公开(公告)号：US08146855B2

公开(公告)日：2012-04-03

申请号：US12230638

申请日：2008-09-03

Applicant: Anvar Ismailov

Inventor： Anvar Ismailov

IPC: B64C3/56

CPC classification number: F42B10/64 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/121 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/208 ,  F42B10/14

Abstract: An unmanned air vehicle for military, land security and the like operations includes a fuselage provided with foldable wings having leading edge flaps and trailing edge ailerons which are operable during ascent from launch to control the flight pattern with the wings folded, the wings being deployed into an open unfolded position when appropriate. The vehicle is contained within a pod from which it is launched and a landing deck is provided to decelerate and arrest the vehicle upon its return to land.

Abstract translation: 用于军事，陆上安全等操作的无人驾驶飞行器包括设置有可折叠翼的机身，其具有前缘翼片和后缘副翼，其可以在发射时上升操作以控制翼折叠的飞行图案，翼部署成 在适当的时候打开展开位置。 车辆被容纳在发射的荚内，并且提供着陆甲板以在车辆返回陆地时减速和阻止车辆。

公开(公告)号：US20110233329A1

公开(公告)日：2011-09-29

申请号：US13037436

申请日：2011-03-01

Applicant: Brian Theodore McGeer ,  Robert Joseph Heavey, III ,  Damon Lucas McMillan ,  John William Stafford

Inventor： Brian Theodore McGeer ,  Robert Joseph Heavey, III ,  Damon Lucas McMillan ,  John William Stafford

IPC: B64F1/02 ,  B64D37/16 ,  B64D37/20

CPC classification number: B64F1/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/182 ,  B64D37/00 ,  B64F5/00

Abstract: An aircraft capable of thrust-borne flight can be automatically retrieved, serviced, and launched using equipment suitable for use on a small vessel, or at a base with similarly limited space or irregular motion. For retrieval, the aircraft drops a tether, and pulls the tether at low relative speed into contact with a horizontal guide. The tether is pulled across the guide until the guide is captured by a hook or other end effector. The tether length is then adjusted as necessary, and the aircraft swings on the guide to hang in an inverted position. Translation of the tether along the guide then brings the aircraft to a docking carriage, in which the aircraft parks for servicing. For launch the carriage is swung upright, the end effector is released from the guide, and the aircraft thrusts into free flight. A full ground-handling cycle can thus be accomplished automatically with simple and economical apparatus. It can be used with low risk of damage, and requires only moderate accuracy in manual or automatic flight control.

Abstract translation: 可以使用适合在小型船舶上使用的设备或具有类似有限空间或不规则运动的基座自动检索，维修和启动能够推力飞行的飞机。 为了检索，飞机坠落系绳，并以相对较低的速度牵引系绳与水平导轨接触。 将系绳拉过引导件，直到引导件被钩或其他端部执行器捕获。 然后根据需要调整系绳长度，并且飞机在引导件上摆动以悬在倒立的位置。 沿着导轨翻转系绳，然后将飞机带到对接车厢，飞机停在其中，以便维修。 为了发射，托架正直摆动，末端执行器从引导件释放，飞机起飞进入自由飞行。 因此，可以使用简单经济的装置自动完成全面的地面处理循环。 它可以使用低损害风险，并且在手动或自动飞行控制中只需要适度的准确性。

公开(公告)号：US20110150565A1

公开(公告)日：2011-06-23

申请号：US12928796

申请日：2010-12-16

Applicant: Itzhak Sapir

Inventor： Itzhak Sapir

IPC: F16B2/10

CPC classification number: B64F1/06 ,  B64C39/028 ,  B64C2201/084 ,  F41F3/052 ,  F42B39/22 ,  Y10T403/69

Abstract: The invention comprises a clamping mechanism comprising a first and second hinged retaining members for the receiving of a terminal member of a connecting rod. The terminal member is affixed within a retaining volume defined by the first and second hinged retaining members while in a closed first position when the clamping mechanism is disposed within a retaining structure.During a launch operation, a drive shaft urges the clamping mechanism forward of the retaining structure, permitting the retaining members to separate and releasing the retaining member. The connecting rod may be connected to and used to propel a micro-UAV or any other device, such as during a launch operation.

