子分类：
- B64C2025/325： ..直升机专用
- B64C25/34： ..轮式,例如多轮起落架
- B64C25/38： ..履带式
- B64C25/40： ..部件是在接地前旋转的
- B64C25/42： ..制动器的布置或配置(通过速度情况,例如起落架接合地面滑行的加速度或减速度至少可部分地对地面制动力加以调节的入B60T8/32)〔4〕
- B64C25/50： ..可转向的起落架;减摆架(应用于地面车辆的转向装置入B62D)
- B64C25/52： ..雪橇或滑橇
- B64C25/54： ..浮筒
- B64C25/58： ..减震器或弹簧的布置或配置(减摆器入B64C25/50;一般车辆悬架装置入B60G;减震器本身入F16F)
- B64C25/66： ..可转换的起落架;不同种类地面滑行或类似接合部件的组合
| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 181 | Aeroplane construction | US40337729 | 1929-10-30 | US1882416A | 1932-10-11 | LOUIS GASTWIRTH |
| 182 | Airplane landing-gear. | US22686018 | 1918-04-05 | US1296770A | 1919-03-11 | CURTISS GLENN H |
| 183 | Flying-machine. | US1912677100 | 1912-02-12 | US1077258A | 1913-11-04 | COFFMAN HURSHEL R |
| 184 | 3상 전력 무선충전형 무인비행체 및 이를 위한 3상 전력 무선충전 장치 | KR1020160107444 | 2016-08-24 | KR1020180022260A | 2018-03-06 | 김정호; 송치억 |
| 본발명은 3상무선충전형무인비행체와이의구동에필요한전력을무선충전할수 있는장치가개시된다. 비행체의 3개의착륙용다리말단부에 3개의전력수신코일이장착된다. 각전력수신코일마다공진전류가흐르도록하는공진부가부가된다. 비행체에설치된 3상전력컨버터는공진부및 상기 3개의전력수신코일에의해유도된 3상교류유도전류를입력받아직류전류로변환하여배터리에충전되게한다. 무인비행체용 3상전력무선충전장치는상기무인비행체의상기 3개의착륙용다리가충전플랫폼에마련된 3개의코일안착부에안착하였을때, 3개의전력전송코일에서 3개의전력수신코일로 3상전력을무선으로전달한다. 공진전류가흐르도록하는공진부도포함한다. 누설자속이무인비행체로접근하지못하게하여무인비행체의전자장비의오동작가능성을막아주는누설자속차폐코일이코일안착부입구부에마련될수 있다. 전력전달효율이우수하고, 전자파방해잡음또한줄일수 있다. | ||||||
| 185 | 카메라를 구비한 무인 비행체 | KR20160101501 | 2016-08-09 | KR20180017537A | 2018-02-21 | LEE WU SEONG; JANG SEUNG HO; KANG NEUNG EUN; KIM TAE KYUN; KIM HYUN SOO; BAEK SANG IN; LEE JUNG JAE; AHN DAE KYUNG; LEE KWAN HEE; KIM SEUNG NYUN; HEO CHANG RYONG |
| 무인비행체에있어서, 본체, 상기본체의적어도일측면으로부터지정된길이로연장된복수의프로펠러연결부, 상기복수의프로펠러연결부의끝단에각각연결된복수의프로펠러, 및상기본체의적어도일면에장착된복수의카메라를포함하고, 상기복수의카메라중 상기복수의프로펠러연결부사이에배치된제1 카메라는상기본체의중심점으로부터제1 크기의거리만큼이격되어배치되고, 상기복수의프로펠러중 상기제1 카메라와인접하게배치된제1 프로펠러의중심점과상기본체의중심점을연결한제1 직선은제2 크기의길이를갖고, 상기제1 카메라로부터상기제1 직선까지수직하게그어지는제2 직선은제3 크기의길이를갖고, 상기제3 크기는상기제1 프로펠러의반경보다크고, 상기제1 크기는상기제2 크기보다작은것을특징으로하는무인비행체가개시된다. 이외에도명세서를통해파악되는다양한실시예가가능하다. | ||||||
| 186 | 고소 작업용 드론 장비 및 이를 이용한 고소 작업 방법 | KR20160093337 | 2016-07-22 | KR20180010744A | 2018-01-31 | |
| 본발명은원격조정에의해고소의특정위치로비행이가능한드론을이용하여구조물의고소위치에형성된러그등의잔재물의절단과표면의연마를수행할수 있도록한 것으로서, 보다상세하게는상부에회전익(110)이구비되어사용자가원하는고소의위치로무인주행이가능한드론비행체(10)와, 상기드론비행체(10)에구비되어구조물(200) 상의고소의표면에상기드론비행체(10)를고정시킬수 있도록하는고정장치(120) 및상기드론비행체(10)에구비되어상기드론비행체(10)가상기구조물(200) 상에고정된상태로상기구조물(200)의표면에형성된잔재물(L)의절단또는표면의연마중 적어도어느하나이상의작업을수행하는작업모듈부(130)를포함하는것을특징으로하는고소작업용드론장비에관한것이다. | ||||||
| 187 | 드론용 모터 및 이를 포함하는 드론 | KR20160087834 | 2016-07-12 | KR20180007091A | 2018-01-22 | PARK YOUNG DAE |
| 본발명은회전축; 상기회전축이삽입되는홀을포함하는스테이터; 상기스테이터의외측에배치되는로터를포함하고, 상기로터는, 상기회전축과결합하여상기스테이터의상부를덮는커버부; 상기스테이터의측부를덮는몸체부및 상기몸체부의내주면에결합하는마그넷을포함하고, 상기커버부는, 상기회전축이관통하는홀을포함하는프로펠러결합부; 상기몸체부와연결되는상면부; 상기프로펠러결합부와상기상면부를연결하는연결부; 및상기프로펠러결합부의측면에서방사방향으로형성되며, 상기상면부와이격되어형성된복수개의블레이드를포함하는드론용모터를제공하여, 방열을위한공기유로를확보하면서도, 물이나이물질이모터내부로침입하는것을방지하는유리한효과를제공한다. | ||||||
| 188 | 무인비행시스템 | KR1020150013910 | 2015-01-29 | KR101610801B1 | 2016-04-11 | 정유미 |
| 본발명은무인비행시스템에관한것으로서, 기상, 방재, 군사등 다양한분야에서유용한자료로활용될수 있도록 3D 공간구축 DB를수집하기위하여, 본체, 상기본체에구축되는모터/변속기처리부, 짐벌탈착부, 배터리장착부으로구성된비행체와; 상기비행체의본체에구축되는통합항법부(FCC), 센서모듈(GPS/IMU/ETC), 파워처리부(메인, 모터, 주변기기), 통신처리부, I/O 처리부, 영상처리부로구성된통합항법장치; 를포함하는무인비행시스템에있어서, 상기무인비행시스템의이륙시에상기본체의좌우편상하에구비된프로펠러를보호하는용도로활용되는한편, 무인비행시스템의착륙시에무인비행시스템의하중을지지하는랜딩기어용도로도활용될수 있는겸용가능한프롭가이드가더 포함됨에따라, 무선비행체의비행과정에서외부장애물과충돌시에도프로펠러가보호되어프로펠러의파손및 고장을방지하고, 프로펠러의부품교체나무선비행체의추락에따른비용손실을예방하게되는무인비행시스템을제공한다. | ||||||
