【作者】 李慧通；

【导师】 赵阳；

【作者基本信息】 哈尔滨工业大学 ， 人机与环境工程， 2012， 硕士

【摘要】 现阶段航天器分离动力学仿真研究一般针对具体的分离方案，尚没有通用的分离仿真软件，本文主要设计通用的分离仿真软件并且对分离过程中偏差进行辨识研究。本文首先进行的是两体分离动力学研究，对分离过程中比较典型的分离环节进行系统仿真建模，充分考虑分离过程中分离体的姿态变化过程，考虑总体、气动、动力等偏差因素带来的不确定性影响，模拟分离体的分离过程中各个分离阶段，能够更好地、更真实地预示分离设计的正确性，更为精确地对分离时序、分离运动过程和分离方案进行仿真验证。本文开发的动力学仿真软件能够针对多种航天运载器两体分离运动情况进行分析计算，根据使用者的选择添加不同的外载荷，具有适用范围广，灵活性强的特点。软件根据输入的初始组合体运动状态、分离体质量特性以及外部载荷变化情况，计算出分离体运动状态随时间的变化情况，得到相应的运动曲线。软件可以设定仿真时间、积分步长和输出步长以及分离特殊时间点，采用四阶龙格库塔方法或者四阶阿达姆斯预测矫正方法求解动力学常微分方程。设计的软件具有根据运动变化情况辨识出分离体所受外力随时间的变化情况的功能，同时可以验证软件动力学正向仿真的正确性。本文还针对实际试验得到的结果量比较少，可能的偏差量较多的特点，利用均匀实验方法设计偏差组合方案，进行动力学仿真，寻求偏差最优组合，供分离方案设计人员参考。本文以级间冷分离和单体整流罩分离为例进行了仿真分析，考虑气动力、分离火箭推力、主级火箭推力，空气压力等因素，经计算得到分离体的基本运动规律，并进行了相应分析。更多还原

【Abstract】 The spacecraft separation dynamic simulation is usually for a specific separationplan at this stage. Yet there is no versatility separation simulation software. In this paper,we design the general separation of simulation software and identify the deviations inthe separation process.In this paper，the dynamic simulation of two-body system is the emphasis. Thisresearch has made the mathematical models and simulated for the typical separationsystems. Take the full account of the separation of body posture changes in theseparation process; consider the deviation of the general, pneumatic, power and otherfactors which brought uncertain influence. Simulate the vehicle’s separation process. Itcan be better and more truly to indicate the correctness of the separation design, and canprecise verify the timing of the separation, the separatist movement process and eventhe separation programs.In this thesis, a method which can calculate and analyze a variety of space launchvehicle separation movement of the two-body types is proposed for the design andrealization of two-body simulation software. Add the outer loads according to the user’schoice. It has the characteristics of wide range of applications and strong flexibility.Input the motion states of the combination, the mass characteristics of the separationbodies and outer load changes. Using integral calculation a trajectory curves can be get.The function can demonstrate the correctness of the software. The simulation time, theintegration step, output step size and separation of specific points can be set. Thefourth-order Runge-Kutta method and fourth-order Adams forecast correction methodhas been used for solving first order differential equations.The software also has the function of inferring the outer load changes based on themovement curves. In actual test, the obtained results may be very little, and the possibledeviation may be large. We use the uniform experimental method to design deviationcombinations and seek the optimal combination of the deviation for the separationprogram designers.This thesis simulate and analyze the separation process of the monomer fairing andthe stages, considering the aerodynamic, the separation rocket thrust, the main stagerocket thrust and other factors. Get and analyze the movement regularity of the fairingand the rocket after been calculated.更多还原