| 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 | 一种具有可倾转尾翼的飞行器及其控制方法 | CN201710202643.8 | 2017-03-30 | CN107010205A | 2017-08-04 | 翟剑豪; 孙媛; 张伟; 蔡海宁 |
| 本发明涉及一种具有可倾转尾翼的飞行器，属于航空系统技术。现如今国内外可以变体的飞机主要有倾转旋翼飞机V‑22“鱼鹰”，可变后掠翼飞机F‑14“雄猫”和一些尚处验证阶段的一些机翼可倾转的概念无人机等。这些飞机可作动的位置都是主机翼，现阶段尚无尾翼变体飞机方案。对于尾翼变体飞翼无人机来说最大的难点在于，飞机采用多舵面混合控制方式，可同时满足两种气动布局不同的气动要求，无论在V型尾翼状态还是在巡航状态都可以保持稳定的飞行。飞行器可以在起飞、降落和巡航状态下使用V型尾翼飞机布局提高飞机稳定性，在进入攻击区域转变成具有隐身功能的飞翼布局飞机执行打击任务。 | ||||||
| 2 | 一种隐身飞行器的火箭助推脱落顶窝 | CN201510835968.0 | 2015-11-25 | CN105366052A | 2016-03-02 | 孟令赛 |
| 本发明公开了一种隐身飞行器的火箭助推脱落顶窝，涉及航空技术领域。所述隐身飞行器的火箭助推脱落顶窝包含第一顶面(4)、第二顶面(7)、第一侧面(5)、第二侧面(8)及机身面(6)，其中，所述第一顶面(4)与第二顶面(7)相交形成顶边(47)，所述第一顶面(4)与机身面(6)相交形成第一侧顶边(46)，第一侧顶边(46)与第一前缘边(11)平行；所述第二顶面(7)与机身面(6)形成第二顶边(76)，第二顶边(76)与第二前缘边(12)平行；所述第一侧面(5)分别与第一顶面(4)及机身面(6)相交；所述第二侧面(8)分别与第二顶面(7)及机身面(6)相交。本发明的优点在于：增强了飞行器的隐身性能。 | ||||||
| 3 | 飞机及将有机电致发光板敷设在飞机外表面上的方法 | CN201610313052.3 | 2016-05-12 | CN105984578A | 2016-10-05 | 刘建言; 艾俊强; 王健 |
| 本发明公开了一种飞机及将有机电致发光板敷设在飞机外表面上的方法。所述飞机包括飞机主体(1)、机载动力装置以及有机电致发光板(2)，所述有机电致发光板(2)覆盖所述飞机主体外表面；所述有机电致发光板(2)与所述机载动力装置连接。采用这种结构，具有全固态显示、轻薄、亮度和对比度高、超低的能耗、响应速率快速(≤10μs)、视角宽，自发光、成本低、加工工艺简单以及发光效率高等优点。具有透明轻薄、柔软价廉、可塑性强、可弯曲折叠等特点，而且还具有类似于无机半导体型的导电性，可以制作出P‑N结。 | ||||||
| 4 | 飞翼布局隐身无人机的前缘载荷安装系统 | CN201710641173.5 | 2017-07-31 | CN107310739A | 2017-11-03 | 不公告发明人 |
| 本发明涉及无人机领域，具体涉及飞翼布局隐身无人机的前缘载荷安装系统，其目的在于解决隐身飞机由于载荷安装不便而无法反射雷达波的问题。飞翼布局隐身无人机的前缘载荷安装系统,包括设置在机翼前缘的内凹安装缺口、前梁、前缘尖劈和前缘载荷舱盖，前梁装在安装缺口的底部，前缘尖劈设置在前梁上并将前梁覆盖，前缘载荷舱盖装在前缘尖劈上且与机身圆滑过渡，前缘尖劈上设有用于安装载荷的安装孔，所述前缘尖劈为向外凸出的楔形，且与前缘载荷舱盖间形成V形空腔，所述前缘尖劈为导电材料，所述前缘载荷舱盖为透波材料。载荷系统具有搭载内置反射器的能力，可以模拟各种假想目标，且不影响气动外形。 | ||||||
| 5 | 一种可变飞行状态的侦打一体化高空无人机 | CN201610530935.X | 2016-07-07 | CN106081050A | 2016-11-09 | 聂万胜; 王迪; 杨新垒; 吴睿; 刘晓慧; 彭冠华; 苏凌宇; 何浩波; 侯志勇; 车学科; 石天一; 刘瑜 |
| 本发明公开了一种可变飞行状态的侦打一体化高空无人机，包括机体和动力系统；机体采用翼身融合体布局，机体由两个双向三角翼相互拼接形成一个类似菱形的气动外形；机体上表面呈凸起流线形，机体下表面呈光滑扁平状。两个双向三角翼为大小相等的两个等腰三角形，两个双向三角翼的底边相互拼接；动力系统设置在机体的拼接处，动力系统包括动力装置和升力装置；动力装置，用于实现超声速飞行状态与亚声速飞行状态之间的转换；升力装置，用于提供机体上升所需的升力。本发明能实现亚声速与超声速飞行状态转换、具有高机动性、最大飞行高度高的优点，能够作为一款具有持续威慑力和作战潜力的无人机投入使用。 | ||||||
