| 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 | Toy for vertical taking-off/landing airplane | JP2635588 | 1988-02-05 | JPH01201294A | 1989-08-14 | FUJIHIRA YUJI; SAMUZAWA AKIRA |
| PURPOSE: To obtain the title toy of a vertical taking-off/landing airplane having an easy operation and safety by mutually reversely rotating a propeller on one diagonal line on a quadrilateral with four positions around a vertical taking- off/landing airplane main body as four corners and the propeller on the other diagonal line, and respectively and separately rotation-driving the propellers to generate upward thrust. CONSTITUTION: Propellers 6, 7, 8 and 9 are provide as the four corners of the quadrilateral, in such a case, of a square, the propellers 6 and 8 on one diagonal line are reversely rotated to the propellers 7 and 9 on the other diagonal line, for example, the propellers 6 and 8 are clockwisely rotated as shown by the arrow symbol of a broken line, and the propellers 7 and 9 are coun terclockwisely rotated. For a vertical taking-off/landing airplane main body 1 and the propellers 6, 7, 8 and 9, for example, by receiving a radio wave emitted from a transmitter possessed by an operator with a receiver equipped with the vertical taking-off/landing airplane main body 1, motors 2, 3, 4 and 5 are driving-controlled, and based on it, the respective propellers 6, 7, 8 and 9 are rotated in a desirable way, and a vertical movement, the rotary movement of a vertical shaft rotation and a tilt movement are attained. COPYRIGHT: (C)1989,JPO&Japio | ||||||
| 182 | VARIABLE ENGINE INLET FOR SHORT TAKE-OFF AND LANDING AND VERTICAL TAKE-OFF AND LANDING AIRCRAFT | PCT/US2005046755 | 2005-12-22 | WO2006069304A3 | 2006-09-14 | PARKS ROBERT |
| A system and method for tilting an engine in a vertical take-off and landing/short take-off and landing aircraft (VTOL/STOL A/C) is provided comprising a main control system, an engine tilting mechanism, and an air flow volume detector, which is located in the engine. The system and method tilt the engine to maximize engine performance based on a variety of parameters including the air flow volume so that forward and horizontal speeds are maximized at the appropriate times, and also to reduce radar cross section and infra-red visibility. | ||||||
| 183 | 수직이착륙 무인기의 함상 이착륙 수단 | KR20160111468 | 2016-08-31 | KR20180024720A | 2018-03-08 | LEE SANG SU |
| 본발명은무인기의착륙장치에형성되는제1면대면탈착수단; 및상기제1면대면탈착수단에대응되는것으로상기제1면대면탈착수단에소정의결합력에의해탈착되며, 함상착륙대에형성되는제2면대면탈착수단을포함하는수직이착륙무인기의함상이착륙수단에관한것으로써, 특히, 이륙중량 200㎏이하의무인기의함상이착륙시벨크로등과같은면대면탈차수단을이용하여무인기의이착륙을용이하게수행할수 있도록보조하는수직이착륙무인기의함상이착륙수단에관한것이다. | ||||||
| 184 | 관절형 붐 어샘블리를 갖는 단거리 이착륙 및 수직 이착륙 자유 날개 항공기 | KR1019950703027 | 1994-01-21 | KR1019960700173A | 1996-01-19 | 엘버트엘.루탄; 휴즈제이.쉬미틀 |
| 185 | Vertical taking off/landing flying device | JP2003365112 | 2003-10-24 | JP2005125976A | 2005-05-19 | ISHIBA MASAJI |
| PROBLEM TO BE SOLVED: To provide a compact vertical taking off/landing flying device capable of being simply and safely operated. SOLUTION: Fans 2 are provided at a front part 1A of a vehicle body and a rear part 1C of the vehicle body respectively. An occupant seat 4 for seating an operator H is provided at a central part 1B of the vehicle body. A seating surface 4b of the occupant seat 4 is arranged at a lower position than a rotation surface of the fan 2. Further, at the central part 1B of the vehicle body, a driving source 3 for driving the fan 2 is arranged below the seating surface 4b of the occupant seat 4. According to such arrangement, the center of gravity of the flying device 1 is positioned at a position close to a lower part of the center of the vehicle body and is hung down from above by the thrust of the fans at the front and rear side of the vehicle body at flying. Accordingly, the stability of the vehicle body during flying is increased and the safety is enhanced. COPYRIGHT: (C)2005,JPO&NCIPI | ||||||
| 186 | КОМПОНОВКА АВИАЦИОННОГО НОСИТЕЛЯ ДЛЯ ВОЗДУШНОГО ВЕРТИКАЛЬНОГО СТАРТА КОСМИЧЕСКИХ РАЕКТ | PCT/IB2015/058792 | 2015-11-13 | WO2017081521A1 | 2017-05-18 | ГАЛЕЕВ, Дамир |
