| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 1 | 货运飞机 | CN200580047011.4 | 2005-11-22 | CN101102931A | 2008-01-09 | E·小埃洛 |
| 本发明涉及一种用于运载至少一个刚性集装箱飞机，包括一个横梁结构，以及附着横梁结构前部机身和附着横梁结构后端的尾部。机翼和发动机安装在横梁结构上，流线机身外壳产生的机舱能够接收标准尺寸的联合运输集装箱。轻质并且具有刚性结构的联合运输集装箱放置在机舱内并牢固地固定在其中。横梁结构被设计用于飞机空载时支撑其飞行、起飞和降落着陆，但飞机载重时需要牢固地固定到横梁结构的集装箱提供附加的强度。所述的飞机被设计为无人驾驶飞机。 | ||||||
| 2 | 飞船系统 | CN02802310.2 | 2002-06-17 | CN1230350C | 2005-12-07 | 赤堀丰 |
| 本发明的飞船系统有飞船(110)、基站120、至少3个测定点。接收到来自基站(120)的指令的飞船(110)一旦发出超声波，便通过在测定点单元(S1～S3)接收超声波，测定至这3个测定点的距离，安装在基站(120)内的MPU算出飞船的位置。基站(120)根据该位置，将航行指令发送给飞船(110)，控制飞船(110)的航线。因此，能提供一种能不需要操作员的操作，同时能降低飞船的载重及功耗的飞船系统。 | ||||||
| 3 | 用于消雹降雨的遥控飞机及消雹降雨方法 | CN201710546418.6 | 2017-07-06 | CN107318546A | 2017-11-07 | 李晓东; 李文铎 |
| 本发明公开了一种用于消雹降雨的遥控飞机及消雹降雨方法，采用遥控飞机将碘化银撒播于云层中，安全性较好，空域管制相对较宽松，适应性强；将碘化银溶解于丙酮-酒精溶液，避免了氯酸铵的使用，减少污染，有更好的环保性；而且本发明中避免了使用爆炸品，更加安全，而且库存管理、运输管理、操作管理的管制宽松；机翼可折叠，便于存储、运输、操作，降低成本；含碘化银的丙酮-酒精溶液在喷气式发动机尾部喷管处燃烧，避免了对喷气式发动机的腐蚀，延长使用寿命。 | ||||||
| 4 | 一种适用于火箭推进的四旋翼飞行器 | CN201610641408.6 | 2016-08-08 | CN106184704A | 2016-12-07 | 韩潮; 李娴; 陈欢; 黎桪; 杨鹏斌 |
| 本发明公开了一种适用于火箭推进的四旋翼飞行器，该四旋翼飞行器包括有旋臂、机身架、旋臂展开锁定组件、主轴、支架组件、以及用于驱动螺旋桨转动的无刷电机。旋臂位于机身架的下方，机身架的上方是支架组件，四个无刷电机分别安装在旋臂和机身架的圆环端上，无刷电机的输出轴上安装螺旋桨，旋臂展开锁定组件与机身架固定安装，主轴安装在旋臂展开锁定组件上。本发明四旋翼飞行器在由火箭产生推力输送至指定高度位置后，搭载的四旋翼飞行器与火箭脱离，并自动展开至飞行状态，执行拍摄侦查等任务。由于四旋翼飞行器由火箭搭载，具有工作高度高，覆盖面积广，到达指定高度速度快等特点。 | ||||||
| 5 | 货运飞机 | CN200580047011.4 | 2005-11-22 | CN100491200C | 2009-05-27 | E·小埃洛 |
| 本发明涉及一种用于运载至少一个刚性集装箱飞机，包括一个横梁结构，以及附着横梁结构前部机身和附着横梁结构后端的尾部。机翼和发动机安装在横梁结构上，流线机身外壳产生的机舱能够接收标准尺寸的联合运输集装箱。轻质并且具有刚性结构的联合运输集装箱放置在机舱内并牢固地固定在其中。横梁结构被设计用于飞机空载时支撑其飞行、起飞和降落着陆，但飞机载重时需要牢固地固定到横梁结构的集装箱提供附加的强度。所述的飞机被设计为无人驾驶飞机。 | ||||||
| 6 | 飞船系统 | CN02802310.2 | 2002-06-17 | CN1464856A | 2003-12-31 | 赤堀丰 |
| 本发明的飞船系统有飞船(110)、基站120、至少3个测定点。接收到来自基站(120)的指令的飞船(110)一旦发出超声波，便通过在测定点单元(S1～S3)接收超声波，测定至这3个测定点的距离，安装在基站(120)内的MPU算出飞船的位置。基站(120)根据该位置，将航行指令发送给飞船(110)，控制飞船(110)的航线。因此，能提供一种能不需要操作员的操作，同时能降低飞船的载重及功耗的飞船系统。 | ||||||
| 7 | 飛行船システム | JP2003510336 | 2002-06-17 | JPWO2003004352A1 | 2004-10-21 | 赤堀 豊; 豊 赤堀 |
| 本発明の飛行船システムは、飛行船(110)と、基地局120と、少なくとも3つの測定点とを有する。基地局(120)からの指令を受けた飛行船(110)が超音波を発信すると、測定点ユニット(S1〜S3)にて超音波を受信することにより、これら3つの測定点までの距離を測定し、基地局(120)内に内蔵されたMPUが飛行船(110)の位置を算出する。この位置に応じて基地局(120)は飛行船(110)に対して航行指令を送信し、飛行船(110)の航路を制御する。これにより、オペレータの操船を不要にすることができるとともに、飛行船の搭載重量及び消費電力の低減が可能な飛行船システムを提供することができる。 | ||||||
| 8 | AIRCRAFT WITH VERTICAL TAKEOFF AND LANDING AND ITS OPERATING PROCESS | EP16831647.9 | 2016-12-16 | EP3390224A1 | 2018-10-24 | RAZVAN, Sabie |
| The invention relates to an aircraft with vertical takeoff and landing and its operation method. Aircraft with vertical takeoff and landing of aerodyne type according to the invention comprises a circular symmetrical aerodynamic body (1) having an internal stiffening platform (2) located on the chord of the aerodynamic profile and which supports the components of the aircraft, at least four vertical ducted propellers (3a), (3b), (3c), (3d) arranged symmetrically to the central vertical axis of the carrier body (1), but also to the predetemined