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：US20090294575A1

公开(公告)日：2009-12-03

申请号：US11840713

申请日：2007-08-17

Applicant: Adam N. Chu

Inventor： Adam N. Chu

IPC: B64B1/00

CPC classification number: B64D17/025 ,  B64C39/024 ,  B64C2201/022 ,  B64C2201/042 ,  B64C2201/185

Abstract: An orientation system is disclosed for a lighter-than-air aircraft having a lower stage suspended from an envelope. The orientation system includes a swivel and a plurality of thrust generators. The swivel is affixed between the envelope and the lower stage. The swivel is oriented for allowing the lower stage to rotate with respect to the envelope. The plurality of thrust generators are affixed to the lower stage. At least some of the trust generators generating differential thrust produces a change in rotation of the lower stage with respect to the envelope.

Abstract translation: 公开了一种具有从信封悬挂的较低级的轻型飞机的定向系统。 定向系统包括旋转件和多个推力发生器。 旋转体固定在信封和下层之间。 旋转件被定向成允许下阶段相对于外壳旋转。 多个推力发生器固定在下阶段。 产生差分推力的信任发生器中的至少一些相对于包络产生下阶段的旋转变化。

公开(公告)号：US06808144B1

公开(公告)日：2004-10-26

申请号：US10331009

申请日：2002-12-26

Applicant: Leland M. Nicolai ,  William R. Ramsey, Jr. ,  Douglas J. Robinson

Inventor： Leland M. Nicolai ,  William R. Ramsey, Jr. ,  Douglas J. Robinson

IPC: B64D1700

CPC classification number: G05D1/105 ,  B64C39/024 ,  B64C2201/104 ,  B64C2201/128 ,  B64C2201/141 ,  B64C2201/185 ,  B64C2201/187 ,  B64D17/025 ,  B64D17/343

Abstract: A parafoil recovery system capable of autonomously controlling the descent profile of a payload to a recovery area and maneuvering the parafoil to execute a soft landing in the recovery area is disclosed. A descent profile management system determines wind speed and direction, altitude, heading, and position of the payload based on sensor input. The descent profile management system also determines a gliding flight path profile from the launch point to the desired recovery area. A flare and stall maneuver is executed at the end of the landing sequence by braking the parafoil to slow the vertical descent speed and groundspeed for a soft landing. The pitch attitude of the payload can be adjusted by the descent profile management system to prevent nose-first impact with the ground. The parafoil canopy is released from the payload upon touchdown to prevent the canopy from dragging the payload on the ground after landing.

Abstract translation: 公开了一种能够自主地将有效载荷的下降曲线自动控制到恢复区域并操纵石灰石以在恢复区域中执行软着陆的石蜡回收系统。 下降轮廓管理系统基于传感器输入确定有效载荷的风速和方向，高度，航向和位置。 下降概况管理系统还确定从发射点到期望的恢复区域的滑翔飞行路径轮廓。 在着陆顺序结束时执行火炬和失速机动，通过制动铲车来减慢垂直下降速度和地面速度进行软着陆。 有效载荷的俯仰姿态可以通过下降轮廓管理系统进行调整，以防止与地面的鼻尖碰撞。 登陆时，Parafoil冠层从有效载荷中释放出来，以防止雨篷在着陆后拖动地面上的载荷。

公开(公告)号：US06626398B1

公开(公告)日：2003-09-30

申请号：US10143603

申请日：2002-05-10

Applicant: Beverly Cox ,  Hampton Dews ,  Nicholas Nyroth

Inventor： Beverly Cox ,  Hampton Dews ,  Nicholas Nyroth

IPC: B64C338

CPC classification number: B64C39/024 ,  B64C39/068 ,  B64C2201/104 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/185

Abstract: The present invention provides an unmanned airborne reconnaissance vehicle having a fuselage, a forward wing pair and a rearward wing pair vertically separated by a gap and staggered fore and aft therebetween such that a general biplane configuration is formed. The present invention provides a pair of wing tip plates for joining the wing tips of the forward and rearward wings. The unmanned airborne reconnaissance vehicle of the present invention includes a power plant to propel the vehicle through the air and a generally T-shaped tail having a vertical stabilizer including a rudder and a full span elevator.

