The invention discloses a speed constraint separation method based on a solid rocket engine boosting aircraft. The method comprises the following steps: S1, determining a first maximum speed threshold value Vmax1, a second maximum speed threshold value Vmax2 and latest separation time Tmax; s2, the full-missile flight speed Vt0 at the end of work of the engine is compared with a first maximum speed threshold Vmax1, when Vt0 is smaller than Vmax1, the aircraft is separated in time when work of the engine is finished, and when Vt0 is larger than or equal to Vmax1, the step S3 is executed; s3, delaying separation of the aircraft after the engine finishes working; the specific method for delayed separation comprises the steps that if the full-missile flight time is smaller than Tmax, the full-missile flight speed Vt at the current moment is compared with Vmax2, when Vt is smaller than Vmax2, the aircraft is separated, and when Vt is larger than or equal to Vmax2, full-missile flight continues; and if the flight time of the whole missile is greater than or equal to Tmax, separating the aircraft. The separation time can be judged according to the real-time flight speed, the proper speed is provided after the main stage is separated, and the main stage flight control requirement and the speed requirement after separation are guaranteed.

    本发明公开了一种基于固体火箭发动机助推飞行器的速度约束分离方法,包括S1确定第一最大速度阈值Vmax1、第二最大速度阈值Vmax2和最晚分离时间Tmax;S2将发动机工作结束时的全弹飞行速度Vt0与第一最大速度阈值Vmax1比较,当Vt0<Vmax1,使飞行器在发动机工作结束时及时分离,当Vt0≥Vmax1,进入步骤S3;S3使飞行器在发动机工作结束后延迟分离;延迟分离的具体方法为:若全弹飞行时间<Tmax,则将当前时刻的全弹飞行速度Vt与Vmax2比较,当Vt<Vmax2时,使飞行器分离,当Vt≥Vmax2时,继续全弹飞行;若全弹飞行时间≥Tmax,使飞行器分离。本发明可根据实时飞行速度判断分离时间,为主级分离后提供适合速度,保证了分离后主级飞行控制要求和速度要求。


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    Titel :

    Speed constraint separation method based on solid rocket engine boosted aircraft


    Weitere Titelangaben:

    基于固体火箭发动机助推飞行器的速度约束分离方法


    Beteiligte:
    LIU BAONING (Autor:in) / KONG ZHE (Autor:in) / CHEN XIAOYU (Autor:in) / LONG JING (Autor:in) / LIN RUI (Autor:in) / HU SIAO (Autor:in) / ZHANG ZHICHAO (Autor:in) / LI YONGBO (Autor:in) / LIAO YIQI (Autor:in) / WANG YONGPING (Autor:in)

    Erscheinungsdatum :

    2023-06-27


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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