flight axis and to the transverse axis of the carrier body (1), propellers (3a) and (3c) having the same rotational direction opposite to that of propellers (3b) and (3d) at least two horizontal ducted propellers (4) with opposite rotation directions located inside the carrier body or outside of it, placed parallel symmetrical with the predetermined flight axis and on both sides of it, vector nozzles (5), one for each horizontal propeller (4), which provides vector orientation to jets of the horizontal ducted propellers (4), the means of power supply (6), which are designed to provide electricity necessary to operate all engines and all electrical and electronic devices on board, an electronic control and management flight module (7) and a landing gear (9), which aims to promote contact between the aircraft and the ground. | ||||||
| 9 | UNMANNED AIR VEHICULES AND METHOD OF LANDING SAME | EP05759026.7 | 2005-07-06 | EP1784331A1 | 2007-05-16 | SIRKIS, Omri |
| There is provided an Unmanned Air Vehicule (uav) (2) including an engine (4) and an airframe (6), including means for performing a deep stall maneouvre; at least one inflatable sleeve (12) connected or connectable to the airframe (6), and means for inflating the sleeve (12) during flight, wherein the inflated sleeve (12) extends along the lower side of the airframe (6) so as to protect same during deep stall landing. A method for operating an Unmanned Air Vehicle (UAV), including an engine and an airframe is also provided. | ||||||
| 10 | 展開可能な送信/受信モジュール装置を有するラムジェット付き無人航空ビークル | JP2017100925 | 2017-05-22 | JP2018020761A | 2018-02-08 | キム, イニョン ダニエル; ウィルソン, ライアン エス. |
| 【課題】超音速無人航空ビークルを用いたバイスタティック戦術レーダーの用途に関し、具体的には、格納された超音速巡航ポジションから、拡張された三角形状へと展開可能な送信/受信用アンテナを有する小型無人航空ビークル(UAV)を用いたシステムをする。 【解決手段】超音速巡航のためのラムジェットエンジンを有する無人航空ビークル(UAV)14を用いる。展開可能アンテナアームは、超音速巡航用の第1の格納ポジションを有し、エアブレーキとして機能し且つレーダー受信器のボアサイトアライメントを提供する、第2の拡張位置へと展開可能なように適合している。母機10は、レーダーパルスを送信するレーダー送信器を有し、通信データリンクが、UAVと戦術母機を操作可能に相互接続し、反射レーダーパルスをUAVレーダーアンテナでバイスタティック受信することによって生成されたデータを、母機に向けて送信する。 【選択図】図1 |
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| 11 | UNMANNED AERIAL VEHICLE WITH DEPLOYABLE ANTENNA ARMS | EP17155363.9 | 2017-02-09 | EP3248865A1 | 2017-11-29 | KIM, Inyoung Daniel; WILSON, Ryan S. |
A system for bistatic radar target detection employs an unmanned aerial vehicle (UAV) (14) having a ramjet engine (30) providing supersonic cruise of the UAV (14). Deployable antenna arms (22) support a passive radar receiver for bistatic reception of reflected radar pulses. The UAV (14) operates with a UAV flight profile in airspace beyond a radar range limit. The deployable antenna arms (22) have a first retracted position for supersonic cruise and are adapted for deployment to a second extended position acting as an airbrake and providing boresight alignment of the radar receiver. A mothership aircraft (10) has a radar transmitter for transmitting radar pulses and operates with an aircraft flight profile outside the radar range limit. A communications data link operably interconnects the UAV (14) and the tactical mothership aircraft (10), transmitting data produced by the bistatic reception of reflected radar pulses in the UAV radar antenna (46) to the mothership aircraft (10).
