The invention relates to the field of rocket recovery, in particular to an ignition reverse thrust deceleration landing system for a recoverable rocket, which designs a reverse thrust engine module, defines a propellant and a plurality of parameters, perfects a fuel supply system, and covers solutions to storage, vaporization, collapse, vortexes and other problems. According to the accurate control algorithm, the trajectory and speed of a rocket are predicted through multi-sensor data, a reverse thrust engine is dynamically adjusted through complex steps including target setting, control strategy, ignition, thrust adjustment and the like, and real-time feedback and landing stage control are further achieved. The integrated sensor system comprises various types of sensors and is responsible for collecting and processing data and transmitting the data to the control system. System integration involves hardware, software and debugging, and test plans include ground, simulation and flight testing. The safety and redundancy design comprises a redundancy control path, a fault detection mechanism and countermeasures when an engine and a sensor have faults. According to the scheme, the rocket recovery accuracy and safety can be improved, and the cost is reduced.

    本发明涉及火箭回收领域,特别涉及可回收火箭用点火反推力减速着陆系统,设计了反推力发动机模块,明确推进剂及诸多参数,完善燃料供应系统,涵盖存储、汽化、塌陷、漩涡等问题的解决措施。精确控制算法利用多传感器数据预测火箭轨迹和速度,通过复杂步骤动态调整反推力发动机,包括目标设定、控制策略、点火和推力调整等,还有实时反馈和着陆阶段控制。集成传感器系统包含多种类型传感器,负责采集和处理数据传输给控制系统。系统整合涉及硬件、软件和调试,测试计划包括地面、模拟和飞行测试。安全性与冗余设计包括冗余控制路径和故障检测机制,以及发动机和传感器故障时的应对措施。此方案可提高火箭回收精确性和安全性,降低成本。


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    Title :

    Ignition reverse thrust deceleration landing system for recoverable rocket


    Additional title:

    可回收火箭用点火反推力减速着陆系统


    Contributors:
    CHEN KERU (author)

    Publication date :

    2024-12-27


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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