Design And Simulation Verification Of Escape System Based On Single-capsule Manned Spaceship

Escape system is an important way to ensure astronaut's safety.The Shenzhou spacecraft would not meet the requirements of diversified manned space missions of our country in the future because of its lesser load,unreusability,module redundancy and incapability of returning from deep space.The single-capsule reusable manned spaceship is thus designed,bringing new requirements on escape system.Based on the concept of single-capsule manned spaceship,studies on the scheme selection,parameters design,simulation verification and ascent assistance of escape system are carried out,the main research achievements are as follows.New escape system scheme for single-capsule manned spaceship is put forward.A new properer tower escape system is put forward with reference to characteristics of escape system home and abroad,and its constitution is also confirmed.Relative to escape system of Shenzhou spaceship,the designed new escape system has advantages of simpler structure,better escape performance and flying stability.Research on Escape System parameters design is conducted.With study of the relationship among escape performan index,engine operating parameters,geometry and mass parameters,the overall parameters design flow of escape system is given as well as parameters design flow of each engine part and linkage segment,after that kinds of input parameters and formulas are presented,bassed on which preliminary values of the overall parameters and parameters of each part of the escape system are presented.Simulation model for the escape system is estabilished and simulation verification is implemented.(1)Based on the characteristics of single-capsule spaceship,escape modes are re-divided according to trajectory height with reference to escape modes of Shenzhou spaceship.(2)According to escape flight kinetic equations and compurational formulas of escape system parameters,the parameter compurational program and flight simulation program aredesigned and coded.(3)Typical simulation conditions are set respectively according to every escape mode.And then simulation verifications of escape performance indexes and flight stability are conducted.Finally overall parameters and parameters of each part of the escape system are presented.Ascent-assistance strategy of escape system is studied.(1)Reasonable ascentassistance scheme is put forward according to engine operating parameters and escape tower seperating time.(2)The optimization model for ascent assistance is established,and then a new optimization strategy which is based on genetic algorithm and sequential quadratic programming is proposed.(3)Quantitative analysis of two key factors,including the payload increment and the velocity increment are performed and The payload increment obtained is 246 kg while the velocity increment obtained is 45m/s.Research achievements of this thesis has some theoretical and engineering reference significance to the design of our country's escape system in the future.