公开(公告)号：US20100237192A1

公开(公告)日：2010-09-23

申请号：US12406173

申请日：2009-03-18

Applicant: Terry M. Sanderson ,  Rudy A. Eisentraut ,  David B. Hatfield

Inventor： Terry M. Sanderson ,  Rudy A. Eisentraut ,  David B. Hatfield

IPC: B64C3/30 ,  B64C3/38

CPC classification number: B64C3/30 ,  B64C2201/102 ,  B64C2201/105 ,  F42B10/14 ,  F42B10/146 ,  F42B10/20

Abstract: A reinforced inflatable wing improves the tolerance of the OML and reinforces the wing in at least the high load areas. This approach provides fitment constrained air vehicles with wings having increased surface area to improve flight endurance or aerodynamic control. A wing box forms a first portion of the wing. A skin having a plurality of rigid plates affixed thereto is inflated to form a second portion of the wing to either increase the chord length or lengthen the wing span. The skin is suitably inflated with foam to form a solid wing.

Abstract translation: 增强的充气翼改善了OML的公差，并加强了至少在高负载区域中的机翼。 这种方法提供具有增加的表面面积的具有翼的装备受限的空中车辆，以改善飞行耐力或空气动力学控制。 翼盒形成翼的第一部分。 具有固定到其上的多个刚性板的皮肤被充气以形成机翼的第二部分，以增加弦长或延长机翼跨度。 皮肤适当地用泡沫充气以形成固体翼。

公开(公告)号：US20080149775A1

公开(公告)日：2008-06-26

申请号：US11645029

申请日：2006-12-26

Applicant: Storm Dunker ,  Martin Gilbert

Inventor： Storm Dunker ,  Martin Gilbert

IPC: B64D17/62

CPC classification number: B64D17/62 ,  B64C39/024 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/128 ,  B64C2201/145 ,  B64D17/34

Abstract: A deployment brake release system for use with an airborne guidance unit (AGU) of a parachute suitable for precision cargo delivery. The parachute includes deployment brake lines secured at one end to the edge of the canopy and connected at the other end through looped ends to motor control lines. The motor control lines are, in turn, engaged with the motor of the AGU. The deployment brake release system includes at least one hook mount having a hook secured to the AGU frame. The looped ends of the deployment brake lines are engaged with the hook during rigging so that, upon deployment, opening forces are applied to the hook mount rather than the motor. After full canopy inflation, the motor, via the motor control lines, pulls on the brake line looped ends to disengage them from the hook, transferring subsequent canopy loads to the AGU motor for the remainder of the flight. A method for releasing the deployment brake lines is also disclosed.

Abstract translation: 与用于精密货物运送的降落伞的空中引导单元（AGU）一起使用的部署制动器释放系统。 降落伞包括一端固定在顶盖边缘的部署制动线，另一端通过环形端连接到电机控制线。 马达控制线又与AGU的马达接合。 部署制动器释放系统包括至少一个钩安装件，其具有固定到AGU框架上的钩子。 在索具期间，展开制动管线的环形端部与钩接合，使得在展开时，打开力被施加到钩安装件而不是马达。 在全冠层膨胀后，电机通过电机控制线拉动制动线环路端部，将其从钩上脱离，将剩余的顶盖负载转移到AGU电机，以用于其余的飞行。 还公开了一种用于释放展开制动线的方法。

公开(公告)号：US06260797B1

公开(公告)日：2001-07-17

申请号：US09229599

申请日：1999-01-13

Applicant: Miles R. Palmer

Inventor： Miles R. Palmer

IPC: B64C356

CPC classification number: F42B15/00 ,  B64C39/024 ,  B64C2201/044 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/105 ,  B64C2201/121 ,  B64C2201/126 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/205 ,  B64D1/22 ,  B64D37/04 ,  B64D37/06 ,  B64D37/12 ,  B64D39/00

Abstract: A transformable gun launched aero vehicle having a ballistic projectile configuration and an aeroplane configuration includes a cylinder forming a shell of the vehicle in the ballistic projectile configuration and wings deployable from the cylinder. The wings are capable of achieving sufficient lift for sustained flight in the aeroplane configuration. The cylinder forms a fuselage of the vehicle in the aeroplane configuration. A wing includes plural rib elements, plural inflatable tubes where each tube is braced by the plural rib elements, and a wind shell disposed around the plural inflatable tubes and the plural rib elements. The vehicle includes an inflatable tail section that is inflated while the vehicle is in the aeroplane configuration. The vehicle includes a parachute that is reversibly deployable from a nose portion of the vehicle. The vehicle includes at least one landing rod. Each landing rod is reversibly extendable from the vehicle. A landing controller controls a first landing rod to extend after the vehicle has begun to vertically descend. The vehicle includes a folding propeller deployable from the fuselage in the aeroplane configuration. The vehicle includes a control system, and the control system includes a module to determine when the vehicle has reached a first predetermined state that defines an initiation of a transition from the ballistic projectile configuration to the aeroplane configuration.

