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    SATELLITE WITH INTEGRAL THRUSTERS
    3.
    发明公开
    SATELLITE WITH INTEGRAL THRUSTERS 审中-公开

    公开(公告)号：EP3439962A1

    公开(公告)日：2019-02-13

    申请号：EP16788609.2

    申请日：2016-10-11

    申请人： Raytheon Company

    发明人： KOEHLER, Frederick, B. ,  DANFORTH, Jeremy, C. ,  LYMAN, Ward, D. ,  LANGHENRY, Mark, T. ,  SUMMERS, Matt, H. ,  PONTIUS, Paul, E. ,  PAPE, Brian, M. ,  STALLINGS, Jared, D. ,  VILLARREAL, James, K. ,  VILLARREAL, Thomas

    IPC分类号： B64G1/10 ,  B64G1/40

    摘要： A satellite has thrusters that are integral parts of its frame. The frame defines cavities therein where thrusters are located. The thrusters may include an electrically-operated propellant and electrodes to activate combustion in the electrically-operated propellant. The frame may be additively manufactured, and the propellant and/or the electrodes may also be additively manufactured, with the frame and the propellant and/or the electrodes also being manufactured in a single process. In addition the thrusters may have nozzle portions through which combustion gases exit the thrusters. The thrusters may be located at corners and/or along edges of the frame, and may be used to accomplish any of a variety of maneuvers for the satellite. The satellite may be a small satellite, such as a CubeSat satellite, for instance having a volume of about 1 liter, and a mass of no more than about 1.33 kg.

    ADDITIVE MANUFACTURED COMBUSTIBLE ELEMENT WITH FUEL AND OXIDIZER
    6.
    发明公开
    ADDITIVE MANUFACTURED COMBUSTIBLE ELEMENT WITH FUEL AND OXIDIZER 审中-公开
    添加剂制造燃烧和氧化剂可燃元素

    公开(公告)号：EP3303812A1

    公开(公告)日：2018-04-11

    申请号：EP16708787.3

    申请日：2016-02-01

    申请人： Raytheon Company

    发明人： DANFORTH, Jeremy, C. ,  LANGHENRY, Mark, T. ,  SUMMERS, Matt, H. ,  PERDUE, Teresa E.

    IPC分类号： F02K9/12

    摘要： A combustible element includes regions of fuel material interspersed with regions of oxidizer material. The element may be made by additive manufacturing processes, such as three-dimensional printing, with the fuel material regions and the oxidizer material regions placed in appropriate locations in layer of the combustible element. For example, different extruders may be used to extrude and deposit portions of a fuel filament and an oxidizer filament at different locations in each layer of the combustible element. The combustible element may define a combustion chamber within the element, where combustion occurs when the combustible element is ignited. The fuel material and the oxidizer material may be selected, and their relative amounts may be controlled, such that desired relative amounts of fuel and oxidizer are present for combustion with desired characteristics, such as combustion rate.

    ROCKET MOTOR PRODUCED BY ADDITIVE MANUFACTURING
    9.
    发明公开
    ROCKET MOTOR PRODUCED BY ADDITIVE MANUFACTURING 审中-公开
    通过添加剂制造生产的火箭发动机

    公开(公告)号：EP3303813A1

    公开(公告)日：2018-04-11

    申请号：EP16708786.5

    申请日：2016-02-01

    申请人： Raytheon Company

    发明人： DANFORTH, Jeremy, C. ,  PERDUE, Teresa, E. ,  LANGHENRY, Mark, T. ,  SUMMERS, Matt, H.

    IPC分类号： F02K9/72 ,  F02K9/76

    CPC分类号： F02K9/95 ,  F02K9/72 ,  F02K9/76

    摘要： A nozzleless hybrid rocket motor includes a fuel element that defines a combustion chamber therewithin, in which combustion of the fuel and an oxidizer occurs. The combustion gases produced by the combustion between the fuel and the oxidizer transition to supersonic flow before leaving the fuel element, eliminating the need for a separate nozzle. The fuel element may be a part of a structural element of a vehicle, for example being a part of a fuselage, wing, fairing, or other part of a space vehicle or an air vehicle, with the fuel element an integral and continuous part of the structural element. Combustion of part of the fuel element may allow vehicle structure to be used to provide thrust, such as for maneuver, consuming part of the structure. The fuel element may be made by an additive manufacturing process.