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| 12 | CARGO AIRCRAFT | EP05857018.5 | 2005-11-22 | EP1833721B1 | 2014-03-26 | Helou, Elie Jr. |
| In one embodiment, an aircraft for transporting at least one cargo container is disclosed. The aircraft comprises a forward fuselage, an empennage, a beam structure, and mounts to detachably and structurally engage the at least one cargo container with the beam structure. The beam structure is disposed between the forward fuselage and the empennage and the beam structure configured to receive the at least one cargo container. The beam structure and structurally engaged cargo container provide sufficient structural rigidity to support the aircraft in flight. | ||||||
| 13 | CARGO AIRCRAFT | EP05857018 | 2005-11-22 | EP1833721A4 | 2010-05-05 | HELOU ELIE JR |
| In one embodiment, an aircraft for transporting at least one cargo container is disclosed. The aircraft comprises a forward fuselage, an empennage, a beam structure, and mounts to detachably and structurally engage the at least one cargo container with the beam structure. The beam structure is disposed between the forward fuselage and the empennage and the beam structure configured to receive the at least one cargo container. The beam structure and structurally engaged cargo container provide sufficient structural rigidity to support the aircraft in flight. | ||||||
| 14 | UNMANNED AERIAL SYSTEMS | EP13845941 | 2013-07-25 | EP2879954A4 | 2016-07-27 | BYE GEORGE; BICKEL MATT |
| 15 | UNMANNED AERIAL SYSTEMS | EP13845941.7 | 2013-07-25 | EP2879954A2 | 2015-06-10 | BYE, George; BICKEL, Matt |
| The present invention provides an Unmanned Aircraft System, including an integrated unmanned aerial vehicle and all related components and subsystems that can be packaged and transported as a kit, and customized to fit desired mission profiles, and easily repaired by replacement of damaged components or subsystems. The present invention further provides unmanned aircraft system components and subsystems that facilitate low power and low noise operation, and extended flight times. | ||||||
| 16 | CARGO AIRCRAFT | EP05857018.5 | 2005-11-22 | EP1833721A2 | 2007-09-19 | Helou, Elie Jr. |
| In one embodiment, an aircraft for transporting at least one cargo container is disclosed. The aircraft comprises a forward fuselage, an empennage, a beam structure, and mounts to detachably and structurally engage the at least one cargo container with the beam structure. The beam structure is disposed between the forward fuselage and the empennage and the beam structure configured to receive the at least one cargo container. The beam structure and structurally engaged cargo container provide sufficient structural rigidity to support the aircraft in flight. | ||||||
