| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 101 | Unmanned aircraft and method for controlling attitude thereof | JP2012073802 | 2012-03-28 | JP2013203206A | 2013-10-07 | HASHIMOTO KAZUNORI |
| PROBLEM TO BE SOLVED: To provide an unmanned aircraft capable of securing stability during a flight, and to provide a method for controlling an attitude thereof.SOLUTION: A small unmanned aircraft 1 includes: an airframe 2, the planar shape of which is symmetrically circular, oval, elliptical or polygonal; ducted fans 3 and 4, which are provided in the airframe 2; a duct 6 which connects a right-side air inlet 8 to the ducted fan 3 and which connects the ducted fan 3 to a left-side air outlet 9; and a duct 5 which connects a left-side air inlet 7 to the ducted fan 4 and which connects the ducted fan 4 to a right-side air outlet 10. | ||||||
| 102 | Flight equipment | JP2004540701 | 2003-09-25 | JP4359239B2 | 2009-11-04 | ヴァゲルズ、ディーター |
| 103 | Missile position control device, and missile | JP2008100459 | 2008-04-08 | JP2009248808A | 2009-10-29 | ISHIBA MASAJI |
| PROBLEM TO BE SOLVED: To provide a missile position control device and a missile controlling a position while maintaining the attitude of an airframe even if receiving disturbance such as a blast in the missile provided with a thrust generation means generating thrust for controlling the position and the attitude. SOLUTION: A control CPU 3 controls a thrust generating part 5 by a controlled variable corresponding to deviation between the present position of a vertical take-off and landing aircraft 1a and a target position. In addition, a GYRO 2 detects the disturbance to the vertical take-off and landing aircraft 1a, and the control CPU 3 corrects the controlled variable according to the disturbance detected by the GYRO 2. Thereby, even if receiving the disturbance such as the blast, the controlled variable is corrected to a value corresponding to the disturbance. Accordingly, the position is controlled while maintaining the attitude of the airframe. COPYRIGHT: (C)2010,JPO&INPIT | ||||||
| 104 | Exhaust nozzle of a reversible integrated turbo fan engine of | JP2000004204 | 2000-01-13 | JP4128714B2 | 2008-07-30 | グザビエ・ジヤン−ミシエル・アンドレ・ギヨネ; ジル・アラン・シヤリエ; ジル・ルイ・ロラン |
| 105 | Vertical taking-off/landing flying device | JP2005241479 | 2005-08-23 | JP2007055372A | 2007-03-08 | ISHIBA MASAJI |
| PROBLEM TO BE SOLVED: To provide a technology capable of keeping the stability of attitude control of a machine body, even if weight distribution in the machine body of a vertical taking-off/landing flying device varies. SOLUTION: The moment of inertia about a predetermined shaft of the machine body of the vertical taking-off/landing flying device is timely derived (S105). In the attitude control of the machine body, trust to be generated by a plurality of thrust generating machines disposed on the machine body is adjusted based on the moment of inertia at the time of the attitude control (S117). COPYRIGHT: (C)2007,JPO&INPIT | ||||||
| 106 | Helicopter | JP18238793 | 1993-07-23 | JPH0733090A | 1995-02-03 | SUGIYAMA KATSUMASA |
| PURPOSE:To reduce air resistance or the like in a helicopter blowing off high pressure gas from the lower face of a body in order to improve taking-off/ landing performance by forming a skirt for improving this effect in such a way as to be rotatable and enclosable independently of the blowoff of high pressure gas. CONSTITUTION:In a helicopter, high pressure gas is blown off from the lower face of a body 5 in order to improve taking-off/landing performance, and a skirt 11 is added to the lower part of the body 5 in order to improve this effect. In this case, the skirt 11 is added in such a way as to be movable (19) through a hinge 18. In association with the operation of a switch 16 by a pilot 17, this electric signal is transmitted to a hydraulic device or a motor 14 through wiring 15, and the skirt 11 is driven by an actuator 13 through a rod 12. At this time, the driving operation of the skirt 11 is performed by the pilot 17 independently of the blowoff operation of high pressure gas. At the non-used time, the skirt 11 is moved (19) into a storage position 20 so as to reduce air resistance. | ||||||