Abstract translation: 本发明提供了一种无人机载侦察车辆，其具有机身，前翼对和后翼对，其间隔开间隔并在前后交错，从而形成一般的双翼面构型。 本发明提供了一对用于连接前翼和后翼的翼尖的翼尖板。 本发明的无人机载侦察车辆包括通过空气推动车辆的动力装置和具有垂直稳定器的大致T形的尾部，其包括舵和全跨越电梯。

公开(公告)号：US06576880B2

公开(公告)日：2003-06-10

申请号：US10150726

申请日：2002-05-17

Applicant: Richard T. Martorana ,  Jamie Anderson ,  Simon Mark Spearing ,  Seth Kessler ,  Brent Appleby ,  Edward Bergmann ,  Sean George ,  Steven Jacobson ,  Donald Fyler ,  Mark Drela ,  Gregory Kirkos ,  William McFarland, Jr.

Inventor： Richard T. Martorana ,  Jamie Anderson ,  Simon Mark Spearing ,  Seth Kessler ,  Brent Appleby ,  Edward Bergmann ,  Sean George ,  Steven Jacobson ,  Donald Fyler ,  Mark Drela ,  Gregory Kirkos ,  William McFarland, Jr.

IPC: B64C351

CPC classification number: F42B15/105 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/185 ,  B64C2201/201

Abstract: A flyer assembly is adapted for launching with, transit in, and deployment from an artillery shell having a central void region extending along a ballistic shell axis. The flyer assembly includes a jettisonable shroud and a flyer. The shroud extends along a shroud axis, and is positionable within the central void region with the shroud axis substantially parallel to the shell axis. The flyer is adapted to withstand a launch acceleration force along a flyer axis when in a first state, and to effect aerodynamic flight when in a second state. When in the first state, the flyer is positionable within the shroud with the flyer axis parallel to the shroud axis and the shell axis. The flyer includes a body member disposed about the flyer axis, and a foldable wing assembly mounted to the body member. The wing assembly is configurable in a folded state characterized by a plurality of nested wing segments when the flyer is in the first state. The wing assembly is configurable in an unfolded state characterized by a substantially uninterrupted aerodynamic surface when the flyer is in the second state. The flyer assembly is adapted to be launched from a ballistic delivery system such as an artillery cannon, and can thus reach a target quickly, without expending system energy stored within the flyer. During launch, the flyer is coupled to the shroud so as to maintain a portion of the flyer in tension during an acceleration of the flyer along the flyer axis resulting from the launch. The flyer assembly is adapted to withstand the high g-load and high temperature environments of a cannon launch, and can tolerate a set-back g load of about 16,000 g.

公开(公告)号：US20020066825A1

公开(公告)日：2002-06-06

申请号：US09884852

申请日：2001-06-18

Inventor： Carlos T. Miralles ,  Bart D. Hibbs

IPC: B64C003/56

CPC classification number: B64G1/222 ,  B64C1/30 ,  B64C3/56 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/148 ,  B64C2201/185 ,  B64C2201/203 ,  B64G1/105 ,  B64G1/62

Abstract: Disclosed is a spacecraft carrying a number of pods, each containing an aircraft that has been folded to fit in the pod. Each aircraft has a vertical stabilizer and outboard wing-portions that fold around fore-and-aft axes. Each aircraft also has a fuselage that folds around a lateral axis. The spacecraft releases one or more of the pods into an atmosphere. Each of the pods is configured with an ablative heat shield and parachutes to protect its aircraft when the pod descends through the atmosphere. The pod releases its aircraft at a desired altitude or location, and the aircraft unfolds while free-falling. The aircraft then acquires and follows a flight path, and activates scientific experiments and instruments that it carries. The aircraft relays results and readings from the experiments and instruments to the spacecraft, which in turn relays the results and readings to a mission command center.

