The invention relates to a carrier rocket launch de-mission design method, and provides a de-mission design thought which needs to be considered in a carrier rocket development process from an overall perspective according to problems encountered in a carrier rocket performance design process, namely, calculation of a carrier rocket trajectory, calculation of the carrier rocket trajectory, calculation of the carrier rocket trajectory, calculation of the carrier rocket trajectory and calculation of the carrier rocket trajectory. A task-removing design method is provided in the aspects of aerodynamic thermal environment, load environment, space thermal environment scheme design, satellite-rocket separation scheme design, measurement and control scheme design, guidance system scheme design, attitude control scheme design, flight control software design and the like, and customized design work for different launching tasks in the performance design process is reduced as much as possible. The development period is shortened, the launching cost is reduced, and the de-task requirement in the performance process of the carrier rocket is met.

    本发明涉及一种运载火箭发射去任务化设计方法,本发明根据运载火箭履约设计过程中遇到的问题入手,从总体的角度提出了在运载火箭研制过程中需考虑去任务化设计思想,即在运载火箭弹道计算,气动热环境、载荷环境、空间热环境方案设计、星箭分离方案设计、测控方案设计、制导系统方案设计、姿态控制方案设计、飞行控制软件设计等方面给出了去任务设计方法,尽可能减少履约设计过程中针对不同发射任务的定制化设计工作,缩短研制周期,降低发射成本,满足运载火箭履约过程中的去任务化需求。


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    Titel :

    De-mission design method for launch of carrier rocket


    Weitere Titelangaben:

    一种运载火箭发射去任务化设计方法


    Beteiligte:
    WANG XIAOWEI (Autor:in) / FAN WEI (Autor:in) / ZOU YANBING (Autor:in) / WANG LIAN (Autor:in) / LIU LILEI (Autor:in) / YUE XIAOFEI (Autor:in) / YIN SHIQING (Autor:in) / SUN XIAODONG (Autor:in) / ZHANG XU (Autor:in)

    Erscheinungsdatum :

    2023-07-28


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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