Abstract translation: 可变形枪发射具有弹道射弹配置的航空车辆，并且飞机配置包括形成弹道射出构造的车辆壳体的气缸和从气缸展开的翼。 机翼能够在飞机配置中实现足够的升力以持续飞行。 汽缸在飞机配置中形成车辆的机身。 翼包括多个肋元件，多个可充气管，其中每个管由多个肋元件支撑，以及设置在多个可充气管和多个肋元件周围的风壳。 车辆包括在车辆处于飞机配置中时充气的可充气尾部。 车辆包括可从车辆的鼻部部分可逆地展开的降落伞。 车辆包括至少一个着陆杆。 每个着陆杆可从车辆可逆地延伸。 着陆控制器控制第一着陆杆在车辆开始垂直下降之后延伸。 该车辆包括在飞机配置中可从机身部署的折叠螺旋桨。 车辆包括控制系统，并且控制系统包括用于确定车辆何时已经达到第一预定状态的模块，该第一预定状态定义了从弹道射弹配置到飞机配置的转变的开始。

公开(公告)号：US08746620B1

公开(公告)日：2014-06-10

申请号：US13747626

申请日：2013-01-23

Applicant: Sunlight Photonics Inc.

Inventor： John Peter Moussouris ,  Sergey V. Frolov ,  Michael Cyrus

IPC: B64C3/30 ,  B64C1/34

CPC classification number: B64C1/34 ,  B64C3/30 ,  B64C3/46 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/105 ,  B64C2201/122 ,  B64D2211/00 ,  H01L31/0543 ,  H02S10/40 ,  H02S20/32 ,  Y02E10/52 ,  Y02T50/14

Abstract: Methods and apparatus for an adaptable solar airframe are provided herein. In some embodiments, an adaptable solar airframe includes a solar PV system having at least one solar tracking system and being able to follow the sun position in order to increase sunlight collection and power output; and an expandable body having an aerodynamic cross-section that minimizes parasitic air drag at any given thickness of the body, further being at least partially transparent to sunlight, further enclosing the solar PV system, and further being able to change its shape in response to changes in the positions of the solar PV system.

Abstract translation: 本文提供了适用于太阳能机身的方法和装置。 在一些实施例中，适应性太阳能机身包括具有至少一个太阳能跟踪系统并且能够跟随太阳位置以增加阳光收集和功率输出的太阳能PV系统; 以及具有空气动力学横截面的可膨胀体，该空气动力学横截面最小化在本体的任何给定厚度的寄生空气阻力，进一步包围太阳能光伏系统，并进一步包围太阳能光伏系统，并且还能够响应于 太阳能光伏系统的位置变化。

公开(公告)号：US08104713B2

公开(公告)日：2012-01-31

申请号：US12406173

申请日：2009-03-18

Applicant: Terry M. Sanderson ,  Rudy A. Eisentraut ,  David B. Hatfield

Inventor： Terry M. Sanderson ,  Rudy A. Eisentraut ,  David B. Hatfield

IPC: B64C3/54

CPC classification number: B64C3/30 ,  B64C2201/102 ,  B64C2201/105 ,  F42B10/14 ,  F42B10/146 ,  F42B10/20

Abstract: A reinforced inflatable wing improves the tolerance of the OML and reinforces the wing in at least the high load areas. This approach provides fitment constrained air vehicles with wings having increased surface area to improve flight endurance or aerodynamic control. A wing box forms a first portion of the wing. A skin having a plurality of rigid plates affixed thereto is inflated to form a second portion of the wing to either increase the chord length or lengthen the wing span. The skin is suitably inflated with foam to form a solid wing.

Abstract translation: 增强的充气翼改善了OML的公差，并加强了至少在高负载区域中的机翼。 这种方法提供具有增加的表面面积的具有翼的装备受限的空中车辆，以改善飞行耐力或空气动力学控制。 翼盒形成翼的第一部分。 具有固定到其上的多个刚性板的皮肤被充气以形成机翼的第二部分，以增加弦长或延长机翼跨度。 皮肤适当地用泡沫充气以形成固体翼。

公开(公告)号：US07377470B2

公开(公告)日：2008-05-27

申请号：US11252185

申请日：2005-10-18

Applicant: Haru Miyake

Inventor： Haru Miyake

IPC: B64C13/20

CPC classification number: B64C13/20 ,  A63H27/007 ,  A63H27/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/165

Abstract: A wireless-controlled airplane includes a flying unit and an on-ground controller which is connected to the flying unit through a communication section and flies the flying unit. The flying unit includes a body, a drive section installed on the body, a propulsion apparatus which generates a propulsive force when driven by the drive section, a main wing including a plurality of wing elements which are installed so as to be able to move with respect to each other, an opening and closing mechanism which changes the relative positions of the wing elements to change the effective area of the main wing, and a dropping apparatus which selectively holds and drops a load. By changing the effective area of the main wing, the flight speed can be changed, so the capacity and size of the drive section for rotating the propulsion apparatus can be decreased.

