A novel dual-power tandem loitering powerplant comprises a fuel system, a turbojet engine, an air intake duct, a fork form jet pipe and a solid rocket engine. The solid rocket engine is arranged at the tail end of a missile body. The turbojet engine is provided with the fork form jet pipe, then the turbojet engine is mounted at the front portion of the solid rocket engine, and lengthened segments of the fork form jet pipe come out from two sides of the missile bodies and until to ends of the missile bodies. The front portion of the turbojet engine is provided with the air intake duct. The front portion of the air intake duct is provided with the fuel system. On the premise of no changes on launch gross weight of an original flight device and aerodynamic configuration of the missile body, a miniature low-cost turbojet engine being provided with the fork form jet pipe is combined with a low-mass solid rocket engine to form a powerplant, and the air intake duct and the fuel system are symmetrically arranged at the left and right sides, the specific impulse of the powerplant can be greatly raised, problems of high-temperature protection can be overcome, the powerplant can be repeatedly ignited to be started up, the thrust is ensured to be free of influence caused ambient temperature, and the thrust can be timely adjusted and controlled.


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    Titel :

    Novel dual-power tandem loitering powerplant


    Beteiligte:
    LYU GENWEI (Autor:in) / YE HUAN (Autor:in) / WANG CHEN (Autor:in)

    Erscheinungsdatum :

    09.12.2015


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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