| 189 | SYSTEMS AND METHODS FOR RESPONSE TO EMERGENCY SITUATIONS USING UNMANNED AIRBORNE VEHICLES WITH IMPROVED FUNCTIONALITIES | US15978060 | 2018-05-11 | US20180327091A1 | 2018-11-15 | Philip E. Burks; James Nipp; Jerry Daniel Claridge; Paul Miller |
| Various embodiments of systems, apparatus, and/or methods are described for enhanced responsiveness in responding to an emergency situation using unmanned aerial vehicles (drones). Drones are fully autonomous in that they are operated without human intervention from a pilot, an operator, or other personnel. The disclosed drone utilizes movable access doors to provide the capability of vertically takeoff and landing. The drone also includes an emergency recovery system including a mechanism to deploy a parachute in an event of a failure of the on-board autopilot. Also disclosed herein is a drone port that provides an IR-based docking mechanism for precision landing of the drone, with a very low margin of error. Additionally, the drone port includes pads that provide automatic charge to the drone's batteries by contact-based charging via the drone's landing gear legs. | ||||||
| 190 | UNMANNED AERIAL VEHICLE AND OPERATIONS THEREOF | US15947650 | 2018-04-06 | US20180229834A1 | 2018-08-16 | Tao Wang; Tao Zhao; Shaojie Chen; Zhigang Ou |
| The present invention provides methods and apparatus for unmanned aerial vehicles (UAVs) with improved reliability. According to one aspect of the invention, interference experienced by onboard sensors from onboard electrical components is reduced. According to another aspect of the invention, user-configuration or assembly of electrical components is minimized to reduce user errors. | ||||||
| 191 | Gyroscopic orbiter with vertical takeoff and vertical landing capabilities | US15184186 | 2016-06-16 | US10017278B2 | 2018-07-10 | Thomas Norman Hesse |
| A gyroscopic orbiter with vertical takeoff and vertical landing capabilities can transition between different functional modes while in-flight. The orbiter typically includes a fuselage, a front boom, a front propulsion unit, a rear boom, and a rear propulsion unit. The front boom is mounted at two pivot points to a bow of the fuselage by the front boom. The rear boom is mounted at two pivot points to a stern of the fuselage by the rear boom. One functional mode is the vertical takeoff and landing mode, wherein the propulsion units are oriented parallel to each other and are directed upward. Another functional mode is the shuttle mode, wherein the propulsion units are oriented at an angle with each other, and the front propulsion unit is directed forward. Another functional mode is the high speed mode, wherein the propulsion units are oriented collinear with a roll axis of the fuselage. | ||||||
| 192 | Vertical take-off-and-landing unmanned aerial vehicle system capable of landing on uneven or sloped terrain | US15081163 | 2016-03-25 | US09994307B2 | 2018-06-12 | Hoa G. Nguyen; Aaron B. Burmeister |
| A system for landing, comprising a vertical-take-off-and-landing (VTOL) unmanned air vehicle (UAV) having landing gear, wherein the landing gear is telescopic and comprises a sensor, and wherein the landing gear is compressed upon landing on a surface, and the compression causes a signal to be sent to a system that computes the slope of the ground surface using the length of the compressed landing gear and the attitude of the UAV. If the center of gravity falls within the support area, the legs are locked and the UAV power is turned off. If the center of gravity falls outside the support area, the UAV is forced to take off and find a safer landing spot. | ||||||
