公开(公告)号：US11754399B1

公开(公告)日：2023-09-12

申请号：US17182362

申请日：2021-02-23

Applicant: Orbital Research Inc.

Inventor： Michael Jankowski ,  Edward J. Rapp

IPC: G06T7/11 ,  G01C21/16 ,  F42B15/01 ,  F42B30/10

CPC classification number: G01C21/165 ,  F42B15/01 ,  F42B30/10

Abstract: Systems and methods for providing location and guidance are herein described, and more particularly for providing location and guidance in environments where global position systems (GPS) are unavailable or unreliable (GPS denied and/or degraded environments). The systems and methods herein utilize inertial measurement units (IMUs) to provide such location and guidance. More particularly, the systems and methods herein utilize a series of low-accuracy or low-resolution IMUs, in combination, to provide high-accuracy or high-resolution location and guidance results.

公开(公告)号：US11747121B2

公开(公告)日：2023-09-05

申请号：US17111914

申请日：2020-12-04

Applicant: BAE SYSTEMS Information and Electronic Systems Integration Inc.

Inventor： Steven F. Kimball ,  Andrew W. White

IPC: F42B10/26 ,  F42B15/01

CPC classification number: F42B10/26 ,  F42B15/01

Abstract: The system and method of spin stabilizing a guided munition where a motor provides necessary de-spinning torque. The despun PGK portion of a guided projectile is already at high rate of spin relative to the projectile body and the motor is operated to maintain that rate.

公开(公告)号：US20190063875A1

公开(公告)日：2019-02-28

申请号：US15684305

申请日：2017-08-23

Applicant: Rosemount Aerospace Inc.

Inventor： Todd Anthony Ell

IPC: F41G7/22 ,  G02B27/00 ,  G06K9/00 ,  G02B6/04 ,  F42B15/01

CPC classification number: F41G7/2246 ,  F41G7/2253 ,  F41G7/2293 ,  F42B10/46 ,  F42B15/01 ,  G02B5/005 ,  G02B6/04 ,  G02B6/06 ,  G02B27/0037 ,  G02B27/46 ,  G02B2207/129 ,  G06K9/00624

Abstract: Apparatus and associated methods relate to forming images for a terminal-imaging seeker using software defined optics. An optically-neutral lens with a ballistic-ogive-shaped front surface receives light from a scene aligned along an optical axis. The optically-neutral lens transmits the light received at the ballistic-ogive-shaped front surface to a planar rear surface, which is then transmitted to a coded-aperture plate aligned with the optical axis. The coded-aperture plate includes a plurality of pinhole-like apertures, each of which is configured to perform pinhole-like lensing of the scene. The plurality of pinhole-like apertures form a multiplex of overlapping images on a focal plane array aligned with the optical axis. An image processor reconstructs, based on a configuration of the plurality of pinhole-like apertures and the multiplex of overlapping images, a single image of the scene.

公开(公告)号：US20180340779A1

公开(公告)日：2018-11-29

申请号：US15964147

申请日：2018-04-27

Applicant: Atlantic Inertial Systems Limited

Inventor： Nicholas Mark FAULKNER ,  John Keith SHEARD

IPC: G01C21/18 ,  G01C25/00 ,  F42B15/01

CPC classification number: G01C21/18 ,  F41G7/36 ,  F42B15/01 ,  G01C21/16 ,  G01C25/005 ,  G05D1/108

Abstract: An inertial measurement system comprising: a first, roll gyro with an axis oriented substantially parallel to the spin axis of the projectile; a second gyro and a third gyro with axes arranged with respect to the roll gyro; a controller, arranged to: compute a current projectile attitude from the outputs of the first, second and third gyros; operate a Kalman filter that receives a plurality of measurement inputs including at least roll angle, pitch angle and yaw angle and that outputs at least a roll angle error; initialise the Kalman filter with a roll angle error uncertainty representative of a substantially unknown roll angle; generate at least one pseudo-measurement from stored expected flight data; provide said pseudo-measurement(s) to the corresponding measurement input of the Kalman filter; and apply the roll angle error from the Kalman filter as a correction to the roll angle.

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：US09633437B2

公开(公告)日：2017-04-25

申请号：US14173796

申请日：2014-02-05

Applicant: Jahangir S Rastegar

Inventor： Jahangir S Rastegar

IPC: G06T7/20 ,  G06T7/00 ,  G06K9/00 ,  G06K17/00 ,  F42B15/01 ,  F41G7/30 ,  G05D1/12

CPC classification number: G06T7/285 ,  F41G7/30 ,  F41G7/306 ,  F42B15/01 ,  G05D1/12 ,  G06K9/00523 ,  G06K2017/0045 ,  G06K2209/21 ,  G06T7/20

Abstract: A method for displaying successive image frames on a display. The method including: processing image data containing the successive image frames to identify features in an image frame and to display the image frame to a user with two or more of the identified features highlighted; manually selecting one of the identified features by a user; determining a portion of a subsequent image frame in which the selected feature is likely to be present; and if the selected feature is found in the portion of the subsequent image frame, displaying the subsequent image frame to change the position of the selected feature.

