基于蒙特卡罗方法的固体火箭姿态控制系统设计

在固体火箭姿态控制系统设计过程中，为保证设计结果的可靠性，需要针对发动机性能、全箭质量及气动参数等进行拉偏仿真分析，各项偏差的大小及使用方法直接影响对固体火箭控制能力的需求。传统固体火箭姿态控制系统设计时，一般针对各项偏差进行极限拉偏组合仿真，导致设计结果较为保守。针对总体各项偏差量，建立概率模型，采用蒙特卡罗方法进行控制力分析。数学仿真结果表明，相比传统设计方法，在保证系统具有一定的可靠度情况下，大幅降低了对姿态控制系统的需求，优化了系统方案。

Design of Solid-fuel Rocket Attitude Control System Based on Monte Carlo Method

In the design process of solid-fuel rocket attitude control system, it is necessary to simulate based on population deviations of engine performance, whole solid-fuel rocket mass and aerodynamic parameter in order to assure the reliability of design results, because the using method of deviation factors are accounted for the demand of solid-fuel rocket control. The extreme value of population deviations are taken in the traditional design method, but it leads to more conservative design results. The probability models of population deviations are established, and then Monte Carlo methods are introduced to analysis the controlling force. The simulated results show that, compared to the traditional design method, the probability design method reduces the demand of solid-fuel rocket attitude control system and optimizes the system design scheme obviously.