专利检索_ 旋翼机;其特有的旋翼专利检索_ 旋翼机;其特有的旋翼专利检索查询

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序号	专利名	申请号	申请日	公开（公告）号	公开（公告）日	发明人
21	Rotary wing apparatus	JP7661876	1976-06-30	JPS527597A	1977-01-20	PATORITSUKU JIEI KADOMOA

22	多重回転子無人航空機	JP2015542149	2013-11-13	JP2016505435A	2016-02-25	タオワン，; タオジャオ，; シャオジエチェン，; ジガンオウ，
本発明は、向上した信頼性を持つ無人航空機(UAV)のための方法および装置を提供する。本発明の一態様によって、機上のセンサーが経験する機上の電気部品からの干渉が減少される。本発明の別の一態様によって、電気部品のユーザによる構成または組み立てが最小化されて、ユーザエラーが減少する。無人航空機(UAV)は、空洞を形成する外側表面および内側表面を備える筐体と、前記空洞の内側に配置され、かつ前記UAVの動作を制御するように適合された1つ以上の電気部品と、前記筐体の外側に置かれるセンサーであって、前記センサの動作が、前記1つ以上の電気部品によって惹起される干渉を受けやすい、センサーと、を備える。【選択図】なし
23	Helicopter for a rotary wing system	JP2012257490	2012-11-26	JP5281187B1	2013-09-04	忠岩田
【課題】突風を受けた場合に機体のコントロールを容易に行うことができるヘリコプター用回転翼システムを提供する。【解決手段】ローターマスト２と、ローターマストで各々基部を支持された偶数枚の回転翼３と、ローターマストを回転駆動して回転翼をそのローターマストの軸線周りに回転させる動力源とを具える。偶数枚の回転翼が、二枚ずつ、ローターマストを間に挟み、そのローターマストの直径方向に延在して対をなすとともに、そのローターマストの周方向に等間隔に配置され、対をなす二枚の回転翼の基部が、互いに一体的に結合されて、そのローターマストの直径方向に延在する共通の軸線周りに互いに一体に揺動自在に、そのローターマストに直角に設けられた支持軸に支持され、支持軸が、回転翼に水平姿勢からの仰角を与えるとともに、その回転翼の回転方向前方からの風圧を受けると仰角が減少する前後翼端間位置で回転翼を支持する。【選択図】図１
24	Disc rotor retraction system	JP2011288557	2011-12-28	JP2012180083A	2012-09-20	PODGURSKI DANIEL MICHAEL
PROBLEM TO BE SOLVED: To provide a safety mechanism designed to prevent failures, in a disc rotor system which allows partial or full retraction of rotor blades to allow a helicopter as a vertical takeoff or landing aircraft to convert to wing supported flight for high speed cruise.SOLUTION: A disc rotor retraction system includes a main blade spar 22 incorporating a hydraulic cylinder 54 and having a screw thread 34. A ball screw 24 is concentrically carried within the main blade spar and is operably connected to a ball nut 60 which has an outboard end connected to an intermediate spar 26 with a hydraulic piston received for reciprocation in the hydraulic cylinder. A first geared actuator engages the ball screw and a second geared actuator engages a main blade spar screw thread.
25	Helicopter single-blade rotor	JP2000585123	1999-12-01	JP2002531313A	2002-09-24	リダク、ヴラディミーロ
(57)【要約】【課題】ヘリコプタ用シングルブレードロータ。【解決手段】ロータの回転軸に垂直なブレード揚力の成分は、その回転軸に対するロータの質量中心の位置を自己調節することにより得られる慣性力により補償される。ロータの質量中心の位置は、ブレードのコーニング角により定められる。
26	Method and device for measuring airspeed of rotary vane aircraft	JP24476996	1996-09-17	JPH09127144A	1997-05-16	BROCKLEHURST ALAN
PROBLEM TO BE SOLVED: To reduce or solve conventional problems by use of air flow measurement value to a main sustaining rotor capable of directly relating to airspeed and relative wind direction. SOLUTION: This method and device for detecting the airspeed of helicopter 10 provided with a sustaining rotor 23 having a plurality of vanes 23A-23D capable of rotating around a vertical axis 24 measures an air flow laterally sliding angle determined according to the rotation of the rotor 23, in relation to at least one rotor vane, then generating a signal showing the angle, and after the signal is compared in a processor P including information on the known relation between the angle β and the airspeed, an output signal showing the airspeed and wind direction is outputted to a display.
27	Flying platform	JP3294788	1988-02-17	JPS63291798A	1988-11-29	POORU ESU MORAA

