become an invalid mass in orbit

Method used

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  • Layout design method based on satellite launch weight and zero counterweight
  • Layout design method based on satellite launch weight and zero counterweight
  • Layout design method based on satellite launch weight and zero counterweight

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Embodiment Construction

[0058] The present invention will be further described below in conjunction with the accompanying drawings.

[0059] Such as Figure 13 As shown, a layout design method based on satellite launch weight and zero counterweight includes the following steps:

[0060] (1) Establish the satellite body coordinate system, and decompose the structure of the satellite into different equipment installation areas according to the directions of the X, Y, and Z axes of the satellite body coordinate system;

[0061] For example: in this embodiment, the origin O of the established satellite body coordinate system OXYZ is located at the center of the docking surface of the satellite and the rocket, the Z axis is in the vertical direction, the XOY plane is located in the docking surface of the satellite and the rocket, and the X axis and the Y axis Satisfy the right-hand rule with the Z axis;

[0062] According to the satellite configuration, determine the installation location of satellite i...

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Abstract

When the satellite layout design work is carried out, the counterweight design is usually considered as the margin of the satellite, so the distribution of the counterweight is implied in the satellite layout work. The method of the invention takes the zero counterweight of the satellite as the design goal, and the layout work carried out by this method can optimize the scheme and reduce the weight distribution of the counterweight. This method analyzes and sorts out the layout work, abstracts the work elements to realize the zero-weight layout, and combines the influence degree of these elements to clarify the basic scheme to realize the zero-weight layout. And the work flow of the zero counterweight layout method is given, which can save design cost, improve design efficiency, and reduce the uncertainty of development iteration cycle and scheme.

Description

technical field [0001] The invention relates to a layout design method. Background technique [0002] At present, domestic communication satellite platforms are mainly in GEO orbit, and the weight of the whole satellite launched by the satellite is about 5100Kg, and the dry weight is about 2000kg. The DFH-4 platform adopts a box structure with a central bearing tube and a wall plate. The satellite body is divided into three compartments: communication compartment, propulsion compartment, and service compartment. The propulsion cabin is composed of the central load-bearing tube, the middle plate, the back floor, and the partition of the propulsion cabin; the communication cabin is composed of the opposite floor, the south panel of the communication cabin, the north panel of the communication cabin, and the north-south partition of the communication cabin; the service cabin is composed of the south panel of the service cabin. It is composed of the north deck of the service mo...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/20
CPCG06F30/20
Inventor 彭真杨凌轩梅杰邹晨
Owner CHINA ACADEMY OF SPACE TECHNOLOGY
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