ROCKET NOZZLE THROAT INSERT
    1.
    发明申请

    公开(公告)号:WO2019118259A1

    公开(公告)日:2019-06-20

    申请号:PCT/US2018/064165

    申请日:2018-12-06

    Abstract: A rocket throat insert (112) including an annular body (120) having a radially inner annular wall portion (122) and a radially outer annular portion (124). The inner wall portion has a contoured radially inner surface (128) defining a nozzle throat (130). The outer portion includes an annular buttressing structure (132) supporting the inner wall portion and defining one or more insulation gaps (134) arranged annularly around the inner wall portion. The insulation gaps restrict the radial flow of heat through the annular body.

    RESIN TRANSFER MOLDED ROCKET MOTOR NOZZLE WITH ADAPTIVE GEOMETRY

    公开(公告)号:WO2020055625A1

    公开(公告)日:2020-03-19

    申请号:PCT/US2019/049311

    申请日:2019-09-03

    Abstract: A rocket motor has a nozzle that is reconfigurable by erosion or ablation of the material around the throat of the nozzle. The nozzle throat has layers of materials with different erosion characteristics, with the erosion occurring so as to achieve the desired nozzle characteristics (configurations) during different parts of the fuel burn. The nozzle throat includes relatively-high-erosion material layers and relatively-low-erosion material layers, with some layers of the throat resisting erosion, while other of the layers erode or ablate relatively quickly. The relatively-low-erosion material layers may act as thermal barriers to fix the throat at relatively stable geometry for long periods of time, such as during most of the burn of different fuel segments, with the relatively-high-erosion material layers allowing rapid transition of the throat from one geometry to the next. The layers may be made by resin transfer molding (RTM).

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