The invention provides a rocket soft landing guidance method, and belongs to the technical field of carrier rocket control. According to the method, an engine starting instruction is obtained through a self-adaptive engine starting method, a good initial access condition is created for the landing process after the engine is started, a rocket power soft landing section online track planning equation is established according to a rocket landing flight state, and a nominal track with the strongest deviation adaptability in a subsequent flight process can be planned in a real-time online rolling manner; through a guidance tracking method, a rocket can be guided to the nominal track generated in real time, and influence of interference in rocket landing process is greatly reduced; in addition, an engine shutdown condition is determined through a small-step-length prediction shutdown method, and the landing precision of the rocket is further improved.

    本发明提供了一种火箭软着陆制导方法,属于运载火箭控制技术领域。本发明通过自适应发动机开机方法获取发动机开机指令,为发动机开机后的着陆过程创造良好初始接入条件,而且根据火箭着陆飞行状态建立的火箭动力软着陆段在线轨迹规划方程,可以实时在线滚动规划后续飞行过程偏差适应能力最强的标称轨迹;通过制导跟踪方法,可以将火箭导引向实时生成的标称轨迹,大大降低火箭着陆过程中干扰的影响;此外,本发明还通过小步长预测关机方法确定发动机关机条件,进一步提升火箭的着陆精度。


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    Rocket soft landing guidance method


    Weitere Titelangaben:

    一种火箭软着陆制导方法


    Beteiligte:
    SONG ZHENGYU (Autor:in) / WANG CONG (Autor:in) / HU HAIFENG (Autor:in) / GONG QINGHAI (Autor:in)

    Erscheinungsdatum :

    2021-04-16


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS / F42B EXPLOSIVE CHARGES, e.g. FOR BLASTING , Explosive Ladungen, z.B. für Sprengungen