Abstract translation: 本发明包括夹持机构，该夹紧机构包括用于容纳连杆的端子构件的第一和第二铰接保持构件。 当夹持机构设置在保持结构内时，端子构件固定在由第一和第二铰接保持构件限定的保持空间中，同时处于闭合的第一位置。 在发射操作期间，驱动轴将夹持机构推向保持结构的前方，允许保持构件分离并释放保持构件。 连杆可以连接到并用于推动微型UAV或任何其他装置，例如在发射操作期间。

公开(公告)号：US20110011974A1

公开(公告)日：2011-01-20

申请号：US12893407

申请日：2010-09-29

Applicant: William R. McDonnell

Inventor： William R. McDonnell

IPC: B64F1/02

CPC classification number: B64F1/02 ,  B64C25/68 ,  B64C39/024 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/205 ,  B64D3/00 ,  B64F1/04 ,  B64F1/10

Abstract: A method of launching and retrieving a UAV (Unmanned Aerial Vehicle) (10). The preferred method of launch involves carrying the UAV (10) up to altitude using a parasail (8) similar to that used to carry tourists aloft. The UAV is dropped and picks up enough airspeed in the dive to perform a pull-up into level controlled flight. The preferred method of recovery is for the UAV to fly into and latch onto the parasail tow line (4) or cables hanging off the tow line and then be winched back down to the boat (2).

公开(公告)号：US20100123041A1

公开(公告)日：2010-05-20

申请号：US11856037

申请日：2007-09-15

Applicant: Michael L. Nair ,  John A. Condon

Inventor： Michael L. Nair ,  John A. Condon

IPC: B64F1/04 ,  F41B11/12

CPC classification number: B64F1/04 ,  B64C2201/084 ,  F41A21/18 ,  F41B11/62 ,  F41F1/00

Abstract: The launching of an unmanned projectile includes pre-packaging a barrel with a projectile, a pusher cup, and a gas generator. The gas generator generates gas to propel the projectile out of the barrel. A pressure chamber increases a pressure of the gas in the barrel. The pressure chamber comprises a front body portion connected to the gas generator; an aft body portion connected to the front body portion and the gas generator; and a vent sleeve positioned around the front body portion and adapted to provide an aperture through which the gas exits the barrel in order to control a level of gas pressure in the barrel. A triggering of the gas generator causes the pusher cup to push the projectile out of the barrel at a predetermined launch velocity in order to attain a predetermined self-propelled flight trajectory, wherein the triggering causes the pusher cup to exit the barrel.

Abstract translation: 发射无人射弹包括用弹丸预先包装桶，推杯和气体发生器。 气体发生器产生气体以将射弹推出枪​​管。 压力室增加了桶中气体的压力。 压力室包括连接到气体发生器的前主体部分; 连接到前主体部分和气体发生器的后体部分; 以及排气套，其定位在前主体部分周围并且适于提供孔，气体通过该孔离开筒体，以便控制桶中的气体压力水平。 气体发生器的触发导致推动器杯以预定的发射速度将射弹推出筒体，以便获得预定的自推进飞行轨迹，其中触发使推动杯离开枪管。

公开(公告)号：US20090308979A1

公开(公告)日：2009-12-17

申请号：US11992188

申请日：2005-11-30

Applicant: Ronen Nadir

Inventor： Ronen Nadir

IPC: B64D17/00

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/146 ,  B64C2201/185 ,  B64D17/80

Abstract: The disclosure provides a parachute release device which may include a connecting element capable of connecting to an aircraft and to a parachute and a locking mechanism capable of releasing the connecting element from the aircraft upon being actuated by an actuator, wherein the parachute may be connected to the connecting element by a multiplicity of points, wherein the locking mechanism is adapted to inhibit a force from being applied to the actuator and wherein the device may be suitable for use in small weights aircrafts due to its small size and weight. The disclosure further provides a method for releasing a parachute from an aircraft, the method may include activating an actuator capable of releasing a locking mechanism, wherein the locking mechanism is adapted to release a connecting element from an aircraft upon being actuated, wherein the connecting element is adapted to connect a parachute and wherein the locking mechanism is adapted to inhibit a force from being applied to the actuator.