公开(公告)号：US20170101884A1

公开(公告)日：2017-04-13

申请号：US15287362

申请日：2016-10-06

Applicant: Leigh Aerosystems Corporation

Inventor： Stephen L. Harris ,  Gordon L. Harris

IPC: F01D15/10 ,  F01D25/16 ,  F01D5/02 ,  F01D25/24 ,  F42B15/01 ,  F42B30/10

CPC classification number: F01D15/10 ,  F01D5/02 ,  F01D25/16 ,  F01D25/24 ,  F05D2210/12 ,  F05D2240/60 ,  F42B10/64 ,  F42B15/01 ,  F42B30/10 ,  F42C11/008

Abstract: A Projectile Continuous Power Module (PCMP) is configured to take incoming or oncoming airflow of an inflight projectile and direct the airflow to a turbine for converting the airflow into electrical power. The PCMP is mounted within or otherwise coupled to an airframe of the projectile. The PCMP is coupled to the projectile in a manner such that an air inlet of the projectile is positioned to capture incoming or oncoming boundary layer airflow as the projectile travels.

公开(公告)号：US20170074619A1

公开(公告)日：2017-03-16

申请号：US14850141

申请日：2015-09-10

Applicant: THE BOEING COMPANY

Inventor： Kevin Dominguez

IPC: F41G7/00

CPC classification number: F41G7/001 ,  F42B15/01 ,  F42B35/00

Abstract: A missile system includes a plurality of components, and a testing instrumentation platform secured within at least one of the plurality of components. The testing instrumentation platform is secured within the component(s) through at least one platform supporting adapter assembly. The platform supporting adapter assembly may include an adapter having a planar panel that supports one or more fasteners. The fastener(s) are configured to securely connect to a portion of a base of the testing instrumentation platform. At least one through-hole may be formed through a portion of the adapter. At least one tapered bolt is configured to be securely retained within the through-hole(s). The tapered bolt(s) securely connects the adapter to the component(s).

Abstract translation: 导弹系统包括多个部件，以及固定在所述多个部件中的至少一个部件中的测试仪器平台。 测试仪器平台通过至少一个平台支撑适配器组件固定在组件内。 平台支撑适配器组件可以包括具有支撑一个或多个紧固件的平面面板的适配器。 紧固件构造成牢固地连接到测试仪器平台的基部的一部分。 可以通过适配器的一部分形成至少一个通孔。 至少一个锥形螺栓构造成可靠地保持在通孔内。 锥形螺栓将适配器牢固地连接到部件上。

公开(公告)号：US09587923B2

公开(公告)日：2017-03-07

申请号：US15057215

申请日：2016-03-01

Applicant: BAE SYSTEMS ROKAR INTERNATIONAL LTD

Inventor： Gil Wurzel ,  Assaf Malul

IPC: F42B10/06 ,  F42B15/01 ,  F42B10/64 ,  F42B10/04 ,  F42B10/26 ,  F42B15/10

CPC classification number: F42B15/01 ,  F42B10/04 ,  F42B10/26 ,  F42B10/64 ,  F42B15/10

Abstract: A guiding assembly is adapted to be connected to a projectile and comprising a rear main unit adapted to be connected to the front end of the projectile, and a front main unit rotatably connected at its rear end to the front end of the rear main unit. The front main unit is adapted to rotate about a central longitudinal axis. A relative speed control unit is operable between the rear main unit and the front main unit and capable of providing spin braking force to slow the relative speed of rotation of the front main unit. An at least one guiding fin radially extends from the front main unit. The pitch angle of the fin is controllable by a return spring connected to the fin so that the pitch angle of the fin is growing as the aerodynamic pressure on the fin lowers and it is growing smaller as the aerodynamic pressure on the fin gets bigger.

Abstract translation: 引导组件适于连接到射弹，并且包括适于连接到射弹前端的后主单元，以及在其后端可转动地连接到后主体前端的前主单元。 前主体适于围绕中心纵向轴线旋转。 相对速度控制单元可在后主单元和前主单元之间操作并且能够提供旋转制动力以减慢前主单元的相对旋转速度。 至少一个引导翅片从前主单元径向延伸。 翅片的俯仰角可以通过连接到翅片的复位弹簧来控制，使得当翅片上的空气动力压力降低时翅片的俯仰角度增加，并且随着翅片上的空气动力学压力变大，翅片的俯仰角变小。

公开(公告)号：US09580191B2

公开(公告)日：2017-02-28

申请号：US14550782

申请日：2014-11-21

Applicant: Blue Origin, LLC

Inventor： Mark Featherstone ,  Frederick W. Boelitz ,  Roger E. Ramsey ,  David M. Biggs

IPC: B64G1/62 ,  B64G1/00 ,  B64C9/00 ,  B64G1/24 ,  F42B10/64 ,  B64G1/60 ,  F42B15/01 ,  B64G1/40

CPC classification number: B64G1/62 ,  B64C9/00 ,  B64G1/002 ,  B64G1/24 ,  B64G1/40 ,  B64G1/401 ,  B64G1/60 ,  F42B10/64 ,  F42B15/01

Abstract: Vehicles with control surfaces and associated systems and methods are disclosed. In a particular embodiment, a rocket can include a plurality of bidirectional control surfaces positioned toward an aft portion of the rocket. In this embodiment, the bidirectional control surfaces can be operable to control the orientation and/or flight path of the rocket during both ascent, in a nose-first orientation, and descent, in a tail-first orientation for, e.g., a tail-down landing. Launch vehicles with fixed and deployable deceleration surfaces and associated systems and methods are also disclosed.

Abstract translation: 具有控制表面和相关系统和方法的车辆被公开。 在特定实施例中，火箭可以包括朝向火箭的后部定位的多个双向控制表面。 在该实施例中，双向控制表面可操作以控制火箭在朝向前倾的方向上升和向下延伸的方向和/或飞行路径， 降落。 还公开了具有固定和可部署的减速表面的运载火车以及相关的系统和方法。