The invention discloses a horizontal stage separation design method for a parallel double-waverider two-stage injection aircraft. The horizontal stage separation design method comprises the following steps: constructing a combined body structure of an orbit-stage waverider aircraft and a boosting-stage waverider aircraft; when the flight of the assembly structure reaches an interstage separation condition, the lift force borne by the two side wings of the boosting-stage waverider aircraft is unbalanced, and then the assembly structure rolls by 90 degrees in the lateral direction of the aircraft body; under the condition that the lateral rolling of the combined body structure is kept by 90 degrees, the track-level waverider aircraft is pushed by the power of the track-level waverider aircraft to perform horizontal separation action along the upper surface of the boosting-level waverider aircraft; after the orbit-level waverider aircraft is separated from the boosting-level waverider aircraft, the orbit-level waverider aircraft continues to laterally roll by 90 degrees and climbs to a target orbit, and the boosting-level waverider aircraft reversely rolls by 90 degrees to recover an initial flight state, so that horizontal-level separation of the orbit-level waverider aircraft and the boosting-level waverider aircraft is realized. According to the horizontal interstage separation method, the problems of high pressure, high heat flow and stability in the conventional separation process under the hypersonic speed condition are solved.

    本发明公开了一种并联双乘波体两级入轨飞行器水平级间分离设计方法,包括构建轨道级乘波体飞行器和助推级乘波体飞行器的组合体结构;在所述的组合体结构的飞行达到级间分离条件时,使助推级乘波体飞行器的两侧翼所受升力不平衡,进而使组合体结构绕机身侧向滚转90°;在保持组合体结构的侧向滚转90°下,轨道级乘波体飞行器在自身动力推动下沿助推级乘波体飞行器上表面进行水平分离动作;轨道级乘波体飞行器脱离助推级乘波体飞行器后,继续侧向滚转90°,并爬升至目标轨道,助推级乘波体飞行器反向滚转90°恢复初始的飞行状态,实现两者水平级间分离。本发明的水平级间分离方法避免了高超声速条件下常规分离过程中的高压、高热流、稳定性问题。


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    Titel :

    Parallel double-waverider two-stage injection aircraft horizontal stage separation design method


    Weitere Titelangaben:

    一种并联双乘波体两级入轨飞行器水平级间分离设计方法


    Beteiligte:
    WANG YUNPENG (Autor:in) / WANG YUE (Autor:in) / JIANG ZONGLIN (Autor:in)

    Erscheinungsdatum :

    2022-04-01


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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