公开(公告)号：US11982519B2

公开(公告)日：2024-05-14

申请号：US17753387

申请日：2020-08-20

Applicant: BAE SYSTEMS plc

Inventor： Andrew Michael Carr ,  Timothy Keith Girling ,  Murray Thomson

IPC: F42B12/36 ,  B63B22/00 ,  B63G1/00 ,  B64C39/02 ,  F42B10/56 ,  F42B15/10 ,  H04K3/00 ,  B63G6/00 ,  B63G9/00 ,  B64U70/00 ,  B64U101/20

CPC classification number: F42B12/365 ,  B63B22/003 ,  B63G1/00 ,  B64C39/024 ,  F42B10/56 ,  F42B15/10 ,  H04K3/62 ,  H04K3/825 ,  B63G6/00 ,  B63G2009/005 ,  B64U70/00 ,  B64U2101/20 ,  H04K2203/22

Abstract: According to a first aspect of the present invention, there is provided a reconnaissance and communication assembly, adapted to be launched from a gun barrel into the air over a body of water. The assembly comprises a carrier (with a cavity) and a payload (within the cavity). The payload is arranged to be controllably expelled from the carrier and once expelled from the carrier, the payload is adapted to enter the water; and the payload transmits a signal after entering the water.

公开(公告)号：US11796292B2

公开(公告)日：2023-10-24

申请号：US17927902

申请日：2022-02-15

Applicant: JIANGSU UNIVERSITY

Inventor： Yue Shen ,  Yicen Li ,  Dewei Wang ,  Xiuli Wang ,  Zhixiang Shi ,  Yayun Shen

IPC: F42B10/58 ,  F42B10/56 ,  F42B12/56 ,  B63C9/26

CPC classification number: F42B10/58 ,  B63C9/26 ,  F42B10/56 ,  F42B12/56

Abstract: In an intelligent multi-rotor rescue thrower, a throwing projectile head is located at a foremost end of the thrower, a parachute storage bin is mounted at a center of a front end of the throwing projectile head, a rear end of the throwing projectile head is connected to a projectile body shell through threads, and a first splitter plate, a second splitter plate, and a third splitter plate are directly connected to the projectile body shell through slide grooves built in the projectile body shell to equally divide a space in a cavity of the projectile body shell; connecting flanges tightly connect the projectile body shell to motors, a rotor is connected to an upper end of each of the motors, and three rotors are provided in the space in the cavity of the projectile body shell.

公开(公告)号：US20190137246A1

公开(公告)日：2019-05-09

申请号：US16091784

申请日：2017-04-04

Applicant: BAE SYSTEMS BOFORS AB

Inventor： Anders HAGBERG ,  Anders EKBERG ,  Tomas HULTGREN ,  Jonas LILJA ,  Olle NORRVI

IPC: F42B10/56 ,  B64D17/58 ,  B64D17/72 ,  B64D1/02 ,  F42B12/42

CPC classification number: F42B10/56 ,  B64D1/02 ,  B64D17/58 ,  B64D17/725 ,  F42B12/42

Abstract: A parachute device is provided for a divisible shell that includes an active body and a shell base. The parachute device includes two parachutes, a first, main parachute connected to the active body by parachute lines and a second parachute connected to the shell base.

公开(公告)号：US10071810B1

公开(公告)日：2018-09-11

申请号：US15876146

申请日：2018-01-20

Applicant: F. Richard Langner

Inventor： F. Richard Langner

IPC: F42B10/56 ,  F42B33/06 ,  B64D17/76 ,  F41F1/00

CPC classification number: B64D17/76 ,  F41F1/00 ,  F41H11/12 ,  F42B10/56 ,  F42B33/067

Abstract: Movement of a disrupter cannon is arrested by a parachute. The parachute is coupled (e.g., tethered) to the disrupter cannon. Prior to firing the cannon, the parachute is held in a retainer. Movement of the disrupter cannon in response to firing pulls the parachute from the retainer. The parachute deploys and arrests the movement of the disrupter cannon. The retainer protects the parachute prior to firing the disrupter cannon. The retainer may hold the parachute during transport.

公开(公告)号：US09234728B2

公开(公告)日：2016-01-12

申请号：US14075990

申请日：2013-11-08

Applicant: Lonestar Inventions, L.P.

