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公开(公告)号:US20040211862A1
公开(公告)日:2004-10-28
申请号:US10423187
申请日:2003-04-25
Inventor: Daryl B. Elam
IPC: B64D041/00
CPC classification number: A63H27/02 , B64C39/024 , B64C2201/046 , B64C2201/048 , B64C2201/104 , B64C2201/126 , B64C2201/127 , B64C2201/146 , B64C2201/167 , B64D27/24 , Y02T50/44 , Y02T50/62
Abstract: An unmanned aerial vehicle, such as a remotely-piloted airplane, includes lift-producing wings that have batteries embedded or otherwise located within them. Locating the batteries within the wings allows more efficient use of the interior space of the unmanned vehicle. Space within a fuselage of the vehicle, which would otherwise be used for batteries, may be used for other components. Alternatively, fuselage, weight and/or size of the unmanned aerial vehicle may be reduced. In addition, locating the batteries within the wings may provide better structural performance of the wings, and/or may allow characteristics of the wings, such as inertia and moments, to be optimized.
Abstract translation: 诸如遥控飞机的无人驾驶飞行器包括具有嵌入或以其他方式位于其中的电池的升降机翼。 将电池放置在机翼内可以更有效地利用无人驾驶车辆的内部空间。 车辆的机身中的空间,否则将用于电池,可用于其他部件。 或者,可以减少无人驾驶飞行器的机身,重量和/或尺寸。 此外,将电池定位在机翼内可以提供更好的机翼的结构性能,和/或可以允许优化机翼的特性,例如惯性和力矩。
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公开(公告)号:US20030025034A1
公开(公告)日:2003-02-06
申请号:US10189796
申请日:2002-07-03
Inventor: Yutaka Akahori
IPC: B64B001/02 , B64B001/06
CPC classification number: G08G5/0052 , B64B1/06 , B64C39/024 , B64C2201/022 , B64C2201/042 , B64C2201/048 , B64C2201/101 , B64C2201/122 , B64C2201/141 , B64C2201/146 , B64C2201/165 , B64C2201/167 , B64F1/18 , G01S5/20 , G01S5/22 , G05D1/0202 , G08G5/00 , G08G5/0013
Abstract: An airship system according to the invention has an airship (110), a base station (120), and at least three measurement points. The airship (110) emits ultrasonic waves upon receiving an instruction from the base station (120). Measurement point units (S1-S3) receive the ultrasonic waves, and thereby measure distances from the airship (110) to the respective measurement points. An MPU that is incorporated in the base station (120) calculates a position of the airship (110). The base station (120) controls a route of the airship (110) based on the calculated position by sending a flight instruction to the airship (110). In this manner, an airship system can be provided that makes it unnecessary for an operator to pilot the airship and that can reduce the load weight and the power consumption of the airship.
Abstract translation: 根据本发明的飞艇系统具有飞艇(110),基站(120)和至少三个测量点。 飞艇(110)在接收到来自基站(120)的指令时发射超声波。 测量点单元(S1-S3)接收超声波,从而测量从飞艇(110)到相应测量点的距离。 并入基站(120)的MPU计算飞艇(110)的位置。 基站(120)通过向飞艇(110)发送飞行指令,基于计算出的位置来控制飞艇(110)的路线。 以这种方式,可以提供一种飞艇系统,使得飞行员不需要飞行飞艇,并且可以减少飞艇的负载重量和功率消耗。
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公开(公告)号:US5056737A
公开(公告)日:1991-10-15
申请号:US499809
申请日:1990-03-27
Applicant: Douglas R. Taylor
Inventor: Douglas R. Taylor
CPC classification number: B64C25/66 , B64C29/02 , B64C39/024 , B64F1/12 , B64C2201/048 , B64C2201/088 , B64C2201/104 , B64C2201/165 , B64C2201/167
Abstract: A vertical take-off and landing aircraft is configured so as to provide, when landing tail-first with its fuselage (1) in a generally vertical attitude, a touchdown area (21) at the tail of the aircraft at a position offset from a line extending along the length of the fuselage through the centre of gravity (23) of the aircraft such that after the touchdown area contacts a landing surface the aircraft topples under the action of gravity to bring an undercarriage (11, 13) of the aircraft into contact with the landing surface, thereby to attain a stable landed position.
Abstract translation: 垂直起飞和着陆飞机被配置为当其以机身(1)以大致垂直的姿态着陆尾部时,提供在飞行器尾部处的偏移的位置处的触地区域(21) 沿着机身的长度通过飞行器的重心(23)延伸,使得在着陆区域接触着陆表面之后,飞行器在重力作用下俯仰,使飞机的起落架(11,13)进入 与着陆面接触,从而达到稳定的着陆位置。
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公开(公告)号:US3703998A
公开(公告)日:1972-11-28
申请号:US3703998D
申请日:1970-12-28
Applicant: TELEDYNE RYAN AERONAUTICAL CO
Inventor: GIRARD PETER F
CPC classification number: B64C39/024 , B64C1/00 , B64C2001/0045 , B64C2201/048 , B64C2201/102 , B64C2201/121 , B64C2201/146 , B64C2201/162 , B64C2201/167
Abstract: A drone type aircraft having a telescopic fuselage and folding aerodynamic surfaces to facilitate installation in a limited capacity bomb bay or storage compartment of a launch aircraft. Prior to launch, the drone is lowered from the aircraft on a supporting frame, the aerodynamic surfaces are extended, and the nose section of the fuselage is extended. The added fuselage capacity is used as fuel tankage, which is filled from the launch aircraft to increase the operating range of the drone.
Abstract translation: 具有伸缩机身和折叠空气动力学表面的无人机型飞机,以便于安装在发射飞机的有限容量的炸弹舱或储藏室中。 在发射之前,无人机在支架上从飞机上下降,空气动力学表面延伸,机身的鼻部延伸。 增加的机身容量用作燃油箱,由发射机充满,以增加无人机的运行范围。
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