| 193 | Aerial vehicle with frame assemblies | US15405140 | 2017-01-12 | US09884681B2 | 2018-02-06 | Tao Wang; Tao Zhao; Hao Du; Mingxi Wang |
| Systems, devices, and methods for a transformable aerial vehicle are provided. In one aspect, a transformable aerial vehicle includes: a central body and at least two transformable frames assemblies respectively disposed on the central body, each of the at least two transformable frame assemblies having a proximal portion pivotally coupled to the central body and a distal portion; an actuation assembly mounted on the central body and configured to pivot the at least two frame assemblies to a plurality of different vertical angles relative to the central body; and a plurality of propulsion units mounted on the at least two transformable frame assemblies and operable to move the transformable aerial vehicle. | ||||||
| 194 | Emergency Landing Stability System for Aircraft | US15132930 | 2016-04-19 | US20170297682A1 | 2017-10-19 | Robert E. Grip; Steven R. Kent; Ted K. Rothaupt; Blaine K. Rawdon |
| An aircraft emergency landing stability system includes an aircraft a fuselage and landing gear, and a landing stability apparatus coupled to the fuselage, wherein the landing stability structure mitigates a nose-down pitching moment of the aircraft created in response to contact with a landing surface during an emergency landing. | ||||||
| 195 | Impact protection apparatus | US15349750 | 2016-11-11 | US09789969B2 | 2017-10-17 | Mingyu Wang |
| An impact protection apparatus is provided, comprising a gas container configured to hold a compressed gas and an inflatable member configured to be inflated by the gas and function as an airbag of a movable object, such as an aerial vehicle. A valve controls flow of gas from the container to the inflatable member in response to a signal from a valve controller. The valve and valve controller are powered by an independent power source than one or more other systems of the movable object. A safety mechanism may also be provided that, unless deactivated, prevents inflation of the inflatable member. | ||||||
| 196 | Airship including aerodynamic, floatation, and deployable structures | US15242223 | 2016-08-19 | US09745042B2 | 2017-08-29 | John Goelet |
| An airship is provided. The airship includes a hull configured to contain a gas, at least one propulsion assembly coupled to the hull and including a propulsion device, and at least one aerodynamic component including a plurality of fairing structures including one or more slats, wherein the at least one aerodynamic component is associated with the hull and is configured to direct airflow around the airship. | ||||||
| 197 | AERIAL VEHICLE WITH FRAME ASSEMBLIES | US15405140 | 2017-01-12 | US20170144741A1 | 2017-05-25 | Tao Wang; Tao Zhao; Hao Du; Mingxi Wang |
