公开(公告)号：US20250051009A1

公开(公告)日：2025-02-13

申请号：US18514686

申请日：2023-11-20

Applicant: AGENCY FOR DEFENSE DEVELOPMENT

Inventor： Junho LEE ,  Minji BAE ,  Youngil KIM ,  Sora JEONG

IPC: B64D7/08

Abstract: Provided is a detent apparatus for a rocket, The detent apparatus includes a detent including a first end portion, a second end portion opposite to the first end portion, an extension extending between the first end portion and the second end portion, and a detent protrusion configured to engage with the rocket, a first elastic body configured to elastically support the first end portion of the detent and connected to the first end portion, and an electrical safety device configured to prevent rotation of the detent including a hinge fixing frame having a hinge axis parallel to the detent rotation axis, a detent support configured to rotate around the hinge axis and support the detent, a hinge axis shaft arranged on the hinge axis, a solenoid configured to rotate the detent support by pushing the detent support, and a micro switch activated when the detent support rotates.

公开(公告)号：US11577835B2

公开(公告)日：2023-02-14

申请号：US16806111

申请日：2020-03-02

Applicant: Textron Innovations Inc.

Inventor： Steven Ray Ivans ,  Brent Chadwick Ross

IPC: B64D7/06 ,  B64D7/08 ,  B64D9/00 ,  B64C29/02

Abstract: A cargo transporting system for a tailsitter aircraft includes a cargo receptacle rotatably coupled to an underside of a wing and a cargo assembly selectively coupled to the cargo receptacle. By rotating the cargo receptacle, the cargo transporting system can transition between a deployed position and a retracted position. In the deployed position, the cargo receptacle is substantially perpendicular to the wing, and accommodates ground personnel charged with connecting or removing the cargo assembly from the cargo transporting system. In the retracted position, the cargo receptacle is substantially parallel to the wing, and positioned for flight operations.

公开(公告)号：US20220074722A1

公开(公告)日：2022-03-10

申请号：US17328107

申请日：2021-05-24

Applicant: Raytheon Company

Inventor： Robert A. Bailey ,  James T. Erdmann ,  Stephen A. Streib ,  Armando Guerrero ,  Roy P. Mcmahon ,  Jessica R. Deherdt

IPC: F42B39/28 ,  B64D1/04 ,  B64D7/08 ,  F41G7/00

Abstract: A munitions rack includes a munitions rack structure that houses multiple compact ejectors. The structure includes a pair of internal longitudinal ribs, inboard of a pair of external longitudinal ribs. A spine of the munitions rack structure links all the ribs, and the munitions rack structure may be formed out of a single piece of material. The ribs define a pair of side recesses on the port and starboard sides of the bomb, which each may be further subdivided into a forward pocket and an aft pocket. Removable ejectors are located in the pockets. The ejectors may receive pressurized gas from pressurized gas source(s) located outside of the ejectors. The ejectors may each have multiple forward pistons and multiple aft pistons. The ejectors may include pitch control valving to control the relative amounts of pressurized gas sent to the forward piston(s) and aft piston(s).

公开(公告)号：US20200010195A1

公开(公告)日：2020-01-09

申请号：US16470429

申请日：2017-12-27

Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.

Inventor： Yoav Herzig ,  Daniel Marom

IPC: B64D1/06 ,  B64D9/00 ,  B64C1/26 ,  B64D7/08

Abstract: An aircraft pylon is provided, configured for mounting to the underside of an aircraft wing projecting from a fuselage and for carrying an external payload suspended therefrom. The pylon comprises an attachment mechanism configured for facilitating mounting of the pylon to the aircraft wing, and a carrying arrangement configured for carrying the payload and being pivotally articulated to the attachment mechanism. The pylon is configured to selectively pivot the carrying arrangement about a pylon axis between a vertical position in which it is suspended in a substantially vertical orientation, and a tilted position in which it is tilted toward the fuselage.

公开(公告)号：US20180362163A1

公开(公告)日：2018-12-20

申请号：US15736813

申请日：2016-06-21

Applicant: BAE Systems plc

Inventor： Andrew Charles White

IPC: B64D1/10 ,  B64D1/06 ,  B64D7/08

CPC classification number: B64D1/10 ,  B64D1/02 ,  B64D1/06 ,  B64D7/08

Abstract: An aircraft (2) comprising a launch tube (14) extending along at least part of a length of a wing of the aircraft (2),and through which an item (24) may be launched from the aircraft (2). The launch tube (14) comprises an opening (22) at a distal end of the wing (6).