Abstract translation: 无线控制飞机包括飞行单元和地面控制器，其通过通信部分连接到飞行单元并飞行飞行单元。 飞行单元包括主体，安装在主体上的驱动部分，当由驱动部驱动时产生推进力的推进装置，包括多个翼元件的主翼，其安装成能够与 相对于彼此相对的改变主翼的有效面积而改变翼元件的相对位置的开闭机构，以及选择性地保持和降低载荷的下落装置。 通过改变主翼的有效面积，可以改变飞行速度，因此可以减小用于旋转推进装置的驱动部的容量和尺寸。

公开(公告)号：US07059566B2

公开(公告)日：2006-06-13

申请号：US10856360

申请日：2004-05-27

Applicant: David W. Byers ,  Gary A. Hall ,  Graham D. Hunter ,  Colen G. Kennell ,  Aleksander B. Macander ,  Judah H. Milgram ,  Jason D. Strickland

Inventor： David W. Byers ,  Gary A. Hall ,  Graham D. Hunter ,  Colen G. Kennell ,  Aleksander B. Macander ,  Judah H. Milgram ,  Jason D. Strickland

IPC: B64C1/00

CPC classification number: B64C1/068 ,  B64C1/061 ,  B64C1/22 ,  B64C3/58 ,  B64C29/02 ,  B64C31/02 ,  B64C39/024 ,  B64C2201/082 ,  B64C2201/084 ,  B64C2201/105 ,  B64C2201/128 ,  B64C2201/141 ,  B64C2201/185 ,  B64C2201/187 ,  B64D5/00

Abstract: A hollow elliptical-cylindrical hull conformingly houses a hollow rectangular-prismatic cabin whereby the four longitudinal parallel outside edges of the latter make contact with the inside surface of the former. The fully constructed aircraft (either non-powered or powered) includes the integral hull-plus-cabin structure along with nose, tail and airfoil structures that are coupled therewith. The cabin conformingly accommodates hollow rectangular-prismatic modules useful for cargo storage. While the nose and/or tail structure is uncoupled from the integral hull-plus-cabin structure, the modules are inserted into the cabin and the cabin is sealed. The aircraft is lifted (e.g., via airplane, helicopter, rocket or balloon) to a particular elevation and released, whereupon the two wings fully emerge and the aircraft effects controlled flight until reaching its destination. After landing, the nose and/or tail structure is uncoupled from the integral hull-plus-cabin structure, the cabin is unsealed, and the modules are removed from the cabin.

Abstract translation: 中空的椭圆柱形船体适合地容纳中空矩形棱柱舱，由此四个纵向平行的外边缘与前者的内表面接触。 完全构造的飞机（非动力或动力）包括一体的船体加舱结构以及与其结合的鼻，尾和翼型结构。 机舱适合容纳用于货物存储的中空矩形模块。 当鼻部和/或尾部结构与整体的船体 - 舱室结构脱离时，模块被插入到舱室中，舱室被密封。 飞机被提升（例如，通过飞机，直升机，火箭或气球）到特定的高度并被释放，于是两翼完全出现，并且飞机实现控制的飞行直到到达其目的地。 在着陆后，鼻部和/或尾部结构与整体式的船体 - 舱室结构脱离，舱室被开封，模块从舱室中取出。

公开(公告)号：US06676084B2

公开(公告)日：2004-01-13

申请号：US10168588

申请日：2002-06-24

Applicant: Jean Asseline ,  George De Noni

Inventor： Jean Asseline ,  George De Noni

IPC: B64D1734

CPC classification number: A63H27/08 ,  A63H30/04 ,  B64C2201/086 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/187 ,  Y10S244/902 ,  Y10S244/903

Abstract: A small radio controlled flying device propelled by a thermal engine (20) with pusher type airscrew (19) for remote sensing, the device being capable of short take-off and landing and flying at maximum speed of 35 Km/h. The device includes a pod and wings, the pod (1) being a rigid tricycle carriage dismountable by disengagement of substantially pyramidal jig with rear base (2) and front apex (7), lower plane (3), two lateral planes (4, 5) and an upper plane (6). The base is a welded one-piece element that includes the engine, the airscrew, a tank and the radio control. The apex is a welded one-piece element. The lower plane and the two lateral planes include spars (11, 12) assembled at the base and as the apex. The lower plane includes at its three end angles two rear wheels (8) and a front wheel (9), the front wheel being provided to protrude towards the front in the apex and the wheels being low pressure tires. The wings (13) are a caisson-type supple parachute and are connected to the pod in an adjustable fashion by two front slings (17), two braking slings (18) acting on the two flaps/ailerons.

