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Method for adjusting transverse mass center of parallel storage tank satellite

An adjustment method and center of mass technology, applied to artificial satellites, space vehicle propulsion system devices, aerospace equipment, etc., can solve the problems of low load-bearing efficiency and adjustment capacity, and achieve weight saving, load-bearing efficiency, and load-bearing capacity Effect

Active Publication Date: 2021-07-23
CHINA ACADEMY OF SPACE TECHNOLOGY
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Problems solved by technology

[0007] The technical problem solved by the present invention is: in the current prior art, the existing method of determining the center of mass through the adjustment of the counterweight is prone to low load-carrying efficiency, and the method of using high-precision control of the center of mass of the satellite does not use the propellant of the parallel storage tank to add The ability to adjust the fluence to the lateral center of mass of the whole satellite is a problem, and a method for adjusting the lateral center of mass of satellites with tanks arranged in parallel is proposed

Method used

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  • Method for adjusting transverse mass center of parallel storage tank satellite
  • Method for adjusting transverse mass center of parallel storage tank satellite
  • Method for adjusting transverse mass center of parallel storage tank satellite

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Embodiment Construction

[0041] A method for adjusting the lateral center of mass of a parallel-arranged storage tank satellite, by designing the propellant weights in different storage tanks of the parallel-connected storage tank satellite, while completing the propellant filling of the spacecraft, there is no need to add additional counterweights to realize the spacecraft The adjustment of the horizontal center of mass of the entire star in the launch state, the specific steps are as follows:

[0042] (1) Obtain the installation position coordinates of each propellant tank, the propellant tank includes the first oxygen tank, the second oxygen tank, the first fuel tank, and the second fuel tank, and the installation position coordinates of each propellant tank are Coordinates of the center of mass of the propellant tank;

[0043] Among them, according to the satellite configuration layout design, the horizontal coordinates of the center points of the four propellant tanks are obtained. The horizonta...

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Abstract

According to a method for adjusting the transverse mass center of a parallel storage tank satellite, by designing the filling weights of propellants in different storage tanks of the parallel storage tank satellite, the transverse mass center of the whole satellite in the launching state of a spacecraft is adjusted without additionally adding a balancing weight while filling of the propellants of the spacecraft is completed, by means of the filling weight difference of the same propellant storage tank, the whole-satellite zero-counterweight transverse mass center adjusting strategy is achieved, the load bearing capacity of the spacecraft can be effectively improved, and the method has high engineering application value and prospects.

Description

technical field [0001] The invention relates to a method for adjusting the lateral center of mass of a satellite with storage tanks arranged in parallel, and belongs to the field of center of mass adjustment of spacecraft. Background technique [0002] The center of mass is an important mass characteristic of a spacecraft, which will directly affect the launch and on-orbit performance of the spacecraft, and even the success or failure of the entire mission. On the one hand, in order to reduce the interference moment of the rocket launch stage and ensure the success of the launch, the launch vehicle will put forward clear requirements on the lateral center of mass of the spacecraft during the design stage; on the other hand, for the spacecraft that needs orbit change and position maintenance, The lateral center of mass directly affects the attitude disturbance moment introduced during orbit control, and then affects the control performance and propellant consumption of the sp...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/40B64G1/10B64F5/60
CPCB64G1/402B64G1/10B64F5/60
Inventor 刘敏裴胜伟吕红剑孙恒超侯凤龙
Owner CHINA ACADEMY OF SPACE TECHNOLOGY
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