Inventor： Osman Ersed Akcasu ,  Ibrahim Onur Uslu ,  Yusuf Leblebici

IPC: F42B12/36 ,  F42B10/56 ,  B64D17/00 ,  F42B30/00 ,  F42B5/02 ,  F42B10/50 ,  F42B12/58

CPC classification number: F42B12/365 ,  B64D17/00 ,  F42B5/025 ,  F42B10/50 ,  F42B10/56 ,  F42B12/58 ,  F42B30/006

Abstract: A modular reconnaissance capsule or reconnaissance pod is provided that is suitable for deployment by means of an artillery launching platform, such as a conventional 40 mm grenade launcher or 155 mm cannon wherein a parachute is deployed at a pre-calculated observation altitude, the parachute being designed to yield a sufficiently slow rate of descent to permit live video capture and transmission of images as forward observation information. Alternatively, pods according to the invention may also be air dropped from an aircraft, either piloted or pilotless, thus allowing the aircraft to operate at a safe distance and yet provide close reconnaissance even under a cloud cover. Accurate information about targeting dynamics is made available to the user through commercially available products. The invention complements other reconnaissance methods and provides easy-to-use real-time visual information for a desired area of interest.

Abstract translation: 提供了一种适用于通过火炮发射平台进行部署的模块化侦察舱或侦察舱，例如常规的40毫米榴弹发射器或155毫米炮，其中降落伞以预先计算的观测高度部署，降落伞为 旨在产生足够慢的下降速率，以允许实时视频捕获和图像传输作为前向观察信息。 或者，根据本发明的舱也可以是从飞行器空中飞行的，无论是驾驶员还是驾驶员，从而允许飞机在安全距离上操作，并且即使在云层下也提供近距离的侦察。 通过市售产品，可以向用户提供有关瞄准动态的准确信息。 本发明补充了其他侦察方法，并为所需感兴趣的领域提供了易于使用的实时视觉信息。

公开(公告)号：US20150128823A1

公开(公告)日：2015-05-14

申请号：US14075990

申请日：2013-11-08

Applicant: Lonestar Inventions, L.P.

Inventor： Osman Ersed Akcasu ,  Ibrahim Onur Uslu ,  Yusuf Leblebici

IPC: F42B12/36 ,  B64D17/00

CPC classification number: F42B12/365 ,  B64D17/00 ,  F42B5/025 ,  F42B10/50 ,  F42B10/56 ,  F42B12/58 ,  F42B30/006

Abstract: A modular reconnaissance capsule or reconnaissance pod is provided that is suitable for deployment by means of an artillery launching platform, such as a conventional 40 mm grenade launcher or 155 mm cannon wherein a parachute is deployed at a pre-calculated observation altitude, the parachute being designed to yield a sufficiently slow rate of descent to permit live video capture and transmission of images as forward observation information. Alternatively, pods according to the invention may also be air dropped from an aircraft, either piloted or pilotless, thus allowing the aircraft to operate at a safe distance and yet provide close reconnaissance even under a cloud cover. Accurate information about targeting dynamics is made available to the user through commercially available products. The invention complements other reconnaissance methods and provides easy-to-use real-time visual information for a desired area of interest.

Abstract translation: 提供了一种适用于通过火炮发射平台进行部署的模块化侦察舱或侦察舱，例如常规的40毫米榴弹发射器或155毫米炮，其中降落伞以预先计算的观测高度部署，降落伞为 旨在产生足够慢的下降速率，以允许实时视频捕获和图像传输作为前向观察信息。 或者，根据本发明的舱也可以是从飞行器空中飞行的，无论是驾驶员还是驾驶员，从而允许飞机在安全距离上操作，并且即使在云层下也提供近距离的侦察。 通过市售产品，可以向用户提供有关瞄准动态的准确信息。 本发明补充了其他侦察方法，并为所需感兴趣的领域提供了易于使用的实时视觉信息。

公开(公告)号：US20060049316A1

公开(公告)日：2006-03-09

申请号：US10525701

申请日：2003-08-20

Applicant: Sergey Antonenko ,  Sergey Belavskii

Inventor： Sergey Antonenko ,  Sergey Belavskii

IPC: B64G1/40

CPC classification number: F42B15/36 ,  B64G1/002 ,  B64G1/14 ,  F42B10/56 ,  F42B15/10