Abstract translation: 由具有推进式螺旋桨（19）的热力发动机（20）推进的用于遥感的小型无线电控制飞行装置，该装置能够以35Km / h的最大速度短时起飞和着陆并飞行。 该装置包括荚和翼，荚（1）是刚性三轮车，可通过基本上棱锥形的夹具与后基部（2）和前顶点（7），下平面（3），两个侧平面（4， 5）和上平面（6）。 底座是焊接的单件元件，包括发动机，螺旋桨，油箱和无线电控制。 顶点是焊接的单件元件。 下平面和两个横向平面包括组装在基部和顶点的翼梁（11,12）。 下平面在其三个端角处包括两个后轮（8）和前轮（9），前轮设置成朝向顶点的前部突出，并且轮是低压轮胎。 机翼（13）是沉箱式柔软的降落伞，并且通过两个前吊索（17）和作用在两个翼片/副翼上的两个制动吊索（18）以可调节的方式连接到吊舱。

公开(公告)号：US20040004157A1

公开(公告)日：2004-01-08

申请号：US10296137

申请日：2003-06-30

Inventor： Lance A. Liotta

IPC: B64D027/00 ,  B64D029/00

CPC classification number: B64C39/066 ,  A63H27/00 ,  B64C39/028 ,  B64C2201/105 ,  B64C2201/107

Abstract: An aircraft which is designed for remote controlled slow flight, indoor or in a small outdoor yard or field. The aerial lifting body is defined by a series of lightweight planar or thin airfoil surfaces (A1, A2, A3, A4) arranged in a radially symmetrical configuration. Suspended within the cavity (O) formed by the thin airfoil surfaces (A1, A2, A3, A4) is a thrust generating propeller system (C) that is angled upwardly and that can be regulated remotely so as to change the angle of the thrust vector within the cavity (O) for steering. Lifting, stability, turning, and general control of the direction of motion in flight is accomplished without any formal wings, rudder, tail, or control surfaces.

Abstract translation: 一种专为遥控慢速飞行，室内或室外小型场地设计的飞机。 升降体由一系列以径向对称构造布置的轻型平面或薄型翼型表面（A1，A2，A3，A4）限定。 悬挂在由薄翼面（A1，A2，A3，A4）形成的空腔（O）内的是推力发生螺旋桨系统（C），其向上倾斜并且可以远程调节，以便改变推力角 在腔（O）内的向量用于转向。 飞行中的运动方向的提升，稳定性，转向和一般控制是在没有任何正式的机翼，方向舵，尾翼或控制面的情况下完成的。

公开(公告)号：WO2017178899A2

公开(公告)日：2017-10-19

申请号：PCT/IB2017/000883

申请日：2017-07-27

Applicant: ALSHDAIFAT, Wasfi

Inventor： ALSHDAIFAT, Wasfi

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/086 ,  B64C2201/105 ,  B64C2201/128 ,  B64C2201/162 ,  B64C2201/187

Abstract: A Multiple Task Aeroarrier (MTA) (20) with a semi-cuboid shape housing a two front ducted propellers (21) with their swinging mechanism (23) and outlet ducts (22) which are extending toward the rear side, rear ducted propellers (24) are installed inside the second half of two central ducts (25) from the back, these ducts are extending from the front and ending with swivel type nozzles (26). Two inflatable wings (27) are provided with stowing or retarding mechanisms. MTA (20) vertical take-off is initiated by swinging the front ducted propellers into vertical configuration, the rear swivel nozzles are turned into vertical position while the wings still stowed, at a suitable height, the wings are deployed, the front ducted propellers are swung horizontally while the rear swivel nozzles are positioned horizontally. For landing the front ducted propellers and swivel nozzles are swung vertically up, and the wings are stowed.

Abstract translation: 具有半长方体形状的多任务航空母板（MTA）（20），其容纳两个前导管螺旋桨（21），其具有摆动机构（23）和出口导管（22） 后侧导管螺旋桨24从后方安装在两个中央导管25的后半部分内，这些导管从前部延伸并以旋转式喷嘴26结束。 两个充气翼（27）设有收起或减速机构。 MTA（20）垂直起飞是通过将前导管螺旋桨摆动到垂直状态启动的，后部旋转喷嘴转入竖直位置，同时机翼仍然收起，在合适的高度上展开机翼，前导管螺旋桨 水平摆动，而后部旋转喷嘴水平放置。 为了着陆，前管道螺旋桨和旋转喷嘴垂直向上摆动，并且机翼被收起。