| 17 | SYSTEM AND METHOD FOR REMOTE CONTROL OF INTERDICTION AIRCRAFT | EP05857551.5 | 2005-07-29 | EP1789315A2 | 2007-05-30 | Bernard, Charles W. |
| An aircraft attack interdiction system using an unmanned interdiction aircraft piloted using a remote control system. In-flight refueling system, weapons launcher systems and intelligence gathering equipment are mounted on the interdiction aircraft. A remote flight control operator to remotely fly the interdiction aircraft can be based on a remote flight control commander aircraft that can be flown at safe distances from targets that are attacked by the interdiction aircraft | ||||||
| 18 | 펼쳐질 수 있는 송신/수신 모듈 장치와 함께 램제트를 가진 무인항공기 | KR1020170025271 | 2017-02-27 | KR1020170134184A | 2017-12-06 | 인영다니엘킴; 라이언에스.윌슨 |
| 바이스태틱레이더타겟검출을위한시스템은 UAV(14)의초음속순항을제공하는램제트엔진(30)을갖는무인항공기(UAV)(14)를이용한다. 펼쳐질수 있는안테나아암들(22)은반사레이더펄스들의바이스태틱수신을위한패시브레이더수신기를지원한다. UAV(14)는레이더범위한계를넘는공역내의 UAV 비행프로파일을가지고동작한다. 펼쳐질수 있는안테나아암들(22)은초음속순항을위한제1 수축된포지션을갖고, 공기제동기로서작동하고레이더수신기의보어사이트정렬을제공하는제2 확장된포지션으로의펼침을위해적용된다. 모선항공기(10)는레이더펄스들을전송하기위한레이더송신기를가지고, 레이더범위한계밖의항공기비행프로파일을가지고동작한다. 통신데이터링크는 UAV(14)와전술모선항공기(10)를동작가능하게상호연결하고, UAV 레이더안테나(46)에서의반사레이더펄스들의바이스태틱수신에의해생성된데이터를모선항공기(10)에전송한다. | ||||||
| 19 | UNMANNED AERIAL VEHICLE WITH DEPLOYABLE TRANSMIT/RECEIVE MODULE APPARATUS WITH RAMJET | US15165663 | 2016-05-26 | US20170343645A1 | 2017-11-30 | Inyoung Daniel Kim; Ryan S. Wilson |
| A system for bistatic radar target detection employs an unmanned aerial vehicle (UAV) having a ramjet providing supersonic cruise of the UAV. Deployable antenna arms support a passive radar receiver for bistatic reception of reflected radar pulses. The UAV operates with a UAV flight profile in airspace beyond a radar range limit. The deployable antenna arms have a first retracted position for supersonic cruise and are adapted for deployment to a second extended position acting as an airbrake and providing boresight alignment of the radar receiver. A mothership aircraft has a radar transmitter for transmitting radar pulses and operates with an aircraft flight profile outside the radar range limit. A communications data link operably interconnects the UAV and the tactical mothership aircraft, transmitting data produced by the bistatic reception of reflected radar pulses in the UAV radar antenna to the mothership aircraft. | ||||||
| 20 | DRONE LAUNCH SYSTEMS AND METHODS | US14843329 | 2015-09-02 | US20170057635A1 | 2017-03-02 | James David Strayer |
| A drone launch system includes a canister defining an internal cavity, and a drone positioned within the internal cavity in a stowed state. The drone is configured to be ejected from the canister and transition from the stowed state into a deployed state outside of the canister. A method for launching a drone, the method includes positioning the drone in a stowed state in an internal cavity of a canister, ejecting the drone from the canister, and transitioning the drone into a deployed state after the ejecting operation. | ||||||
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