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    PROPULSION SYSTEM WITH SINGLE INITIATOR FOR MULTIPLE ROCKET MOTORS
    13.
    发明申请
    PROPULSION SYSTEM WITH SINGLE INITIATOR FOR MULTIPLE ROCKET MOTORS 有权

    公开(公告)号：US20230073547A1

    公开(公告)日：2023-03-09

    申请号：US17466245

    申请日：2021-09-03

    申请人： Raytheon Company

    发明人： Jacob Pinello-Benavides ,  John Meschberger ,  Stephen Moore ,  Edward Little, III

    IPC分类号： F02K9/95 ,  F02K9/32

    摘要： A propulsion system includes multiple solid rocket motors that are activated by a single initiator. The rocket motors act in parallel, providing thrust in a single direction. The initiator activates an ignition charge that is in or operatively coupled to a plenum that transports hot gasses from the ignition charge to the rockets to be ignited. The plenum may be an annular plenum, which may be located in an annular manifold. The plenum may be an unchoked plenum, allowing flow of hot gasses without choking. The plenum may be lined with an insulator material. A cover may be used to cover the plenum, and also to receive the rocket motors. The rocket motors may be solid-fuel rocket motors. The individual rocket motors may have separate ignition booster charges coupled to the plenum, which are ignited by the ignition charge and which in turn ignite the propellant grains.

    Onboard structure convertible into a propellant for electric propulsion
    14.
    发明授权
    Onboard structure convertible into a propellant for electric propulsion 有权

    公开(公告)号：US11542926B2

    公开(公告)日：2023-01-03

    申请号：US16897193

    申请日：2020-06-09

    申请人： The Aerospace Corporation

    发明人： Horatiu C. Dragnea ,  Henry Helvajian ,  Kushal Patel

    IPC分类号： F03H1/00 ,  F02K9/08 ,  F02K9/32 ,  F02K9/36 ,  F02K9/44 ,  F02K9/42

    摘要： A vehicle comprising a structure, a plurality of heating sources, and a transport mechanism. The structure is comprised of multiple materials, a composite such that some of the material constituents can be extracted leaving behind others via application of energy (such as de-alloying). The extracted material or materials are configured to be re-purposed into a propellant. The plurality of heating elements surrounds or is embedded within the structure configured to convert the material into the propellant. The transport mechanism is configured to transport the propellant from the structure to a reservoir or to the propulsion system.

    Hybrid rocket motor with integral oxidizer tank
    15.
    发明授权
    Hybrid rocket motor with integral oxidizer tank 有权

    公开(公告)号：US11326556B2

    公开(公告)日：2022-05-10

    申请号：US17035880

    申请日：2020-09-29

    申请人： Raytheon Company

    发明人： Matt H. Summers ,  Jeremy C. Danforth

    IPC分类号： F02K9/72 ,  F02K9/32 ,  F02K9/10 ,  B33Y10/00 ,  B33Y80/00

    摘要： A hybrid rocket motor includes a solid fuel element, and an oxidizer tank containing an oxidizer. The solid fuel element adjoins and at least partially defines a combustion chamber in which the solid fuel and the oxidizer are burned, to produce thrust from the hybrid rocket motor. The oxidizer tank is at least partially within the combustion chamber, and the entire oxidizer tank may be within the combustion chamber. The oxidizer tank may be protected by an insulating material, which may also serve as a structural material that contains the pressure of the oxidizer. The insulating material and the fuel material may both be polymer-based materials, although they may be different materials having different characteristics, for example including different additives to the same polymer material. The fuel element and the oxidizer tank may be made by additive manufacturing processes, for example by adding different materials in different locations.