公开(公告)号：US09180967B2

公开(公告)日：2015-11-10

申请号：US13407692

申请日：2012-02-28

Applicant: Ryan Binkholder ,  John K. Foster

Inventor： Ryan Binkholder ,  John K. Foster

IPC: B64D7/08 ,  F41F3/065

CPC classification number: B64D7/08 ,  F41F3/065

Abstract: In one embodiment there is provided a radar signature and induced aerodynamic drag minimizing, externally mountable, internally configurable pod structure optimized for internal placement of one or more deployable stores through configuration and optimal kinematic operation of a pod door assembly. The pod structure has an externally mountable pod housing, a predetermined pod housing cross-sectional configuration optimized to provide a configurable interior volume accommodating multiple different store configurations, and a predetermined pod housing configuration having a cross-sectional configuration optimized to minimize a radar signature and an induced aerodynamic drag. The pod structure further has a pod door assembly integral with the pod housing and having a plurality of pod doors and one or more seal door mechanism assemblies. The pod structure is optimized in kinematic operational combination of the pod doors and seal door mechanism assemblies controlling ejection launch envelopes.

Abstract translation: 在一个实施例中，提供了通过配置和荚式门组件的最佳运动学操作优化用于内部放置一个或多个可部署商店的雷达签名和感应空气动力学阻力最小化的可外部安装的内部可配置荚结构。 荚结构具有可外部安装的荚壳体，其经过优化以提供容纳多个不同储存结构的可配置内部容积的预定荚壳体横截面构型，以及具有优化以最小化雷达标记的横截面构型的预定荚壳体构型， 诱发气动阻力。 荚结构还具有与荚壳体一体的荚门组件，并具有多个荚门和一个或多个密封门机构组件。 荚结构在荚果门的运动学操作组合和控制喷射发射信封的密封门机构组件的优化。

公开(公告)号：US09055886B1

公开(公告)日：2015-06-16

申请号：US13336146

申请日：2011-12-23

Applicant: Justin Garretson ,  Clinton G. Hobart ,  Thomas S. Gladwell ,  Mark J. Monda

Inventor： Justin Garretson ,  Clinton G. Hobart ,  Thomas S. Gladwell ,  Mark J. Monda

IPC: G01N23/20 ,  A61B6/08 ,  G01N23/203 ,  H01J37/304 ,  F41F3/04 ,  G01V5/00 ,  F41C27/06 ,  G01N23/10 ,  B64D7/08

CPC classification number: A61B6/08 ,  A61B6/04 ,  A61B6/483 ,  B64D7/08 ,  F41C27/06 ,  F41F3/04 ,  F41H11/136 ,  F42B30/00 ,  G01N23/10 ,  G01N23/20 ,  G01N23/203 ,  G01V5/0025 ,  H01J37/3045

Abstract: Technologies pertaining to backscatter x-ray scanning systems are described herein. The backscatter x-ray scanning system includes an x-ray source, which directs collimated x-rays along a plurality of output vectors towards a target. A detector detects diffusely reflected x-rays subsequent to respective collimated x-rays impacting the target, and outputs signals indicative of parameters of the detected x-rays. An image processing system generates an x-ray image based upon parameters of the detected x-rays, wherein each pixel in the image corresponds to a respective output vector. A user selects a particular portion of the image, and a tool is positioned such that its directional axis is coincident with the output vector corresponding to at least one pixel in the portion of the image.

Abstract translation: 本文描述了与背散射X射线扫描系统有关的技术。 反向散射X射线扫描系统包括一个x射线源，它将沿着多个输出向量的准直X射线引向目标。 检测器检测在对准目标物的相应准直X射线之后的漫反射x射线，并且输出表示检测到的x射线的参数的信号。 图像处理系统基于检测到的x射线的参数生成X射线图像，其中图像中的每个像素对应于相应的输出矢量。 用户选择图像的特定部分，并且工具被定位成使得其方向轴与对应于图像的该部分中的至少一个像素的输出向量重合。

公开(公告)号：US07137599B1

公开(公告)日：2006-11-21

申请号：US10832209

申请日：2004-04-26

Applicant: Richard Lee Sitzmann ,  Gregory Alan Wilkinson

Inventor： Richard Lee Sitzmann ,  Gregory Alan Wilkinson

IPC: B64D7/08 ,  B64D1/04

CPC classification number: B64D7/08

Abstract: A system and method for interconnecting analog legacy stores to both legacy and modern aircraft. One aspect of the invention provides for a dual mode launcher having a first interface for interfacing with a modern aircraft and a second interface for interfacing with a legacy aircraft. Either the first or the second interface is connected to the aircraft depending on the hardware platform supported by the aircraft. Signals received from either interface are converted to digital and placed on a digital input/output bus and converted to analog for use by the store. Likewise, signals transmitted by the store to the aircraft are converted to digital and placed on the digital input/output bus for transmission to the aircraft. The signals are further acted upon depending upon which interface is connected to the dual mode launcher assembly. The dual mode launcher provides seamless operation of the store interface regardless of which type of aircraft is equipped to carry the analog store.