| 107 | Thrust deviation system | JP31941891 | 1991-12-03 | JPH05155386A | 1993-06-22 | KONNO HIDETO; UDAGAWA NAOHIKO; KOBAYASHI HIDEHIKO |
| PURPOSE: To obviate the need for a gas leakage sealing device by requiring no complicated structural gimbal or no friction reducing device and by providing simple structure, small size, and light weight, and by reducing the gap of a spherical sliding part. CONSTITUTION: A thrust deviation system deviates gas exhaust direction by rocking a duct for exhausting a high-temperature and high-pressure gas generated by burning fuel by a ball-, and socket-equipped swivel mechanism. Where, a ball 6 and a socket 7 in the thrust deviation system use a ceramics material as a raw material and are of shape having a concentric surface with the point on the center line of the duct as a center and have configuration formed by setting the angle of Sin -1 (W/2R) to the range of 8 degrees to 25 degrees. where, R is the radius of the ball and W is the width of the ball. COPYRIGHT: (C)1993,JPO&Japio | ||||||
| 108 | JPH01501541A - | JP50065488 | 1987-11-23 | JPH01501541A | 1989-06-01 | |
| 109 | Ramming air type steering gear for guided missile | JP28911086 | 1986-12-05 | JPS62152998A | 1987-07-07 | UIRIAMU RICHIYAADOSON BEINZU |
| 110 | High manoeuverable aircraft and flight method thereof | JP8196286 | 1986-04-09 | JPS621695A | 1987-01-07 | TOOMASU EICHI SUTOROOMU |
| 111 | JPS4918397B1 - | JP522769 | 1969-01-23 | JPS4918397B1 | 1974-05-09 | |
| 112 | 乗員推進装置 | JP2019503791 | 2017-04-06 | JP6978795B2 | 2021-12-08 | フランキー ザパタ |
| 113 | Flying object position control apparatus and a flying object | JP2008100459 | 2008-04-08 | JP5252973B2 | 2013-07-31 | 政次 石場 |
| 114 | Air-jet propulsion system | JP2007538443 | 2004-10-29 | JP2008517828A | 2008-05-29 | サンチェス、フェリックス サンチェス |
| この発明は３つのボディからなるエアージェット推進装置に関する。 第１ボディすなわちヘッドは半卵形状を有し、その上方部はグリル（格子）を備え、その下方部は一部で閉塞されている。 第１ボディは閉止リングを備える。 第２ボディすなわち中央部は円筒形状を有し、スパーク点火エンジンに連結された螺旋状円形ハニカムローターから構成される。 第３ボディすなわち後方部は切頭円錐形状を有し、航空機のバランスを取り、安定化させ、操舵するための一連の開口、ゲートおよびバタフライバルブを備える。 これにより航空機は低速度（ｋｍ／ｈ）での飛行が可能になるので燃料消費を軽減し、したがって汚染を軽減する。 よって、最小滑走路での離着陸を容易にし、高速度で離着陸を行わなければならない場合に関連するリスクを取り除くことができる。
【選択図】図１ |
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| 115 | Flight equipment | JP2004540701 | 2003-09-25 | JP2006515542A | 2006-06-01 | ヴァゲルズ、ディーター |
| ここに開示されているのは飛行装置である。 当該飛行装置は、垂直方向に離陸することができ、かつ少なくともホール（１００、２００）内を自由に飛行するために一人または数人の人間を収容することができる、少なくとも一台の飛行ユニット（１０）から構成され、飛行ユニット（１０）がホール（１００、２００、３００）から出るのを前記ホールの境界（２、３、４、５、６）が防止している。 | ||||||
| 116 | High-mobility aircraft and how flight | JP8196286 | 1986-04-09 | JP2534666B2 | 1996-09-18 | TOOMASU EICHI SUTOROOMU |
| 117 | Ram air steering device for the guided missile | JP28911086 | 1986-12-05 | JPH0631720B2 | 1994-04-27 | UIRIAMU RICHAADOSON BEINZU |
| 118 | Antofagasta - bottle engine | JP8398287 | 1987-04-07 | JPH063146B2 | 1994-01-12 | GEERII FURANKU SUZAMINSUKII; DAGURASU JON NAICHINGEERU |
| 119 | Rolling control apparatus for airplane | JP32454791 | 1991-12-09 | JPH05155387A | 1993-06-22 | NAGAHATA MASASHI |
| PURPOSE:To prevent the deteriovation of wing performance by rotatably mounting part of a structure for supporting an engine in the pitch direction on a wing torque box through a pivot and by providing the turning direction of a right and a left engine with the reverse direction respectively by the actuation of a pitch actuator to provide a fuselage with rolling moment. CONSTITUTION:Part of a structure for supporting each engine equipped on a right and a left wing in an air plane is rotatably mounted in the pitch direction on a wing torque box 3 or a structure part connected to the torque box 3 through a pivot 2. In addition, there is provided a pitch actuator 1 for turning the structure for supporting the engine to the pitch direction. The actuation of the pitch actuator 1 provides the turning direction of a right and a left engine with the reverse direction respectively to provide a fuselage with rolling moment. The result limits no flap width, develops no aileron reversal, and provides a rolling control apparatus having no decrease in wing performance and no increase in resistance. | ||||||
| 120 | Gas turbine engine | JP8398287 | 1987-04-07 | JPS62240434A | 1987-10-21 | GEERII FURANKU SUZAMINSUKII; DAGURASU JIYON NAICHINGEERU |
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