| 6 | 一种低可探测性防空机器人 | CN201610297348.0 | 2016-05-09 | CN105856248A | 2016-08-17 | 不公告发明人 |
| 本发明提供一种低可探测性防空机器人，包括防护外壳顶盖、防护外壳本体等，所述的防护外壳顶盖铰接在防护外壳本体上部，所述的防护外壳顶盖在关闭后和防护外壳本体组成一个完成的防护外壳，所述的防护外壳为多面体结构，其内部为空心结构，防护外壳外采用碳纤维材质，并在其表面涂有可以吸收雷达波的材料。本发明自身携带空中侦查无人机，并可以利用无人机携带的相控阵雷达搜索目标，同时无人机也不容易被发现。 | ||||||
| 7 | Aircraft equipped with a spoiler only on the upper surface | JP2006514974 | 2004-05-26 | JP2006527124A | 2006-11-30 | ディー． クラーク，ウォルター |
| 【解決手段】航空機(10)は、後退翼(16)(18)及びスポイラ(30)(32)を具え、それらは後退翼の翼端近傍である上面(36)内に嵌められている。 航空機はまた、航空機の中央後部に形成された昇降舵(34)を有し、該昇降舵はスポイラの後部にある。 昇降舵信号について補助的な制御ができるのは後部であり、航空機の重力中心の後部にあって、上向き動作のみで、スポイラによって引き起こされる好ましくない上向きモーメントを打ち消す。 これらスポイラーの一方又は他方が、揚力をダンピングすることによる直接作用によって、そして翼が後退翼であることにより、偏揺れを横転に変換することによって、横転がなされる。 | ||||||
| 8 | Getarntes Fluggerät | EP12004166.0 | 2012-05-31 | EP2532588B1 | 2016-06-29 | Dornwald, Jochen; Bichler, Bartholomäus |
| 9 | AIRCRAFT WITH TOPSIDE ONLY SPOILERS | EP04809418.9 | 2004-05-26 | EP1631493A2 | 2006-03-08 | CLARK, Walter, D. |
| An aircraft (10) with swept back wings (16, 18) and spoilers (30,32) inlaid into the top surface (36) near the tips of the wings. The aircraft also includes an elevator (34) formed in the center back portion of the aircraft, which is also aft of the spoilers. It is aft to allow an auxiliary control in the elevator signal to cancel the unwanted pitch up moment caused by the spoilers only going up and being aft of the center of gravity of the aircraft. Roll is achieved with these spoilers by the direct action of the lift dumping on one side or the other and by taking advantage of the transformation of yaw into roll by the sweep back of the wings. | ||||||
| 10 | Getarntes Fluggerät | EP12004166.0 | 2012-05-31 | EP2532588A1 | 2012-12-12 | Dornwald, Jochen; Bichler, Bartholomäus |
Ein Fluggerät 10 mit geringer Radarsignatur weist eine erste Seite 12 auf, auf der Turbinenöffnung 14, 16 und Nutzlast- oder Fahrwerkschächte 20, 24, 26 angeordnet sind. Eine zweite Seite 30 des Fluggeräts ist derart ausgeführt, dass sie eine geringere Radarsignatur als die erste Seite 12 aufweist.