| Systems, devices, and methods for a transformable aerial vehicle are provided. In one aspect, a transformable aerial vehicle includes: a central body and at least two transformable frames assemblies respectively disposed on the central body, each of the at least two transformable frame assemblies having a proximal portion pivotally coupled to the central body and a distal portion; an actuation assembly mounted on the central body and configured to pivot the at least two frame assemblies to a plurality of different vertical angles relative to the central body; and a plurality of propulsion units mounted on the at least two transformable frame assemblies and operable to move the transformable aerial vehicle. | ||||||
| 198 | IMPACT PROTECTION APPARATUS | US15349750 | 2016-11-11 | US20170057645A1 | 2017-03-02 | Mingyu Wang |
| An impact protection apparatus is provided, comprising a gas container configured to hold a compressed gas and an inflatable member configured to be inflated by the gas and function as an airbag of a movable object, such as an aerial vehicle. A valve controls flow of gas from the container to the inflatable member in response to a signal from a valve controller. The valve and valve controller are powered by an independent power source than one or more other systems of the movable object. A safety mechanism may also be provided that, unless deactivated, prevents inflation of the inflatable member. | ||||||
| 199 | Vertical Takeoff and Landing Vehicle with Increased Cruise Efficiency | US15332391 | 2016-10-24 | US20170057631A1 | 2017-03-02 | William J. FREDERICKS; Mark D. MOORE; Ronald C. BUSAN; Paul M. ROTHHAAR; David D. NORTH; William M. LANGFORD; Christopher T. LAWS; William T HODGES; Zachary R. JOHNS; Sandy R. WEBB |
| Systems, methods, and devices are provided that combine an advance vehicle configuration, such as an advanced aircraft configuration, with the infusion of electric propulsion, thereby enabling a four times increase in range and endurance while maintaining a full vertical takeoff and landing (“VTOL”) and hover capability for the vehicle. Embodiments may provide vehicles with both VTOL and cruise efficient capabilities without the use of ground infrastructure. An embodiment vehicle may comprise a wing configured to tilt through a range of motion, a first series of electric motors coupled to the wing and each configured to drive an associated wing propeller, a tail configured to tilt through the range of motion, a second series of electric motors coupled to the tail and each configured to drive an associated tail propeller, and an electric propulsion system connected to the first series of electric motors and the second series of electric motors. | ||||||
| 200 | On-board water spray system for aircraft | US14270301 | 2014-05-05 | US09566597B2 | 2017-02-14 | Gary E. McKay |
| A system for simulating wet runway conditions by using a liquid container that is placed inside an aircraft. The liquid container is connected to a nozzle that sprays water in front of the wheels of the aircraft. A valve is used to control the flow of water from the nozzle. Systems, such as the braking system of the aircraft, can then be tested in wet runway conditions simulated by the system. The amount of water sprayed from the nozzle can also be electronically controlled in relation to the speed of the aircraft, such that the nozzle sprays a nearly uniform layer of liquid in front of the wheels. The system can also be modified to include two tanks to manipulate the center of gravity of the aircraft. | ||||||
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