Изобретение относится к авиационно-космической области и описывает устройство авиационного носителя, предназначенного для вывода авиационных и космических аппаратов в атмосферу для их дальнейшего запуска (так называемого, воздушного старта) из вертикального положения – прежде всего космических ракет большой массы. При осуществлении старта носитель находится в режиме висения. Он представляет собой платформу, по периметру которой расположены устройства, создающие вертикальную тягу. Такими устройствами могут быть воздушно-реактивные двигатели, либо воздушные винты или вентиляторы, приводимые в движение двигателями внутреннего сгорания или электродвигателями. Запускаемая ракета подвешена к платформе на тросах (лучше всего из титана). В центре платформы вокруг оси старта ракеты есть свободное пространство, через которое ракета проходит при старте. Устройства, создающие вертикальную тягу, находятся на безопасном расстоянии от оси старта ракеты, таком, что реактивная струя ракетных двигателей при старте не может их повредить. |
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| 187 | IMPROVED VERTICAL TAKE-OFF AND LANDING VEHICLES | PCT/US2004002796 | 2004-02-02 | WO2005003324A2 | 2005-01-13 | MOLLER PAUL S |
| A VTOL vehicle including a fuselage with two foldable wings, two tiltable nacelles attached to the wings, a vertical stabilizer, a horizontal stabilizer, and two auxiliary thrusters. Each nacelle contains a system of vanes located at the rear opening thereof, and actuators are provided for extending and retracting the vanes in conjunction with nacelle tilting mechanisms to deflect the airflow over a predetermined range of angles from the horizontal. Each nacelle also contains two rotary engines, each of which directly drives a fan. The fans face each other and operate in counter-rotating directions at the same rotational speed. An alternative embodiment includes two additional nacelles attached to the fuselage instead of having the auxiliary thrusters. A redundant computerized flight control system maintains stability of the vehicle as it transitions from one flight mode to another. | ||||||
| 188 | VERTICAL TAKEOFF AND LANDING (VTOL) AIR VEHICLE | PCT/US2014036863 | 2014-05-05 | WO2015012935A3 | 2015-05-14 | TAYLOR DANA J; TOKUMARU PHILLIP T; HIBBS BART DEAN; PARKS WILLIAM MARTIN; GANZER DAVID WAYNE; FISHER CHRISTOPHER EUGENE; MUKHERJEE JASON SIDHARTHADEV; KING JOSEPH FREDERICK |
| A flight control apparatus for fixed-wing aircraft includes a first port wing (115) and first starboard wing (120), a first port swash plate (145) coupled between a first port rotor 155) and first port electric motor (135), the first port electric 5 motor (135) coupled to the first port wing (115), and a first starboard swash plate (150) coupled between a first starboard rotor (130) and first starboard electric motor (140), the first starboard electric motor (140) coupled to the first starboard wing (120). | ||||||
| 189 | LANDING ARRESTING SYSTEM FOR VERTICAL TAKE-OFF AND LANDING (VTOL) AERIAL VEHICLES, LANDING AND TAKE-OFF PLATFORM FOR VTOL AERIAL VEHICLES AND VTOL LOCKING MEMBER FOR AERIAL VEHICLES | EP12880637 | 2012-07-05 | EP2870068A4 | 2016-03-09 | CARDELL PER-ERIK; STENBOM KJELL |
| 190 | LANDING ARRESTING SYSTEM FOR VERTICAL TAKE-OFF AND LANDING (VTOL) AERIAL VEHICLES, LANDING AND TAKE-OFF PLATFORM FOR VTOL AERIAL VEHICLES AND VTOL LOCKING MEMBER FOR AERIAL VEHICLES | EP12880637.9 | 2012-07-05 | EP2870068A1 | 2015-05-13 | CARDELL, Per-Erik; STENBOM, Kjell |
| The present invention relates to a landing arresting system for vertical take-off and landing (VTOL) aerial vehicles(1) comprising a landing and take-off platform(6) and at least one VTOL locking member (4) having a projecting portion (32) arranged at a lower portion of the vehicle (1). The landing and take-off platform(6) comprises a plurality of individually displaceable rolls (12),arranged substantially in a horizontal direction, and moveable back and forth, such that the projecting portion (32) of the VTOL locking member (4) can be entered, retained and released between two adjacent rolls (12). The present invention also relates to a landing and take-off platform for VTOL aerial vehicles and a VTOL locking member for aerial vehicles. | ||||||
| 191 | Vertical take off aircraft | US15152416 | 2016-05-11 | US09567071B1 | 2017-02-14 | Stephen Morris |
| An aircraft includes a fuselage, a wing, a ducted fan and a controller. The wing and the ducted fan are coupled to the fuselage. The controller is operable to control the aircraft in a vertical flight mode, a horizontal flight more, and transition the aircraft from the vertical flight mode to the horizontal flight mode. | ||||||