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| 11 | AIRCRAFT WITH TOPSIDE ONLY SPOILERS | EP04809418.9 | 2004-05-26 | EP1631493B1 | 2006-11-22 | CLARK, Walter, D. |
| An aircraft (10) with swept back wings (16, 18) and spoilers (30,32) inlaid into the top surface (36) near the tips of the wings. The aircraft also includes an elevator (34) formed in the center back portion of the aircraft, which is also aft of the spoilers. It is aft to allow an auxiliary control in the elevator signal to cancel the unwanted pitch up moment caused by the spoilers only going up and being aft of the center of gravity of the aircraft. Roll is achieved with these spoilers by the direct action of the lift dumping on one side or the other and by taking advantage of the transformation of yaw into roll by the sweep back of the wings. | ||||||
| 12 | DRONE DEVICE SECURITY SYSTEM | US16017168 | 2018-06-25 | US20180305015A1 | 2018-10-25 | Lucas J. Myslinski |
| A fact checking system utilizes social networking information and analyzes and determines the factual accuracy of information and/or characterizes the information by comparing the information with source information. The social networking fact checking system automatically monitors information, processes the information, fact checks the information and/or provides a status of the information, including automatically modifying a web page to include the fact check results. The fact checking system is able to be implemented utilizing a drone device. | ||||||
| 13 | DRONE DEVICE FOR REAL ESTATE | US16017133 | 2018-06-25 | US20180305014A1 | 2018-10-25 | Lucas J. Myslinski |
| A fact checking system utilizes social networking information and analyzes and determines the factual accuracy of information and/or characterizes the information by comparing the information with source information. The social networking fact checking system automatically monitors information, processes the information, fact checks the information and/or provides a status of the information, including automatically modifying a web page to include the fact check results. The fact checking system is able to be implemented utilizing a drone device. | ||||||
| 14 | Aircraft System for Reduced Observer Visibility | US15870467 | 2018-01-12 | US20180222570A1 | 2018-08-09 | Christopher Eugene Fisher; Steven Bradley Chambers; Pavil Belik; Austin Craig Gunder; John Peter Zwaan |
| An aircraft apparatus is disclosed that has a fuselage boom having proximal and distal ends, a wing coupled to a proximal end of the fuselage boom and at least one transparent stabilizer coupled to a distal end of the fuselage boom. | ||||||
| 15 | Stealth aerial vehicle | US13490593 | 2012-06-07 | US09387930B2 | 2016-07-12 | Jochen Dornwald; Bartholomaeus Bichler |
| An aerial vehicle having a low radar signature includes a first side on which turbine openings, and payload bays or landing gear bays are disposed. A second side of the aerial vehicle is designed to have a smaller radar signature than the first side. | ||||||
| 16 | Stealth Aerial Vehicle | US13490593 | 2012-06-07 | US20150375862A1 | 2015-12-31 | Jochen DORNWALD; Bartholomaeus Bichler |
| An aerial vehicle having a low radar signature includes a first side on which turbine openings, and payload bays or landing gear bays are disposed. A second side of the aerial vehicle is designed to have a smaller radar signature than the first side. | ||||||
| 17 | REMOTELY OR AUTONOMOUSLY PILOTED REDUCED SIZE AIRCRAFT WITH VERTICAL TAKE-OFF AND LANDING CAPABILITIES | US14054080 | 2013-10-15 | US20150225079A1 | 2015-08-13 | Douglas L. Starck; Errica M. Starck |
| An aircraft having a vertical take-off and landing (“VTOL”) propulsion system aircraft, smaller than a standard manned aircraft and remotely or autonomously piloted. The aircraft comprises a symmetrical airfoil shape for the center body section that consists of ribs and spars maintaining an open area in the center. Situated within the open area of the center of the aircraft resides a duct system consisting of a ducted fan and five outlet vents. The main outlet vent functions as the exhaust exiting the aft portion of the aircraft, with the remaining four ducts used for the VTOL capabilities exiting the underside of the aircraft. The aircraft can have a range of wingspan, which can be scaled to satisfy needs and requirements, with a blended wing body that incorporates the inlet and duct system. | ||||||
| 18 | Combined balloon shipping container and deployment system | US13570054 | 2012-08-08 | US08910905B2 | 2014-12-16 | Richard Wayne DeVaul; Eric Teller; Clifford L. Biffle; Joshua Weaver; Brad Rhodes |
| Disclosed embodiments relate to a combined shipping container and balloon deployment system for deploying balloons into a balloon network. Such a shipping container may allow one or more balloons to be transported to a desired launch location, and then launched directly from the shipping container. | ||||||
| 19 | REDUCED VISIBILITY ROTORCRAFT AND METHOD OF CONTROLLING FLIGHT OF REDUCED VISIBILITY ROTORCRAFT | US11189623 | 2005-07-26 | US20060214051A1 | 2006-09-28 | Michael Dammar |
| A rotary aircraft (rotorcraft) in which the entire aircraft rotates about its center of mass as it flies, and in which the center of mass is located external to the aircraft in the generally triangular region formed by the aircraft's single wing and two propellers. As the aircraft flies, the two propellers provide torque about the center of mass and rotate the wing, which provides lift for the aircraft. The aircraft is controllable via a stationary radio transmitter that sends commands for pitch, roll, yaw and altitude. A receiver in the aircraft uses the transmitted signal to establish the aircraft's instantaneous orientation in combination with the sent commands to generate control signals that drive the propeller motors that affect the aircraft's attitude. Pitch and roll are controlled by pulse width modulation of the propeller motor voltages in order to affect the thrust at specific portions of the aircraft's rotation cycle. | ||||||
| 20 | Aircraft with topside only spoilers | US10456176 | 2003-06-06 | US07108230B2 | 2006-09-19 | Walter D. Clark |
| An aircraft with swept back wings and spoilers inlaid into the top surface near the tips of the wings. The aircraft also includes an elevator formed in the center back portion of the aircraft, which is also aft of the spoilers. It is aft to allow an auxiliary control in the elevator signal to cancel the unwanted pitch up moment caused by the spoilers only going up and being aft of the center of gravity of the aircraft. Roll is achieved with these spoilers by the direct action of the lift dumping on one side or the other and by taking advantage of the transformation of yaw into roll by the sweep back of the wings. | ||||||
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