28	Discoid flying machine	JP13440278	1978-10-31	JPS5475795A	1979-06-16	HAINTSU YORUDAN

29	JPS50107697A -	JP1292075	1975-01-30	JPS50107697A	1975-08-25

30	回転翼無人機によるプロペラ推進式滑走移動体、特に、水中翼船	JP2015240082	2015-12-09	JP2016120906A	2016-07-07	アンリセドゥ; ジョンエシェパーレ
【課題】既存の無人機を利用して、単純かつ直観的に無人機の種々の操縦を実現することが可能であって、可動部品を備えていない単純かつ堅牢な構造を備えた滑走変位型移動体を提案する。【解決手段】この移動体は、滑走要素セット110、120g、120dが下側領域に設けられた滑走静的構造100を備える。移動体は、推進群200を形成する複数のロータ221〜224を有する回転翼無人機の取り外し可能な取り付けのための手段300をさらに備え、推進群の複数のロータは、移動体の滑走の主軸X−Xに沿った成分を有する推力をそれぞれかけるように構成され、複数のロータ221〜224の比例且つ個別化された駆動によって、舵がなくても移動体の速度および方向を操縦することができる。【選択図】図1
31	ディスクローター引き込みシステム	JP2011288557	2011-12-28	JP5872284B2	2016-03-01	ポドガルスキー, ダニエルマイケル

32	Hover-capable aircraft	JP2013219608	2013-10-22	JP2014088168A	2014-05-15	ANDREA GABRIELLI; GASPARINI GIUSEPPE
PROBLEM TO BE SOLVED: To provide a hover-capable aircraft designed in such a way that operation noise is notably reduced.SOLUTION: A hover-capable aircraft includes propulsion means, at least one rotor, transmission means of transmitting power from the propulsion means to the rotor and lubricated with a lubricant, a heat exchanger receiving a heated lubricant from the transmission means and returning the lubricant after cooling to the transmission means and a fan 10 generating an air flow in the heat exchanger to cool the lubricant and also has an impeller 16 provided with blades 21 and a discharge pipe 18 discharging high-temperature air generated in cooling the lubricant. The hover-capable aircraft has dissipation means 25 designed in such a way that at least a part 23 of the wall part 22 of the discharge pipe 18 selectively absorbs pressure waves in a specified frequency band related to the rotation speed of the impeller 16 and to the number of blades 21 of the impeller 16.
33	Rotor with a branch-type rotor blade	JP2001507948	2000-07-06	JP4008239B2	2007-11-14	ルドルフバンアッシュ，

34	Method for measuring the airspeed of rotary wing aircraft and equipment	JP24476996	1996-09-17	JP3860264B2	2006-12-20	アラン・ブロックルハースト

35	Main rotor for aircraft	JP20141684	1984-09-26	JPS6092999A	1985-05-24	ENRIKE BANIYOORASU DE AYARA

36	JPS5541960B2 -	JP1292075	1975-01-30	JPS5541960B2	1980-10-27

37	JPS50117199A -	JP14299674	1974-12-12	JPS50117199A	1975-09-12

38	수직 이착륙 비행체	KR1020160029586	2016-03-11	KR101749863B1	2017-06-22	정진덕
일실시예에따른수직방향으로이착륙되는비행체는몸체, 상기몸체에배치되어서동력을공급하는동력공급부, 상기몸체에배치되어서비행모드를제어하는제어부, 상기몸체에배치되고, 상기동력공급부로부터동력을전달받아회전하는수직추력부, 및상기동력공급부로부터동력을전달받아회전하고, 상기몸체의일 측에서배치되는가변추력부를포함할수 있다. 또한, 상기제어부는상기수직추력부와상기가변추력부를제어하며상기수직추력부는상기제어부에의해상기몸체에대하여평행하게배치되고, 상기가변추력부는상기제어부에의해상기몸체에대하여평행및 수직방향으로전환될수 있다.
39	호버링 가능한 항공기	KR1020130127215	2013-10-24	KR1020140053786A	2014-05-08	가브리엘리,안드레아; 가스파리니,쥐세페
Provided is a hover-capable aircraft comprising: a propulsion means (6); at least one rotor (3); a transmission means for transmitting from the propulsion means to the rotor (3) and lubricated with a lubricant; a heat exchanger (9) receiving heated lubricant from the transmission means and feeds cooled lubricant back to the transmission means (5); and a fan (10) producing airflow passing through the heat exchanger (9) to cool the lubricant and including an impeller (16) with blades (21) and an exhaust pipe (18) expelling hot air produced by the cooling the lubricant, wherein at least one portion (23) of the wall (22) of the exhaust pipe (18) includes a dissipating means (25) designed to selectively absorb pressure waves in a predetermined frequency band related to the rotation speed (V) of the impeller (16) and to the number (N) of the blades (21) of the impeller (16).
40	단일 케이블링 조립체를 미리 구비한 항공 전자 기기 랙과 제어 패널을 함께 장착하기 위한 장착 구조물을 구비한 회전익기	KR1020130128125	2013-10-25	KR1020140052906A	2014-05-07	올리브리샤르
Provided is a rotorcraft fitted with a means for mounting at least one front avionics rack (3, 3′) and man-machine interface instruments (2) on board of a fuselage structure (4). A mounting structure (1) comprises a slotted body forming compartments for receiving interface instruments (2), the avionics rack (3, 3′), and a unitary cabling assembly (12) suitable for uniting as a block with the mounting structure (1). The mounting structure (1) is installed as one block on the fuselage structure (4) after the functions thereof has been verified. The unitary cabling assembly (12) may also include separation connectors (14) segregating communications of the front avionics rack (3, 3′) respectively with remote computers (5) by means of a primary communication bus of multiplexed, unidirectional, or bidirectional type, and with ancillary equipment (6), and/or with on-board instruments (7) by means of a secondary fieldbus.

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