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Parallel storage tank non-isobaric air cushion propellant filling quantity and satellite mass center determination method

A technology for determining methods and propellants, applied in special data processing applications, geometric CAD, aerospace equipment, etc., to reduce calculation time, improve calculation accuracy, and facilitate engineering applications

Pending Publication Date: 2022-02-15
CHINA ACADEMY OF SPACE TECHNOLOGY
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  • Abstract
  • Description
  • Claims
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Problems solved by technology

[0008] The adjustment of the center of mass of the traditional single propellant filled by a single tank can only be realized by adding and changing the position of the counterweight

Method used

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  • Parallel storage tank non-isobaric air cushion propellant filling quantity and satellite mass center determination method
  • Parallel storage tank non-isobaric air cushion propellant filling quantity and satellite mass center determination method
  • Parallel storage tank non-isobaric air cushion propellant filling quantity and satellite mass center determination method

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Embodiment Construction

[0080] The present invention will be further elaborated below in conjunction with embodiment.

[0081] The filling quantity of non-isobaric air cushion propellant in parallel storage tanks and the determination method of satellite center of mass, such as Figure 1-3 as shown,

[0082] attached figure 1 It is a schematic diagram of parallel storage tank satellite configuration.

[0083] Parallel storage tank satellites generally include 4 storage tanks, including 2 oxygen tanks and 2 fuel tanks, which are oxygen tank a MON-a, oxygen tank b MON-b, fuel tank a MMH-a, fuel tank b MMH- b. The engine Engine is arranged on the base plate of the satellite.

[0084] attached figure 2 It is the schematic diagram of the parallel tank chemical propulsion system, and the name of each single machine is shown in the legend in the figure.

[0085] attached image 3 is the relationship between satellite centroids.

[0086] No counterweight is added: the barycenter of the dry star is p...

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Abstract

The invention relates to a parallel storage tank non-isobaric air cushion propellant filling quantity and satellite mass center determination method. The method comprises the following steps: obtaining input parameters through experiments, testing and simulation; carrying out balanced filling to obtain the propellant filling mass, the propellant mass center and the satellite mass center coordinates of the launching state of each storage tank during balanced filling; calculating the mass center adjusting capacity during unbalanced filling, and sequentially obtaining the propellant filling mass, the propellant mass center and the satellite mass center coordinates of the launching state of each storage tank when the storage tank is filled according to the maximum filling mass; calculating an intersection point of an engine thrust vector and an XY plane at the center of mass of the satellite; and carrying out propellant and helium filling and subsequent on-orbit operation based on the determined propellant filling amount, the air cushion pressure and the satellite mass center. According to the method, the satellite mass center relation graph is introduced, the position relation between the satellite mass center and the constraint condition at different moments can be vividly displayed, and engineering application can be understood and rapidly guided.

Description

technical field [0001] The invention relates to a non-isobaric air cushion propellant filling amount of a parallel storage tank and a method for determining the center of mass of a satellite, and belongs to the general technical field of missile systems. Background technique [0002] The amount of propellant and the design of the center of mass of the satellite are important tasks after all the satellite assembly work is completed and before the satellite is launched. The weight ratio of liquid propellant is relatively high when the satellite is launched, for example, the weight ratio of propellant for a satellite in geosynchronous orbit is about 40%. Therefore, the propellant filling will also significantly affect the mass characteristics of the satellite in the launch state (such as weight, center of mass position, etc.), so the calculation of the satellite propellant filling amount and the determination of the satellite center of mass position are carried out jointly. Di...

Claims

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Application Information

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IPC IPC(8): G06F30/20G06F30/15B64G5/00
CPCG06F30/20G06F30/15B64G5/00
Inventor 孙恒超李峰郝燕艳宋涛裴胜伟刘敏侯凤龙范为黄华尹文娟
Owner CHINA ACADEMY OF SPACE TECHNOLOGY
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