中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

42 records (took 0.017 seconds)

    THRUST-PRODUCING DEVICE WITH DETONATION MOTOR
    31.
    发明申请
    THRUST-PRODUCING DEVICE WITH DETONATION MOTOR 审中-公开
    带爆震电机的制动装置

    公开(公告)号：US20140137539A1

    公开(公告)日：2014-05-22

    申请号：US13680564

    申请日：2012-11-19

    Applicant: RAYTHEON COMPANY

    Inventor： Jeremy C. Danforth ,  Gavin Buttigieg ,  Brian J. Lukow ,  Henri Y. Kim

    IPC: F42B10/66

    CPC classification number: F42B10/661 ,  F02K7/02 ,  F02K9/08 ,  F42B3/04

    Abstract: A detonation thrust-producing device includes an explosive located in a recess in an external surface of a body. Detonation of the explosive expels material out of the recess, providing thrust to the body in an opposite direction. A mass, such as a metal disk, may be placed blocking or covering the external opening. The body may be a part of a vehicle, such as an airborne projectile. The thrust-producing device may include multiple detonation motors arrayed around the body, capable of being individually or multiply detonated. Such thrust-producing devices may be used for attitude adjustment, steering, or other control of the flight of the projectile or other air vehicle. The detonation thrust-producing devices have the advantage of a faster-response time than propellant-based devices, and do not need the nozzles that are used with many propellant-based devices.

    Abstract translation: 爆炸推力产生装置包括位于身体的外表面的凹部中的炸药。 爆炸物的爆炸将材料排出凹槽，向相反方向的身体提供推力。 可以将诸如金属盘的质量块放置成阻挡或覆盖外部开口。 身体可能是车辆的一部分，例如机载抛射体。 推力产生装置可以包括围绕身体排列的多个爆震电动机，能够单独或多次引爆。 这种推力产生装置可以用于姿态调节，转向或其他控制飞弹或其他空中飞行器的飞行。 爆炸推力产生装置具有比基于推进剂的装置更快的响应时间的优点，并且不需要与许多基于推进剂的装置一起使用的喷嘴。

    Solid propellant additive manufacturing system
    32.
    发明授权
    Solid propellant additive manufacturing system 有权

    公开(公告)号：US11208362B2

    公开(公告)日：2021-12-28

    申请号：US16226741

    申请日：2018-12-20

    Applicant: Raytheon Company

    Inventor： Matthew H. Summers ,  Jeremy C. Danforth ,  David G. Garrett ,  Mark T. Langhenry

    IPC: B29C64/165 ,  B33Y30/00 ,  B33Y40/00 ,  B29B7/00 ,  C06B21/00 ,  B33Y10/00 ,  B33Y70/00 ,  B33Y80/00 ,  B29K23/00 ,  B29K505/00 ,  B29L31/20 ,  B29L31/30

    Abstract: A system is used for additively manufacturing propellant elements, such as for rocket motors, includes partially curing a propellant mixture before extruding or otherwise dispensing the material, such that the extruded propellant material is deposited on the element in a partially-cured state. The curing process for the partially-cured extruded material may be completed shortly after the material is put into place, for example by the material being heated at or above its cure temperature, such that it finishes curing before it fully cools. The propellant material may be prepared by first mixing together, a fuel, an oxidizer, and a binder, such as in an acoustic mixer. After that mixing a curative may be added to the mixture. The propellant mixture may then be directed to an extruder (or other dispenser), in which the mixture is heated to or above a cure temperature prior to the deposition, and then deposited.

    Microwave ignition of electrically operated propellants
    34.
    发明授权
    Microwave ignition of electrically operated propellants 有权

    公开(公告)号：US10808649B2

    公开(公告)日：2020-10-20

    申请号：US15240932

    申请日：2016-08-18

    Applicant: Raytheon Company

    Inventor： James K. Villarreal ,  Jeremy C. Danforth ,  Matt H. Summers ,  Daniel K. Johnson ,  Mark T. Langhenry

    IPC: F02K9/95 ,  F02K9/94 ,  C06B45/10 ,  C06B23/00 ,  C06B27/00 ,  C06B29/00 ,  F02K9/08

    Abstract: Microwave energy is used to ignite and control the ignition of electrically operated propellant to produce high-pressure gas. The propellant includes conductive particles that act as a free source of electrons. Incoming microwave energy accumulates electric charge in an attenuation zone, which is discharged in the form of dielectric breakdowns to create local randomly oriented currents. The propellant also includes polar molecules. The polar molecules in the attenuation zone absorb microwave energy causing the molecules to rapidly vibrate thereby increasing the temperature of the propellant. The increase in temperature and the local current densities together establish an ignition condition to ignite and sustain ignition of an ignition surface of the attenuation zone as the zone regresses without igniting the remaining bulk of the propellant.

    Projectile with single-piece main body
    36.
    发明授权
    Projectile with single-piece main body 有权

    公开(公告)号：US10247530B2

    公开(公告)日：2019-04-02

    申请号：US15217482

    申请日：2016-07-22

    Applicant: Raytheon Company

    Inventor： Jeremy C. Danforth ,  Matthew H. Summers ,  David G. Garrett ,  Stephen M. Bagg

    IPC: F42B10/66 ,  B33Y80/00 ,  F02K9/97 ,  F02K9/42 ,  F42B6/00 ,  F42B10/00

    Abstract: A projectile, such as a railgun-launched projectile, includes a single-piece body that is additively manufactured. The single piece body includes fuel within it, and one or more cavities for receiving an oxidizer. The body also defines one or more combustion chambers therein for combustion of the fuel and oxidizer as part of a divert thruster system. Thus the projectile is able to fully contain the divert thruster system within the single-piece body without using any hot gas seals as part of the system. The body may also define a cavity for receiving a pressurized fluid, used as part of a cold-gas attitude control system of the projectile. The body may also define passages between the pressurized fluid cavity and other parts of the attitude control system, such as valves and/or nozzles that are outside of the body, for example being aft of the one-piece body.

    HYBRID ROCKET MOTOR WITH INTEGRAL OXIDIZER TANK
    40.
    发明申请
    HYBRID ROCKET MOTOR WITH INTEGRAL OXIDIZER TANK 审中-公开

    公开(公告)号：US20170234268A1

    公开(公告)日：2017-08-17

    申请号：US15044490

    申请日：2016-02-16

    Applicant: Raytheon Company

    Inventor： Matt H. Summers ,  Jeremy C. Danforth

    IPC: F02K9/72 ,  B33Y80/00 ,  B33Y10/00

    Abstract: 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.

Patent Agency Ranking