    VARIABLE BURN-RATE SOLID ROCKET MOTOR IGNITION METHOD
    16.
    发明申请
    VARIABLE BURN-RATE SOLID ROCKET MOTOR IGNITION METHOD 有权

    公开(公告)号：US20220082066A1

    公开(公告)日：2022-03-17

    申请号：US17017741

    申请日：2020-09-11

    申请人： Raytheon Company

    发明人： Frederick B. Koehler ,  Mark J. Meisner ,  Jeff L. Vollin

    IPC分类号： F02K9/26 ,  F02K9/32

    摘要： A solid rocket motor uses at least one thermally conductive wire or at least one pair of electrically conductive wires to increase a burn surface area of a propellant grain and thus a thrust of the rocket motor. The rocket motor includes a pulse chamber containing a burnable propellant grain, a propellant inhibited center bore bonded to surfaces of the burnable propellant grain, and at least one conductive wire coupled to the burnable propellant grain and arranged in variable regions along the propellant inhibited center bore. The conductive wire is configured for passive or active activation to ignite the propellant inhibited center bore that subsequently burns in the variable regions. The thermally conductive wire is formed of a refractory metal or refractory alloy material that enables the entire length of the wire to be heated simultaneously or nearly simultaneously when the wire is passively activated.

    Hybrid rocket engine with improved solid fuel segment
    17.
    发明授权
    Hybrid rocket engine with improved solid fuel segment 有权

    公开(公告)号：US11060483B2

    公开(公告)日：2021-07-13

    申请号：US16351179

    申请日：2019-03-12

    申请人： TAIWAN INNOVATIVE SPACE, INC.

    发明人： Yen-Sen Chen

    IPC分类号： F02K9/72 ,  F02K9/32 ,  F02K9/52 ,  B64G1/40

    摘要： A rocket engine with an improved solid fuel segment mainly comprises a combustion chamber, a solid fuel segment installed in the combustion chamber, and an oxidizer injector installed at one end of the combustion chamber. The solid fuel segment surrounds and forms a trajectory to allow the oxidizer injector to inject oxidizer into the trajectory, in particular, on the solid fuel segment is formed with a plurality of protrusions, between the each two protrusions are defined a recess, a flame holding hot-gas region is formed between the protrusion and the recess, so as to produce eddy current in the flame holding hot-gas region when the propellant mixture is burned inside the trajectory, such that the whole solid fuel segment can produce even regression rate and high combustion efficiency.

    Pulse rocket motor including a dividing sheet for separating the first grain propellant from the second grain propellant
    20.
    发明授权
    Pulse rocket motor including a dividing sheet for separating the first grain propellant from the second grain propellant 有权
    脉冲火箭发动机包括用于将第一颗粒推进剂与第二颗粒推进剂分离的分隔板

    公开(公告)号：US09151245B2

    公开(公告)日：2015-10-06

    申请号：US13529836

    申请日：2012-06-21

    申请人： Hiroyuki Kawadu ,  Ichiro Yamaguchi ,  Shuji Hagiwara ,  Shoji Endo ,  Tokuichiro Ojima

    发明人： Hiroyuki Kawadu ,  Ichiro Yamaguchi ,  Shuji Hagiwara ,  Shoji Endo ,  Tokuichiro Ojima

    IPC分类号： F02K9/08 ,  F02K9/28 ,  F02K9/32 ,  F02K9/36

    CPC分类号： F02K9/08 ,  F02K9/28 ,  F02K9/32 ,  F02K9/36

    摘要： A pulse rocket motor has a hollow cylinder-like first grain situated in a rear section of a pressure vessel; a first igniter for igniting the first grain; a hollow cylinder-like second grain situated in a front section of the pressure vessel; a second igniter for igniting the second grain; and a dividing sheet member that covers the second grain within the pressure vessel. The dividing sheet member includes a dividing sheet expanding at least along the inner circumferential surface of the second grain and holders formed integrally with the dividing sheet at both ends of the dividing sheet by cure adhesion and attached to the pressure vessel. The dividing sheet includes a brittle portion that expands along the inner circumferential surface of the second grain through a rear end face of the second grain and is more brittle than other portions.

    摘要翻译： 脉冲火箭发动机具有位于压力容器后部的中空圆柱状的第一颗粒; 点燃第一颗谷子的第一个点火器; 位于所述压力容器的前部的中空的圆筒状的第二颗粒; 用于点燃第二颗粒的​​第二个点火器; 以及覆盖压力容器内的第二颗粒的​​分隔片部件。 分隔片部件包括至少沿着第二颗粒的​​内周面延伸的分隔片，并且通过固化粘合力在分隔片的两端与分隔片一体形成的保持件并且附接到压力容器。 分割片包括通过第二晶粒的后端面沿着第二晶粒的内周面膨胀并且比其它部分更脆的脆性部分。