Abstract: The invention relates to the rocket and space engineering, and can find use in development of reusable rocket complexes for placing various space objects in orbit. A set of rocket boosters for operating launch vehicles comprises expendable and nonexpendable rocket boosters. A part of equipment of the expendable booster and a part of equipment of the nonexpendable boosters are replaceably mounted on said boosters and are capable to be interchangeable. A part of interchangeable equipment is made interconnected to another part of said equipment by at least a part of communications and structurally united into a module by a housing of a compartment of boosters. A method of operating launch vehicles comprises the steps of one-time using an expendable rocket booster within the launch vehicle, and reusing nonexpendable rocket boosters within the launch vehicles. There are the steps of periodical replacing a serviceable portion of the nonexpendable rocket booster (3, 4, 7) for a new one before repeated uses of the nonexpendable rocket booster, and mounting the replaced part onto the expendable rocket booster.

Abstract translation: 本发明涉及火箭和空间工程，并且可用于开发用于将各种空间物体放置在轨道中的可重复使用的火箭复合体。 一组用于运营运载火箭的火箭助推器包括消耗性和不可发射的火箭助推器。 消耗式助力器的一部分设备和非可扩展助力器的一部分设备可更换地安装在所述助力器上并能够互换。 可互换设备的一部分通过至少一部分通信与所述设备的另一部分互连，并且通过增压器隔室的壳体在结构上结合成模块。 操作运载火箭的方法包括在运载火箭内一次性使用消耗火箭助推器的步骤，以及在运载火箭中重新使用不可燃的火箭助推器。 在重复使用不可燃火箭助推器之前，将不可燃火箭助推器（3,4,7）的可维修部分定期替换为新的，并将更换的部件安装到消耗式火箭助推器上的步骤。

公开(公告)号：US06918340B2

公开(公告)日：2005-07-19

申请号：US10242742

申请日：2002-09-12

Applicant: Sami Daoud

Inventor： Sami Daoud

IPC: B60R21/26 ,  B60R21/264 ,  C06D5/06 ,  F42B3/04 ,  F42B10/56 ,  F42B12/60 ,  F42C19/08

CPC classification number: B60R21/2644 ,  B60R2021/2648 ,  C06D5/06 ,  F42B3/04 ,  F42B10/56 ,  F42B12/60

Abstract: This invention relates to a gas generator having two or more compartments, each with a separate initiator, with one compartment discharging before another, i.e., the compartments discharge sequentially. Each compartment has the same propellants, but the propellants have different geometries in each compartment, which results in different rates of gas evolution from each compartment. The gas generator has a rapid initial inflation, followed by a more gradual inflation rate in the subsequent stages, improving safety to occupants. One propellant used for the gas generator comprises (1) ammonium nitrate as the oxidizer, (2) a fuel such as CL-20. and (3) a binder such as polycaprolactone. A second propellant comprises by weight approximately 70-95% energetic nitrate fuel, 5-25% energetic polymer binder and 0.1-5% flash suppressant. No hot metal particles (e.g., CuO) are generated in the new systems.

Abstract translation: 本发明涉及一种具有两个或更多个隔室的气体发生器，每个隔室具有单独的起动器，一个隔室在另一个隔间之间排出，即隔间顺序地排出。 每个舱室具有相同的推进剂，但是推进剂在每个隔室中具有不同的几何形状，这导致从每个隔间不同的气体逸出速率。 气体发生器初期通货膨胀率快，其次是随后阶段通货膨胀率逐渐升高，改善了乘客的安全。 用于气体发生器的一种推进剂包括（1）硝酸铵作为氧化剂，（2）燃料如CL-20。 和（3）粘合剂如聚己内酯。 第二推进剂包括重量约70-95％的能量硝酸盐燃料，5-25％能量聚合物粘合剂和0.1-5％闪络抑制剂。 在新系统中不产生热金属颗粒（例如CuO）。