Abstract translation: 将模拟传统商店与传统和现代飞机相互连接的系统和方法。 本发明的一个方面提供了具有用于与现代飞行器接口的第一接口和用于与传统飞行器接口的第二接口的双模式发射器。 第一或第二接口根据飞机支持的硬件平台连接到飞行器。 从任一接口接收到的信号都将转换为数字信号，并放置在数字输入/输出总线上，并转换为模拟供商店使用。 类似地，由商店发送到飞行器的信号被转换成数字信号并放置在数字输入/输出总线上以便传输到飞行器。 根据哪个接口连接到双模式发射器组件，信号进一步作用。 双模式启动器提供商店界面的无缝操作，而不管哪种类型的飞机装备有模拟商店。

公开(公告)号：US5831200A

公开(公告)日：1998-11-03

申请号：US780277

申请日：1997-01-09

Applicant: Peter Gerd Fisch

Inventor： Peter Gerd Fisch

IPC: B64D7/08 ,  F42B15/00 ,  F41F5/00 ,  F41F7/00

CPC classification number: F42B15/00 ,  B64D7/08

Abstract: A hanger of steel for guiding a missile in a launcher has arcuate flanges matching the shape of the missile an a guiding element of substantially T-shaped cross section. A longitudinal recess is defined on the outer side of the transverse bar of the "T". The surfaces of the transverse bar facing the flanges define rest surfaces and the adjacent lateral surfaces of the vertikal bar of the "T" serve as lateral guiding surfaces for the missile. A longitudinal, rounded recess is provided between each of the lateral surfaces and the adjacent rest surface, in order to increase the notch radius. The surface of the material is treated to generate internal compressive stress in the regions of the recesses.

Abstract translation: 用于在发射器中引导导弹的钢吊架具有与导弹的形状匹配的弧形法兰，具有基本上T形横截面的引导元件。 纵向凹槽限定在“T”横向杆的外侧。 面向凸缘的横向杆的表面限定了搁置表面，“T”的垂直杆的相邻侧面用作导弹的侧向引导表面。 为了增加切口半径，在每个侧表面和相邻的搁置表面之间提供纵向圆形凹槽。 处理材料的表面以在凹部的区域中产生内部压缩应力。

公开(公告)号：US5465212A

公开(公告)日：1995-11-07

申请号：US173601

申请日：1993-12-23

Applicant: Donald W. Fowler ,  Nicholas D. Lappos ,  Joan A. Edwards

Inventor： Donald W. Fowler ,  Nicholas D. Lappos ,  Joan A. Edwards

IPC: B64C13/18 ,  B64C27/57 ,  B64D7/08 ,  F41G5/18 ,  F41G9/00 ,  G05D1/08 ,  B64C11/34 ,  B64C11/18 ,  B64C11/30

CPC classification number: F41G7/007 ,  F41G5/18 ,  F41G9/002 ,  G05D1/085

Abstract: An integrated fire and flight control (IFFC) system determines a ballistic firing solution based on the position of targets relative to a helicopter and also based on the type of weapons to be fired. An elevation command is determined based on the required change in helicopter attitude to achieve the ballistic firing solution that, combined with the estimated time required to perform the aim and release of weapons, provides an estimate of deceleration and velocity loss that will occur. A forward acceleration and velocity profile is determined based on the desire to make a symmetrical maneuver sequence involving a nose down acceleration to achieve the acceleration and velocity profile that will be canceled by the subsequent deceleration and velocity loss during the pitch up maneuver to the ballistic firing solution. The forward acceleration and velocity profile is used to provide a pilot with a forward acceleration command that directs the pilot to fly a nose down attitude until the required forward acceleration and velocity profile is achieved. Alternatively, the acceleration profile is coupled to a flight control wherein a pre-launch maneuver feedforward command signal is summed with a side arm controller control command signal as the primary input to a rotor mixing function and a pre-launch commanded rate signal is summed with a side arm controller commanded rate signal to provide the primary input to an automatic flight control system, to thereby automatically control the aircraft to assume an attitude necessary to achieve the desired forward acceleration and velocity profile. A terminal phase maneuver is calculated to thereby return the aircraft to the previous attitude, velocity hold, hover hold or position hold condition prior to commencement of the pre-launch maneuver.

Abstract translation: 一个综合的火力和飞行控制系统（IFFC）系统根据目标相对于直升机的位置，并根据要被射击的武器类型，确定弹道射击解决方案。 根据直升机态度所需的改变来确定升降指令，以实现弹道射击解决方案，结合执行武器目标和释放所需的估计时间，提供将会发生的减速和速度损失的估计。 根据期望制作一个涉及下降加速度的对称机动序列来达到加速度和速度分布的速度曲线，该速度曲线将被随后的加速和速度损失所消除，在加速和加速时， 解。 前进加速度和速度分布用于为飞行员提供一个前进加速指令，指导飞行员飞行下降姿态，直到达到所需的正向加速度和速度曲线。 或者，加速度曲线被耦合到飞行控制，其中预发射机动前馈指令信号与侧臂控制器控制命令信号相加，作为转子混合功能的主要输入，并且预发射命令速率信号与 侧臂控制器命令速率信号以向主动输入提供自动飞行控制系统，从而自动控制飞机采取所需的姿态以达到所需的正向加速度和速度曲线。 计算终端阶段机动，从而使飞机返回到先前的姿态，速度保持，悬停保持或位置保持状态，然后再启动前的动作。