Abstract translation: 本公开提供了一种降落伞释放装置，其可以包括能够连接到飞机和降落伞的连接元件，以及能够由致动器致动时能够从飞行器释放连接元件的锁定机构，其中降落伞可以连接到 所述连接元件由多个点组成，其中所述锁定机构适于阻止施加到所述致动器的力，并且其中所述装置由于其小的尺寸和重量而适合用于小型重量飞机。 本发明还提供了一种用于从飞行器释放降落伞的方法，所述方法可包括激活能够释放锁定机构的致动器，其中所述锁定机构适于在致动时从飞行器释放连接元件，其中所述连接元件 适于连接降落伞，并且其中所述锁定机构适于阻止施加在所述致动器上的力。

公开(公告)号：US20080203220A1

公开(公告)日：2008-08-28

申请号：US11679365

申请日：2007-02-27

Applicant: Patrick T. Hanzlick ,  Joshua J. Lange

Inventor： Patrick T. Hanzlick ,  Joshua J. Lange

IPC: B64F1/10

CPC classification number: B64F1/10 ,  B64C2201/084 ,  B64C2201/208

Abstract: The present invention discloses an aerial vehicle launching system, which may include a launch platform and a restraint system coupled to the launch platform. The restraint system has at least one passive restraint suitably adapted to indirectly restrain an aerial vehicle, where the restraint system is configured to coordinate the uniform retention and release of the passive restraint in order to launch the aerial vehicle.

Abstract translation: 本发明公开了一种飞行器发射系统，其可以包括发射平台和耦合到发射平台的约束系统。 约束系统具有适当地适应于间接限制飞行器的至少一个被动约束，其中约束系统被配置为协调被动约束的均匀保持和释放以便发射飞行器。

公开(公告)号：US20070252034A1

公开(公告)日：2007-11-01

申请号：US11603815

申请日：2006-11-21

Applicant: Brian McGeer ,  Andreas von Flotow ,  Cory Roeseler

Inventor： Brian McGeer ,  Andreas von Flotow ,  Cory Roeseler

IPC: B64F1/04

CPC classification number: B64F1/06 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/165

Abstract: Methods and apparatuses for launching unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be launched from an apparatus that includes a launch carriage that moves along a launch guide. The carriage can accelerate when portions of the carriage and/or the launch guide move relative to each other. A gripper carried by the launch carriage can have at least one grip portion in contact with the aircraft while the launch carriage accelerates along the launch axis. The at least one grip portion can move out of contact with the aircraft as the launch carriage decelerates, releasing the aircraft for takeoff. A brake can arrest the motion of the gripper after launch.

公开(公告)号：US20070228214A1

公开(公告)日：2007-10-04

申请号：US11235057

申请日：2005-09-26

Applicant: Dan Horak

Inventor： Dan Horak

IPC: B64F1/04

CPC classification number: B64C39/028 ,  A63H27/14 ,  B64C2201/044 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/182 ,  B64F1/04

Abstract: Autonomous micro air vehicles surveillance systems are provided. A MAV system of one embodiment includes an MAV and a launch pad. The MAV has an engine that is adapted to power the MAV. The launch pad has a starter that is adapted to start the engine in the MAV when the MAV is resting on a launching surface of the launch pad. The launch pad further has a battery to power the starter.

Abstract translation: 提供自动微型飞行器车辆监视系统。 一个实施例的MAV系统包括MAV和发射台。 MAV具有适用于为MAV供电的发动机。 发射台具有一个启动器，当MAV在发射台的发射表面上时，该启动器适于在MAV中启动发动机。 发射台还有一个电池为起动器供电。

公开(公告)号：US07152827B2

公开(公告)日：2006-12-26

申请号：US10759541

申请日：2004-01-16

Applicant: Brian T. McGeer

Inventor： Brian T. McGeer

IPC: B64C3/56

CPC classification number: B64F1/04 ,  B64C25/68 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/201 ,  B64C2201/205 ,  B64F1/02 ,  B64F1/06

Abstract: Methods and apparatuses for launching, capturing, and storing unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be assembled from a container with little or no manual engagement by an operator. The container can include a guide structure to control motion of the aircraft components. The aircraft can be launched from an apparatus that includes an extendable boom. The boom can be extended to deploy a recovery line to capture the aircraft in flight. The aircraft can then be returned to its launch platform, disassembled, and stored in the container, again with little or no direct manual contact between the operator and the aircraft.