公开(公告)号：US06782829B1

公开(公告)日：2004-08-31

申请号：US10707307

申请日：2003-12-04

Applicant: Seungeuk Han ,  Raymond Trohanowsky ,  Andrew Ponikowski

Inventor： Seungeuk Han ,  Raymond Trohanowsky ,  Andrew Ponikowski

IPC: F42B1268

CPC classification number: F42B10/56

Abstract: A non-lethal cargo projectile includes a projectile body; a nose cap attached to a front of the projectile body; a boattail attached to a rear of the projectile body; a fin assembly including a boom attached to the boattail; a parachute assembly disposed in a front of the projectile body; a cable connecting the parachute assembly to the boattail; a fuze disposed in the boattail; a first pair of half cylinders disposed in the projectile body behind the parachute assembly; a first circular disc disposed at a front end of the first pair of half cylinders and a second circular disc disposed at a rear end of the first pair of half cylinders; a second pair of half cylinders disposed in the projectile body in front of the first circular disc enclose the parachute assembly; and a payload disposed in a space defined by the first pair of half cylinders and the first and second circular discs.

Abstract translation: 非致命的货物弹丸包括射弹体; 一个鼻盖附着在射弹身前; 附着在射弹体后部的火腿; 包括附接到火车头的吊杆的翼片组件; 设置在射弹体前部的降落伞组件; 将降落伞组件连接到火炬的电缆; 在火炬中的一个引信; 设置在降落伞组件后面的射弹体内的第一对半圆柱体; 设置在所述第一对半圆筒的前端的第一圆盘和设置在所述第一对半圆筒的后端的第二圆盘; 设置在第一圆盘前面的射弹体中的第二对半圆筒包围降落伞组件; 以及有效载荷，其设置在由所述第一对半圆筒和所述第一和第二圆盘限定的空间中。

公开(公告)号：US20030197095A1

公开(公告)日：2003-10-23

申请号：US10315466

申请日：2002-12-09

Inventor： Daniel Preston

IPC: B64D017/14 ,  B64D017/18 ,  B64D017/34

CPC classification number: F42B10/56 ,  B64D1/08 ,  B64D1/14 ,  B64D17/025 ,  B64D17/04 ,  B64D17/08 ,  B64D17/34 ,  B64D17/38 ,  B64D17/54 ,  B64D17/74 ,  F42B4/28 ,  F42B10/58 ,  G05D1/105

Abstract: An autonomous guided parachute system for cargo drops that divides the requirements of guidance and soft landing into separate parachutes. Said invention includes a high wing-loaded ram air parachute for guidance, a larger round parachute for soft landing, a harness/container system, flight computer, position sensors and actuation system. The system is dropped from an airplane. a predetermined period of drogue fall ensures a stable position prior to deploying the guidance parachute. The flight controller determines a heading to intersect with an area substantially above the desired target and controls the guidance parachute via pneumatic actuators connected to the parachutes steering lines to fly on that heading. At a minimum altitude prior to the systems impact with the ground the flight computer transitions the system from the fast high performance guidance parachute to a larger landing parachute by releasing the guidance parachute to static line extract and deploy the landing parachute. If the system reaches a position substantially above target area prior to the parachute transition altitude the flight computer controls the system into a spiral dive or other rapid altitude dropping maneuver until the transition altitude is reached. Once transitioned to the landing parachute the system descends for a brief period unguided under the landing parachute until touchdown.

Abstract translation: 货舱的自主引导降落伞系统，将引导和软着陆的要求分为单独的降落伞。 所述发明包括用于引导的高机翼加载式冲压空气降落伞，用于软着陆的较大圆形降落伞，线束/容器系统，飞行计算机，位置传感器和致动系统。 系统从飞机上掉下来。 预定时间的锥形落下在部署引导降落伞之前确保了稳定的位置。 飞行控制器确定与基本上高于期望目标的区域相交的航向，并通过连接到降落伞转向线的气动执行器在该航向上飞行来控制引导降落伞。 在系统撞击地面之前的最低高度，飞行计算机将系统从快速高性能指导降落伞转换到较大的降落伞，通过将引导降落伞释放到静态线路提取并部署着陆降落伞。 如果系统在降落伞转换高度之前达到大致高于目标区域的位置，飞行计算机将系统控制成螺旋式潜水或其他快速高度降落机动，直到达到过渡高度。 一旦过渡到着陆降落伞，该系统在登陆降落伞之前的短暂时间内下降直到达阵。