公开(公告)号：US09927217B1

公开(公告)日：2018-03-27

申请号：US14847820

申请日：2015-09-08

Applicant: Valley Tech Systems

Inventor： Russell Carlson ,  Dustin Barr ,  Allen Yan

IPC: F42B10/66 ,  F42B15/01 ,  F42B10/00

CPC classification number: F42B15/01 ,  F42B10/663

Abstract: An attitude control system for a guided missile includes a gas generator, an accumulator coupled to the gas generator, and a valve positioned between the gas generator and the accumulator. The gas generator contains propellant that burns to provide hot gas to pressurize the accumulator. The valve is opened to recharge the accumulator with hot gas and closed when it is full. A vent valve can be included to extinguish the propellant in the gas generator. The accumulator can be coupled to thrusters that use the stored hot gas to adjust the attitude of the guided missile.

公开(公告)号：US20180073842A1

公开(公告)日：2018-03-15

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 ,  F42B6/00 ,  F02K9/97 ,  F02K9/42 ,  B33Y80/00

CPC classification number: F42B10/661 ,  B33Y80/00 ,  F02K9/425 ,  F02K9/97 ,  F42B6/006 ,  F42B10/663

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.

公开(公告)号：US20180050825A1

公开(公告)日：2018-02-22

申请号：US15423909

申请日：2017-02-03

Applicant: Bayern-Chemie Gesellschaft für flugchemische Antriebe mbH

Inventor： Jürgen Ramsel ,  Pedro Caldas-Pinto ,  Karl Wieland Naumann ,  Helmut Niedermaier ,  Tobias Meyer ,  Albert Thumann ,  Susanne Risse

IPC: B64G1/26 ,  F41H11/02 ,  F02K9/72 ,  F02K9/80

CPC classification number: B64G1/26 ,  B64G1/401 ,  B64G1/402 ,  F02K9/52 ,  F02K9/68 ,  F02K9/72 ,  F02K9/80 ,  F02K9/88 ,  F02K9/94 ,  F41H11/02 ,  F42B10/663

Abstract: Apparatus for trajectory control and/or position control of a missile (99), comprising a controllable gas generator (109, 200) with a fuel flow control valve (124, 213), an injector head (112, 202), a combustion chamber (111) and at least one outflow nozzle (103, 204) or at least one throttle.

公开(公告)号：US09377279B2

公开(公告)日：2016-06-28

申请号：US14258274

申请日：2014-04-22

Applicant: Raytheon Company

Inventor： Andrew B. Facciano ,  William G. Graves ,  Michael A. Barker ,  Michael S. Alkema ,  Jeffrey S. Larson

IPC: F42B10/66 ,  F42B15/01 ,  F42B10/00 ,  F42B15/00

CPC classification number: F42B15/01 ,  F42B10/661 ,  F42B10/663

Abstract: A flight vehicle includes a nose portion, a fuselage retaining structure aft of the nose portion, and an axial motor for expelling axial thrust along a longitudinal axis of the flight vehicle. Radial motors are coupled to the retaining structure and axisymmetrically arranged about the axial motor. Each radial motor is configured to expel radial thrust radially outwardly in respect to the flight vehicle. Roll thrusters are operatively coupled with the radial motors and coupled to the fuselage retaining structure. The roll thrusters are configured to provide a roll moment of the flight vehicle about a central longitudinal axis of the flight vehicle. Ejectors are operatively coupled to the radial motors, and a controller is operatively coupled to the radial motors and the ejectors. The controller is configured to selectively fire and selectively eject the radial motors to maintain relative centering of a center of gravity of the flight vehicle.

Abstract translation: 飞行器车辆包括鼻部，机身保持结构在前部的后部，以及用于沿着飞行器车辆的纵向轴线排出轴向推力的轴向马达。 径向电动机联接到保持结构并围绕轴向电动机轴对称布置。 每个径向马达构造成相对于飞行器车辆径向向外排出径向推力。 滚动推进器可操作地与径向马达耦合并联接到机身保持结构。 滚动推进器被配置成围绕飞行器车辆的中心纵向轴线提供飞行车辆的滚动时刻。 喷射器可操作地联接到径向马达，并且控制器可操作地联接到径向马达和喷射器。 控制器被配置为选择性地起动并选择性地弹出径向马达以维持飞行器车辆的重心的相对定心。

