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针对探月三期返回器回收的初始条件、约束条件以及返回器的相关特点,提出了一种开伞载荷非均衡的两级降落伞减速系统方案,解决了探月三期返回器降落伞开伞载荷、舱伞系统的稳定性、重量要求以及弹盖拉伞可靠性等多因素的约束,实现了各方面较好的匹配性和降落伞系统的轻量化设计.同时针对轻质、不规则气动外形伞舱盖的特点,对弹盖拉伞的开伞方式进行了设计,确保了弹盖拉伞工作的可靠性.介绍了降落伞系统的主要可靠性分析验证情况.经过地面试验、仿真试验、空投试验和飞行试验的验证,表明探月三期返回器降落伞系统工作性能稳定、可靠,能够确保返回器的安全着陆.
According to the initial condition, restraint condition and the characteristics of the reflector, the paper proposes a two-stage parachute deceleration system with unbalanced loading, which solves the problem of the parachute parachute load , The stability of the bayonet system, the weight requirements and the reliability of the spanning umbrella, the various aspects of the system are well matched and the weight of the parachute system is reduced.At the same time, the lightweight and irregular aerodynamic profile umbrella The design of hatch cover and the way of opening the umbrella cover to ensure the reliability of the flap pull umbrella work.The main reliability analysis and verification of the parachute system is introduced.After the ground test, simulation test, airdrop test And flight test verification, indicating that the moon trip three parachute parachute system performance is stable and reliable, to ensure the safe landing of the reflector.