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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
Applicant: RAYTHEON COMPANY
Inventor： SUMMERS, Matt H. , CASE, David M. , RAYMOND, John J. , FOWLER, Gray , LANGHENRY, Mark T.
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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公开(公告)号：EP3850206A1
公开(公告)日：2021-07-21
申请号：EP19769681.8
申请日：2019-09-03
Applicant: Raytheon Company
Inventor： SUMMERS, Matt H. , CASE, David M. , RAYMOND, John J. , FOWLER, Gray , LANGHENRY, Mark T.
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