公开(公告)号：US09194332B2

公开(公告)日：2015-11-24

申请号：US14118600

申请日：2012-05-16

Applicant: Pascal Caubet ,  Aurore Ferrant

Inventor： Pascal Caubet ,  Aurore Ferrant

IPC: F02K9/08 ,  B64G1/26 ,  F42B10/66 ,  B64G1/40

CPC classification number: F02K9/08 ,  B64G1/26 ,  B64G1/401 ,  F42B10/663

Abstract: A system for in-flight attitude control and side-force steering includes a thruster body and a plurality of valves capable of generating side thrusts put into communication with the thruster body. The valves are arranged in two sets of valves spaced apart from each other towards the front and towards the rear of the thruster body in substantially symmetrical manner relative to the center of gravity of the vehicle situated on a longitudinal axis (A) of the vehicle. Each set comprises a first pair of valves generating thrust in opposite directions along axes that are not in alignment and are parallel to a first axis, and a second pair of valves generating thrust in opposite directions along axes that are not aligned and are parallel to a second axis. The first and second axes are distinct and perpendicular to the longitudinal axis of the vehicle.

Abstract translation: 用于飞行中姿态控制和侧向转向的系统包括推进器主体和能够产生与推进器主体连通的侧向推力的多个阀。 这些阀以相对于位于车辆的纵向轴线（A）上的车辆的重心基本上对称的方式布置成两组彼此间隔开的推进器主体的前部和后部。 每个组包括第一对阀门，其沿着不对准并且平行于第一轴线的轴线沿相反方向产生推力，并且第二对阀门沿着不对准并且平行于第一轴线的轴线沿相反方向产生推力 第二轴。 第一和第二轴线是不同的并且垂直于车辆的纵向轴线。

公开(公告)号：US20140138475A1

公开(公告)日：2014-05-22

申请号：US13669935

申请日：2012-11-06

Applicant: Raytheon Company

Inventor： Andrew B. Facciano ,  Michael S. Alkema ,  Robert T. Moore

IPC: F41G7/00

CPC classification number: F42B10/663

Abstract: A rocket is provided and includes booster stages at a rear of the nose cone, the booster stages being configured for propelling the nose cone in a propulsion direction and a divert control system housed entirely in the nose cone for controlling an orientation of the propulsion direction.

Abstract translation: 提供火箭并且包括位于鼻锥后部的增压器级，助推器级构造成用于推动推进方向上的鼻锥，以及完全容纳在鼻锥中的转向控制系统，用于控制推进方向的取向。

公开(公告)号：US08536502B2

公开(公告)日：2013-09-17

申请号：US13430678

申请日：2012-03-26

Applicant: John William Hunter ,  Harry E. Cartland ,  Philip James Sluder ,  Richard Edward Twogood

Inventor： John William Hunter ,  Harry E. Cartland ,  Philip James Sluder ,  Richard Edward Twogood

IPC: F42B10/02 ,  F42B10/26 ,  F42B15/10 ,  F42B10/00 ,  F42B15/00

CPC classification number: B64G1/002 ,  F41A1/02 ,  F41B11/68 ,  F41F1/00 ,  F42B10/663 ,  F42B15/01

Abstract: A vehicle for launching from a gas gun having a housing; preferably incorporating a precessional attitude control system; and utilizing a flared base, fins, or active use of the attitude control system during passage through the atmosphere. Subtly canting the fins can produce desired spinning of the vehicle. The propulsion system can employ liquid, hybrid, or solid fuel. A removable aero-shell assists atmospheric flight with thermal protection being provided by anticipated ablation, an ablative aero-spike, or transpirational cooling. And a releasable sabot enhances the effectiveness of the launch.