| 192 | Vertical take off aircraft | US14837866 | 2015-08-27 | US09365290B1 | 2016-06-14 | Stephen Morris |
| An aircraft includes a fuselage, a wing, a ducted fan and a controller. The wing and the ducted fan are coupled to the fuselage. The controller is operable to control the aircraft in a vertical flight mode, a horizontal flight more, and transition the aircraft from the vertical flight mode to the horizontal flight mode. | ||||||
| 193 | VERTICAL TAKE OFF PLANE | US12691444 | 2010-01-21 | US20100120321A1 | 2010-05-13 | Steven Rehkemper; Jeffrey Rehkemper; Peter Greenley |
| In one embodiment of the present invention, a vertical take off aircraft is provided with an airframe having an aft section freely pivotally connected to the bow section. The airframe is substantially planar when the aft section is pivotally aligned with the bow section. A propeller system and a pair of wings are secured to the bow section of the airframe. When the bow section is pivoted to a vertical position and the aircraft is placed on a surface, the propeller system when activated will vertically lift the aircraft off of the surface. Furthermore, when the aircraft vertically lifts off of the surface, the aft section freely pivots to form the substantially planar airframe which creates larger lift forces in a horizontal direction than in a vertical direction causing the aircraft to fly in a more horizontal direction, whereby the aircraft automatically switches from a vertical take off to horizontal flight. | ||||||
| 194 | Vertical-takeoff-landing aircraft | US36334764 | 1964-04-27 | US3243146A | 1966-03-29 | CLOVER PAUL B |
| 195 | Vertical take-off aircraft | US14853961 | 1961-10-30 | US3110456A | 1963-11-12 | FREDERICK CREASEY RAYMOND; THOMAS FROUD JOSEPH |
| 196 | Vertical take off aircraft | US10404061 | 1961-04-19 | US3096952A | 1963-07-09 | ROPPEL CLARENCE L |
| 197 | Vertical take-off aircraft | US68461557 | 1957-09-17 | US3065935A | 1962-11-27 | JOHN DUBBURY; MEADOWS FROST JOHN CARVER; DESMOND EARL THOMAS |
| 198 | Vertical takeoff aircraft | US327298 | 1989-03-22 | US5054721A | 1991-10-08 | David L. Brenholt |
| A vertical takeoff ultralight aircraft having an operator controlled high volume vane axial fan in communication with a conduit configured to direct an air stream produced by the fan to a spanwise air duct disposed forwardly of a wing including an air foil. High velocity air is discharged from the air duct and directed over the upper surface of the air foil. An induced air stream flows upwardly and rearwardly through an air flow path defined by the spanwise air duct and the air foil. The wing and air duct are configured such that the induced air stream joins the air stream discharged from the air duct to create reduced static pressure zone on the upper surface of the wing of sufficient magnitude to effect vertical lift. Fan discharge may be partially deflected rearwardly to provide horizontal thrust. | ||||||
| 199 | Vertical take-off aircraft | US611739 | 1975-09-09 | US4071207A | 1978-01-31 | Frank N. Piasecki; Donald N. Meyers |
| A wingless vertical take-off aircraft having multiple ducted propeller rotors with controllable pitch blades symmetrically mounted in the forward and the rear portions and on both sides of the aircraft with the ducts angled downwardly at an acute angle to the aircraft longitudinal axis, transversely extending deflector vanes pivotable vertically within the exit portion of the ducts, and a rudder for yaw control mounted in the exit portion of each rearwardly located duct. Control in altitude and in attitude about the pitch and roll axes is achieved by controlling the collective pitch of the propellers in selected ducts with the roll control being interconnected to the yaw control to counteract roll/yaw coupling effects and control in trim and forward flight thrust being provided by setting the position of the deflector vane to divert the air flow from the ducts in variable directions with respect to the aircraft axis and the vertical. | ||||||
| 200 | Vertical take-off aircraft | US59985466 | 1966-12-07 | US3392935A | 1968-07-16 | ALLMAND JOHN W |
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