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Simulation analysis method for pressure separation of spacecraft

A space vehicle, simulation analysis technology, applied in the field of spacecraft simulation, can solve problems such as inconvenient engineering application, oversimplification of the model, and inability to provide quantitative conclusions.

Active Publication Date: 2018-08-10
BEIJING SPACE TECH RES & TEST CENT
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Problems solved by technology

[0004] A more accurate simulation modeling method is proposed to solve the shortcomings of the original method model that is too simplified, cannot provide effective quantitative conclusions, and is not convenient for engineering applications

Method used

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  • Simulation analysis method for pressure separation of spacecraft
  • Simulation analysis method for pressure separation of spacecraft
  • Simulation analysis method for pressure separation of spacecraft

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Embodiment Construction

[0020] First, establish a theoretical model to provide input and boundary conditions for flow field analysis and simulation calculations;

[0021] Secondly, the CFD method is used to calculate the flow field in the inner area of ​​the docking channel, and the DSMC method is used to solve the flow field in the outer area.

[0022] Finally, the internal and external disturbance forces are comprehensively calculated using the flow field analysis results.

[0023] Such as figure 1 , assuming that the internal gas parameters of the docking mechanism are evenly distributed, the pressure is p1, the density is ρ1, and the temperature is T1 (both are functions of time t); the pressure at the outlet AB of the sealing ring of the docking mechanism is pe, the density is ρe, and the temperature is Te, The outlet area is Ae; the pressure at the outlet CD on the outer edge of the aircraft is p2, the density is ρ2, the temperature is T2, and the outlet area is A2. The purpose of establishin...

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Abstract

The invention relates to a simulation analysis method for pressure separation of a spacecraft, and belongs to the technical field of spacecraft simulation. The simulation analysis method comprises thefollowing steps: decomposing a pressure compartment into an internal continuous flow field and an external rarefied flow field for computation respectively; building a theoretical model to give the boundary condition of the entrance / exit of a computation domain; computing an internal region flow field by a CFD (Computational Fluid Dynamics) method, and solving an external region flow field by a DSMC (Direct simulation of Monte Carlo) method; finally determining the disturbing force of the pressure separation on two spacecrafts according to a flow field analysis result. The computed flow fieldcan be divided into two parts: a flow field inside the pressure compartment (continuous flow) and a flow field outside the spacecraft (rarefied flow). The basic governing equation of the continuous flow field in the pressure compartment is a Navier-Stokes equation, which is computed by the CFD method; the basic governing equation of the rarefied flow field outside the spacecraft is a Boltzmann equation, which is simulated by the DSMC method.

Description

technical field [0001] The invention relates to a simulation analysis method for pressure separation of a space vehicle, which belongs to the technical field of space vehicle simulation. Background technique [0002] The current interference analysis method for the pressure separation of the spacecraft uses the ideal gas equation to describe the diffusion of gas into the vacuum, and then determine the reaction force and moment generated during the pressure separation. This method is simple to operate and has a small amount of calculation. However, due to the complex shape and structure of the spacecraft and many working conditions of pressure separation, it is difficult to obtain accurate simulation results using the above method and can only be used for qualitative analysis. Contents of the invention [0003] 1. Technical problems to be solved [0004] A more accurate simulation modeling method is proposed to solve the shortcomings of the original method that the model i...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/20G06F2119/06Y02T90/00
Inventor 黄震杨宏马晓兵石泳张永邵立民高旭雷剑宇苏令李蒙彭华康霍佳婧
Owner BEIJING SPACE TECH RES & TEST CENT
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