Abstract translation: 用于从具有外壳的气枪发射的车辆; 优选地包括进动姿态控制系统; 并且在通过大气的过程中利用喇叭形底座，翅片或主动使用姿态控制系统。 细小的鳍片可以产生所需的车辆旋转。 推进系统可以采用液体，混合或固体燃料。 可移动的航空壳可以帮助大气飞行，通过预期的消融，消融空气尖峰或蒸气冷却提供热保护。 并且可释放的sabot增强了发射的有效性。

公开(公告)号：US08362408B2

公开(公告)日：2013-01-29

申请号：US12603725

申请日：2009-10-22

Applicant: Robert J. Carlson

Inventor： Robert J. Carlson

IPC: F41G7/00

CPC classification number: F42B10/663 ,  F42B10/40

Abstract: A steerable projectile comprises a pressure chamber to hold gas in a pressurized state; and a body section coupled to the pressure chamber, the body section having a flight system to use the pressurized gas for adjusting a trajectory of the projectile. The pressure chamber comprises an orifice in a wall of the pressure chamber; and a check valve corresponding to the orifice, the check valve configured to allow gas that results from ignition of a propellant to enter the pressure chamber via the corresponding orifice and to prevent the gas, once inside the pressure chamber, from exiting the pressure chamber via the corresponding orifice.

Abstract translation: 可操纵的抛射体包括用于将气体保持在加压状态的压力室; 以及联接到所述压力室的主体部分，所述主体部分具有使用所述加压气体来调节所述弹丸的轨迹的飞行系统。 所述压力室包括在所述压力室的壁中的孔口; 以及与所述孔对应的止回阀，所述止回阀构造成允许由推进剂的点燃引起的气体经由相应的孔口进入压力室，并且一旦在压力室内部阻止气体离开压力室经由 相应的孔。

公开(公告)号：US08245496B2

公开(公告)日：2012-08-21

申请号：US12727335

申请日：2010-03-19

Applicant: Thomas Maier

Inventor： Thomas Maier

IPC: F02K1/00 ,  F02K9/28

CPC classification number: F02K9/88 ,  F02K9/30 ,  F02K9/72 ,  F02K9/94 ,  F42B10/663

Abstract: Control and/or drive device for a flying body for ejecting hot gas streams of a combusted fuel combination of at least a first and second component. Device includes a first hollow chamber body structured and arranged to contain first component, a second hollow chamber body structured and arranged to contain second component, a controllable fuel valve arranged between first hollow chamber body and second hollow chamber body to control feed of first component to second hollow chamber body, and a plurality of outlets structured and arranged to eject respective hot gas streams for influencing a flight path of flying body. Second hollow chamber body is formed as a combustion chamber for combusting the at least first and second components within second hollow chamber body to generate respective hot gas streams, and plurality of outlets are connected to the second hollow chamber body.

Abstract translation: 用于飞行体的用于喷射至少第一和第二部件的燃烧燃料组合的热气流的控制和/或驱动装置。 装置包括构造和布置成容纳第一部件的第一中空室主体，构造和布置成容纳第二部件的第二中空室主体，布置在第一中空室主体和第二中空室主体之间的可控燃料阀，以控制第一部件的进给 第二中空室体，以及多个出口，其结构和布置成喷射用于影响飞行体的飞行路径的各个热气流。 第二中空室体形成为用于燃烧第二中空室主体内的至少第一和第二部件的燃烧室，以产生相应的热气流，并且多个出口连接到第二中空室主体。

公开(公告)号：US20120048991A1

公开(公告)日：2012-03-01

申请号：US13319777

申请日：2011-03-09

Applicant: Robert D. Frey, JR.

Inventor： Robert D. Frey, JR.

IPC: F42B15/01 ,  F42B10/26 ,  F42D99/00 ,  F42B10/02

CPC classification number: F42B10/663 ,  F41G7/2246 ,  F42B10/06 ,  F42B10/66 ,  F42B10/666

Abstract: A system and method for guiding a projectile is presented. A nozzle system includes a boom assembly body that can be attached to a rear end of a projectile. A gas tank in the boom assembly contains pressurized gas. Fins are attached to the boom assembly body to guide the projectile. A valve lets a pulse of gas out of the gas tank. A nozzle expels the pulse of gas to control an angle of attack and lift of the projectile to guide the projectile to a target.

Abstract translation: 介绍了一种引导弹丸的系统和方法。 喷嘴系统包括可附接到射弹的后端的吊杆组件主体。 起重臂组件中的气罐包含加压气体。 叉子连接到悬臂组件体上以引导抛射体。 阀门将气体脉冲从气罐中排出。 喷嘴排出气体脉冲以控制射弹的迎角和升力，以将射弹引导到目标。