公开(公告)号：US20130277497A1

公开(公告)日：2013-10-24

申请号：US13450887

申请日：2012-04-19

Applicant: John Charles Jones ,  Artem Igorevich Grigoryev ,  Luis Carlos Espinosa

Inventor： John Charles Jones ,  Artem Igorevich Grigoryev ,  Luis Carlos Espinosa

IPC: B64F1/06 ,  B64F1/04

CPC classification number: B64F1/06 ,  B64C2201/084

Abstract: A man-portable unmanned aerial system launcher (UAS) launcher includes a rail assembly having an internal track and a carriage assembly having a base configured to translate within the internal track. The carriage assembly also includes a cradle configured to support a UAS and a bracket configured to support the cradle above the base. The UAS launcher includes a launch control system configured to secure the carriage assembly in the launch-ready position until the launch control system receives a launch signal. The UAS launcher also includes one or more elastic members configured to engage the carriage assembly and the rail assembly. Once the carriage assembly is translated to the launch-ready position, strain is applied to the carriage assembly by the one or more elastic members. Release of the carriage assembly enables force generated by strain of the elastic members to propel the carriage assembly toward a launch position.

Abstract translation: 便携式无人机系统发射器（UAS）发射器包括具有内部轨道的轨道组件和具有被配置为在内部轨道内平移的基座的滑架组件。 托架组件还包括支架，其构造成支撑UAS和支架，所述托架被构造成支撑在基座上方的托架。 UAS发射器包括发射控制系统，其配置成将支架组件固定在发射准备位置，直到发射控制系统接收到发射信号。 UAS发射器还包括一个或多个弹性构件，其构造成接合滑架组件和轨道组件。 一旦滑架组件被转换到发射就绪位置，则通过一个或多个弹性构件将应变施加到滑架组件。 托架组件的释放使得由弹性构件的应变产生的力能够将托架组件推向发射位置。

公开(公告)号：US08517306B2

公开(公告)日：2013-08-27

申请号：US11510920

申请日：2006-08-28

Applicant: William R. McDonnell ,  Charles H. Baker

Inventor： William R. McDonnell ,  Charles H. Baker

IPC: B64F1/02 ,  B64C25/68

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：US08336816B2

公开(公告)日：2012-12-25

申请号：US12582208

申请日：2009-10-20

Applicant: Stephen W. Miller

Inventor： Stephen W. Miller

IPC: B64F1/04

CPC classification number: B64F1/06 ,  B64C2201/021 ,  B64C2201/084

Abstract: An aircraft launcher includes a base frame, a first sliding frame that slides with respect to the base frame, a second sliding frame that slides with respect to the first sliding frame, an aircraft support located on the second sliding frame, and a drive apparatus adapted to slide at least one of the first sliding frame and the second sliding frame with respect to the base frame.

Abstract translation: 飞机发射器包括基架，相对于基架滑动的第一滑动框架，相对于第一滑动框架滑动的第二滑动框架，位于第二滑动框架上的飞行器支架，以及适于 相对于基架滑动第一滑动框架和第二滑动框架中的至少一个。

公开(公告)号：US08256705B2

公开(公告)日：2012-09-04

申请号：US12612227

申请日：2009-11-04

Applicant: Timothy D. Smith

Inventor： Timothy D. Smith

IPC: B64C15/00

CPC classification number: B64C39/064 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/084 ,  B64C2201/205

Abstract: A torque production vehicle includes a plenum body having a wall with a central port and a radial port formed within the wall, an impeller disposed within the plenum body to move air through the central port, an engine coupled to the impeller to rotate the impeller about an axis, at least one arm coupled to the plenum body, and a plurality of foils disposed in the radial port to direct air about the plenum body to provide a torque force about the plenum body.

Abstract translation: 扭矩生产车辆包括具有中心端口和形成在壁内的径向端口的壁的增压室，设置在增压室内的叶轮以将空气移动通过中心端口，发动机联接到叶轮以使叶轮围绕 一个轴线，至少一个连接到集气室主体的臂，以及设置在该径向端口中的多个箔，以引导围绕该增压室的空气以提供围绕该增压室的转矩力。

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。