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    Rocket motor with embedded burnable cutting explosive energetic material
    2.
    发明授权
    Rocket motor with embedded burnable cutting explosive energetic material 有权

    公开(公告)号：US11732676B1

    公开(公告)日：2023-08-22

    申请号：US17711409

    申请日：2022-04-01

    Applicant: Raytheon Company

    Inventor： Coulton T. Sadler ,  Mitchell Lee Moffet ,  Erik C. Rupp ,  Reuben E. Weinzinger

    IPC: F02K9/38 ,  F42B1/028 ,  F02K9/34

    CPC classification number: F02K9/38 ,  F02K9/346 ,  F42B1/028

    Abstract: A rocket motor has an energetic material between solid fuel (propellent) and a casing that surrounds the solid fuel. The energetic material is configured to be burned along with the solid fuel during normal operation of the rocket motor to produce thrust. The energetic material can also be detonated to cause rupture of the casing. The detonation may be initiated as part of a flight termination process. The detonation may also be initiated as a part of process to prevent as a higher-order reaction, such as in reaction to heating from a fire or other cause. The energetic material may be arranged to function as part of a shaped charge, able to split the casing when detonated. By being located inside the casing, the energetic material does not adversely affect aerodynamics of the flight vehicle of which the rocket motor is a part, such as a missile.

    Rocket Motors and Their Use
    7.
    发明申请
    Rocket Motors and Their Use 有权
    火箭发动机及其使用

    公开(公告)号：US20150361923A1

    公开(公告)日：2015-12-17

    申请号：US14760974

    申请日：2013-01-15

    Applicant: Roger Mark SLOMAN

    Inventor： Roger Mark Sloman

    IPC: F02K9/34 ,  F02K9/97 ,  F02K9/16

    CPC classification number: F02K9/346 ,  F02K1/00 ,  F02K9/12 ,  F02K9/16 ,  F02K9/28 ,  F02K9/97 ,  F05D2250/12 ,  F41H7/042

    Abstract: Apparatus, methods and computer programs are provided. In one example, an apparatus is a rocket motor, comprising: a casing having a length dimension, a width dimension and a depth dimension, wherein the length dimension is greater than the width dimension and greater than the depth dimension; and propellant, located inside the casing, arranged to generate a force in a direction that is substantially perpendicular to the length dimension of the casing.

    Abstract translation: 提供了装置，方法和计算机程序。 在一个示例中，装置是火箭发动机，包括：具有长度尺寸，宽度尺寸和深度尺寸的壳体，其中所述长度尺寸大于所述宽度尺寸并且大于所述深度尺寸; 并且位于壳体内的推进剂被布置成在基本上垂直于壳体的长度尺寸的方向上产生力。

    BASALT FIBER AND NANOCLAY COMPOSITIONS, ARTICLES INCORPORATING THE SAME, AND METHODS OF INSULATING A ROCKET MOTOR WITH THE SAME
    9.
    发明申请
    BASALT FIBER AND NANOCLAY COMPOSITIONS, ARTICLES INCORPORATING THE SAME, AND METHODS OF INSULATING A ROCKET MOTOR WITH THE SAME 有权
    碱性纤维和纳米颗粒组合物，与其相同的制品，以及与其相同的绝缘电动机的方法

    公开(公告)号：US20100205929A1

    公开(公告)日：2010-08-19

    申请号：US12765585

    申请日：2010-04-22

    Applicant: Himansu M. Gajiwala

    Inventor： Himansu M. Gajiwala

    IPC: F02K9/60 ,  C08K3/34 ,  B05D7/22

    CPC classification number: F02K9/974 ,  F02K9/346 ,  F05D2300/431 ,  F05D2300/433 ,  F05D2300/434 ,  F05D2300/614

    Abstract: An insulation composition that comprises at least one nitrile butadiene rubber, basalt fibers, and nanoclay is disclosed. Further disclosed is an insulation composition that comprises polybenzimidazole fibers, basalt fibers, and nanoclay. The basalt fibers may be present in the insulation compositions in a range of from approximately 1% by weight to approximately 6% by weight of the total weight of the insulation composition. The nanoclay may be present in the insulation compositions in a range of from approximately 5% by weight to approximately 10% by weight of the total weight of the insulation composition. Rocket motors including the insulation compositions and methods of insulating a rocket motor are also disclosed.

    Abstract translation: 公开了一种包含至少一种丁腈橡胶，玄武岩纤维和纳米粘土的绝缘组合物。 进一步公开的是包含聚苯并咪唑纤维，玄武岩纤维和纳米粘土的绝缘组合物。 玄武岩纤维可以以绝热组合物总重量的约1重量％至约6重量％的范围存在于绝缘组合物中。 纳米粘土可以以绝热组合物的总重量的约5重量％至约10重量％的范围存在于绝缘组合物中。 还公开了包括隔热组合物和绝热火箭发动机的方法的火箭发动机。

    Rocket motor with pellet and bulk solid propellants
    10.
    发明授权
    Rocket motor with pellet and bulk solid propellants 有权
    火箭发动机带有颗粒和散装固体推进剂

    公开(公告)号：US07685940B1

    公开(公告)日：2010-03-30

    申请号：US12053475

    申请日：2008-03-21

    Applicant: Robert J. Cavalleri ,  Thomas A. Olden

    Inventor： Robert J. Cavalleri ,  Thomas A. Olden

    IPC: F42B15/10 ,  F02K9/12

    CPC classification number: F02K9/08 ,  F02K9/10 ,  F02K9/24 ,  F02K9/346

    Abstract: There is disclosed a solid fuel rocket motor which may include a case and a nozzle coupled to the case. A plurality of fuel pellets may be disposed within the case. An igniter may be disposed to ignite at least a portion of the fuel pellets. A pellet retainer may be positioned within the case to retain the plurality of fuel pellets within the case. The pellet retainer may be perforated to allow exhaust gases to flow from the ignited fuel pellets to the nozzle while preventing unburned fuel pellets from being expelled through the nozzle.

    Abstract translation: 公开了一种固体燃料火箭发动机，其可以包括壳体和连接到壳体的喷嘴。 多个燃料丸可以设置在壳体内。 可以设置点火器以点燃至少一部分燃料颗粒。 颗粒保持器可以定位在壳体内以将多个燃料颗粒保持在壳体内。 颗粒保持器可以被穿孔以允许废气从点燃的燃料颗粒流到喷嘴，同时防止未燃烧的燃料颗粒通过喷嘴排出。

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