Abstract translation: 公开了一种携带多个荚的飞船，每个荚都包含已折叠以适应荚的飞机。 每架飞机都有一个垂直的稳定器和外侧翼部分，它们围绕前后轴线折叠。 每架飞机还具有折叠横轴的机身。 航天器将一个或多个荚释放到气氛中。 每个荚配置有烧蚀式防护罩和降落伞，以在荚果通过大气层时保护其飞机。 吊舱将其飞机放置在所需的高度或位置，飞机在自由落体时展开。 飞机然后获得并遵循飞行路线，并激活它所携带的科学实验和仪器。 飞机将实验和仪器的结果和读数中继到航天器，然后将结果和读数中继到任务指挥中心。

公开(公告)号：US6144899A

公开(公告)日：2000-11-07

申请号：US410883

申请日：1999-10-04

Applicant: Michael L. Babb ,  Michael William Douglas ,  Davis M. Egle ,  Kenneth Wayne Howard

Inventor： Michael L. Babb ,  Michael William Douglas ,  Davis M. Egle ,  Kenneth Wayne Howard

IPC: B64C13/18 ,  B64C39/02 ,  B64D17/80 ,  G05D1/10 ,  B64D1/00

CPC classification number: G05D1/101 ,  B64C13/18 ,  B64C39/024 ,  B64D17/80 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/125 ,  B64C2201/141 ,  B64C2201/185 ,  B64C2201/187

Abstract: The recoverable airborne instrument platform accurately determines its present position and uses this data to execute a predetermined flight plan and ultimately guide its descent to a predetermined landing site. This is accomplished by installing the instrument package payload in the aerodynamic exterior housing of the recoverable airborne instrument platform, which has a plurality of moveable control surfaces thereon to autonomously control the altitude, attitude and flight path of the recoverable airborne instrument platform. A navigation circuit contained within the aerodynamic housing determines the geographic location of the recoverable airborne instrument platform as well as the location of at least one predetermined recovery site. The determined position data is used to dynamically calculate a flight path which allows the guidance control circuit to both execute a predetermined flight plan and controllably descend the recoverable instrument platform to a selected predetermined recovery site. Upon arrival at the selected predetermined recovery site, the recoverable airborne instrument platform descends to a predetermined height over the selected predetermined recovery site and activates a parachute release mechanism to controllably descend to the selected predetermined recovery site.

Abstract translation: 可恢复的机载仪表平台精确地确定其当前位置，并使用该数据执行预定的飞行计划，并最终指导其下降到预定的着陆点。 这是通过在可恢复的机载仪表平台的空气动力学外壳中安装仪器包装有效载荷来实现的，该平台在其上具有多个可移动的控制表面以自主地控制可恢复的机载仪表平台的高度，姿态和飞行路径。 包含在空气动力学壳体内的导航电路确定可恢复的机载仪表平台的地理位置以及至少一个预定的恢复位置的位置。 所确定的位置数据用于动态地计算飞行路径，其允许引导控制电路执行预定的飞行计划并且可控地将可恢复的仪器平台下降到所选择的预定恢复位置。 在到达所选择的预定恢复站点时，可恢复的机载仪表平台在所选择的预定恢复站点上下降到预定高度，并激活降落伞释放机构以可控地下降到所选择的预定恢复站点。

公开(公告)号：US4666105A

公开(公告)日：1987-05-19

申请号：US784484

申请日：1985-10-04

Applicant: Juergen Dellinger ,  Hans-Jochen Hoeppner ,  Ulrich Kraemer

Inventor： Juergen Dellinger ,  Hans-Jochen Hoeppner ,  Ulrich Kraemer

IPC: B64C39/02 ,  F42B15/36 ,  B64F1/04

CPC classification number: F42B15/36 ,  B64C39/024 ,  B64C2201/046 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/165 ,  B64C2201/185

Abstract: An unmanned craft having a fuselage, a propeller drive with a propeller being arranged in the tail portion of the fuselage for purposes of cruising, and a rocket assist propulsion system for the takeoff phase is releasably mounted to the fuselage, the improvement includes three spring biased thrust rods being secured to the frame and releasably engaging peripheral points of the craft. The thrust rods are radially pivotal in outer direction. Support points on the wings and the rudder engage front ends of the rods in contourmatching relationship but are disengageable therefrom.

Abstract translation: 具有机身的无人飞行器，具有推进器的螺旋桨驱动器布置在机身的尾部以用于巡航，并且用于起飞阶段的火箭辅助推进系统可释放地安装到机身，改进包括三个弹簧偏置 推杆被固定到框架并且可释放地接合工艺的外围点。 推力杆在外部方向上是径向枢转的。 机翼和方向舵上的支撑点以轮廓匹配关系与杆的前端接合，但是与其脱离接合。

公开(公告)号：US4408737A

公开(公告)日：1983-10-11

申请号：US280280

申请日：1981-07-06

Applicant: Hans Schwaerzler

Inventor： Hans Schwaerzler

IPC: B64D17/80

CPC classification number: B64D17/80 ,  B64C2201/185 ,  Y10S244/902

Abstract: A flying body such as an aircraft or a re-entry vehicle is enabled to land substantially horizontally with the aid of one or several glider parachutes also referred to as paragliders, which are stored in an upper body zone and ejected during the landing. The lift capacity of the paraglider is so dimensioned that it replaces the lift loss of the wings due to the low landing speed, whereby the weight of the flying body is kept in equilibrium to the sum of the wing lift and of the paraglider lift. The paraglider resistance or drag is compensated by the engine thrust and an ascending or descending flight is accomplished by modulating the engine thrust.

Abstract translation: 诸如飞机或重新进入车辆的飞行体能够借助一个或多个滑翔机降落伞也被称为滑翔伞基本上水平地落地，这些滑翔机降落伞被储存在上部身体区域中并在着陆期间弹出。 滑翔伞的提升能力的尺寸使其能够代替由于低着陆速度而引起的机翼的升力损失，由此飞行体的重量与机翼升力和滑翔机升力的总和保持平衡。 滑翔机的阻力或阻力由发动机推力补偿，上升或下降的飞行通过调节发动机推力来实现。

公开(公告)号：US4311290A

公开(公告)日：1982-01-19

申请号：US90205

申请日：1979-11-01

Applicant: Kenneth T. Koper

Inventor： Kenneth T. Koper

IPC: B64F1/02

CPC classification number: B64F1/02 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/182 ,  B64C2201/185

Abstract: Apparatus and method for recovering and arresting an aircraft or other vele. A boom is swivelly connected to a support structure via braking mechanism. The boom is pivotally connected to the brake mechanism such that it can also pivot in a second, different plane intersecting the plane of rotation of the brake mechanism. A shear pin prevents pivoting of the boom in the second plane until the boom has experienced a predetermined load in that plane. The distal end of the boom distant from the brake mechanism is provided with structure for engaging the aircraft. When the aircraft is flown at and captured by the boom, the weight and motion of the aircraft breaks the shear pin, causing the boom to move in the second plane until engaged by a stop. This rapid change in position of the engaging end of the boom in the second plane prevents the aircraft from pendulating about the boom. Forward motion of the aircraft also causes movement within the brake mechanism in the first plane which absorbs the kinetic energy of the aircraft as the boom swivels against the brake mechanism, so that the aircraft is slowed and arrested.

Abstract translation: 用于恢复和阻止飞机或其他车辆的装置和方法。 动臂通过制动机构旋转地连接到支撑结构。 吊杆枢转地连接到制动机构，使得其也可以在与制动机构的旋转平面相交的第二不同平面中枢转。 剪切销防止悬臂在第二平面中的枢转，直到悬臂在该平面中经历了预定的载荷。 离开制动机构的悬臂的远端设置有用于接合飞行器的结构。 当飞机飞行并被悬臂捕获时，飞行器的重量和运动会破坏剪切销，导致吊臂在第二平面中移动，直到停止。 在第二平面中，起重臂的接合端的这种快速变化防止飞机在吊杆周围摆动。 飞行器的前进运动也引起在第一平面内的制动机构内的运动，当悬臂靠在制动机构上转动时吸收飞行器的动能，从而使飞行器减慢和停止。