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91. 发明专利

JP2001138996A AIRPLANE MOUNTED WITH FOURTH-FIFTH WINGS AND SATABILIZER WING 失效
公开(公告)号：JP2001138996A
公开(公告)日：2001-05-22
申请号：JP35636699
申请日：1999-11-10
申请人： KUZUU MIKIO
发明人： KUZUU MIKIO
IPC分类号： B64C1/26 , B64C5/00 , B64C39/12
摘要： PROBLEM TO BE SOLVED: To stabilize the head part of an airplane so as not to stall when the airplane takes off, lands and reduces speed, and to heighten stability and safety performance during the flight of the airplane. SOLUTION: In this airplane having horizontal tail units and a vertical tail unit at a tail part, a fuselage of the airplane is mounted with horizontal head wings and a vertical head wing near the head part of the fuselage in addition to main wings, the horizontal tail units and the vertical tail unit.

92. 发明专利

JP2000233799A AIRPLANE 失效
公开(公告)号：JP2000233799A
公开(公告)日：2000-08-29
申请号：JP3796599
申请日：1999-02-17
申请人： KAYAMA TSUNEO
发明人： KAYAMA TSUNEO
IPC分类号： B64C39/04 , B64C39/08 , B64C39/12
摘要： PROBLEM TO BE SOLVED: To use a canard plane as a passenger airplane by arranging a tip tail assembly in front of a main fuselage, vertically separating a main wing backward, installing the main wing so as to be dislocated forward, and connecting the tip tail assembly and the tip of the main wing by a sub-fuselage. SOLUTION: A main wing 31 is arranged in front and in rear, and an airframe is supported by longitudinally dislocating the main wing 31. Even if the center of gravity existing in the central vicinity of a main fuselage 34 of the airframe moves slightly longitudinally more than when supported by a single main wing, a flight can be stably performed, and a moving range of the center of gravity of a canard plane is increased to enhance stability. A sub-fuselage 32 is installed outside, and the tip of a front wing 33 and the main wing 31 is fixed in both three wings. A large passenger airplane is improved in stability, and the outside of a main wing of a voyager type is too long, but brings about the same effect as a wing of an outside part is installed inside the sub-fuselage 32. Thus, the airframe can be made compact, and strength of the whole airframe can be increased.

93. 发明专利

JPH0710088A HIGH-LIFT AIRCRAFT 失效
公开(公告)号：JPH0710088A
公开(公告)日：1995-01-13
申请号：JP17859393
申请日：1993-06-28
申请人： SHIN MEIWA IND CO LTD
发明人： HARA KOSABURO
IPC分类号： B64C9/00 , B64C39/12
摘要： PURPOSE:To provide an aircraft which can fly with high lift during the taking- off and landing on the ground (or water). CONSTITUTION:An aircraft is provided with main wings 22, a vertical tail 23, and horizontal ailerons 24 provided forward of the main wings 22. The aerodymanical center C in the high-lift condition during the taking-off and landing is moved on the main wings 22 afterward of the position when flying at the cruising speed. Thus, the lift is changed into the moment around the center of gravity G and the moment is applied on the aircraft body in the direction to lower the head of the aircraft body 21 (the leading edge of the aircraft body 21). On the other hand, in order to cancel this moment, the lift to generate the moment in the direction to lift the head of the aircraft body 21 is generated upward on the horizontal ailerons 2 4. Thus, the aircraft 20 takes off or is landed in the high-lift condition where the lift is increased by the horizontal ailerons 24.

94. 实用新型

JPH037098U 失效
公开(公告)号：JPH037098U
公开(公告)日：1991-01-23
申请号：JP6610690
申请日：1990-06-25
IPC分类号： B64C39/12

95. 发明专利

JPH01254497A AIRCRAFT USING MICROWAVE AS POWER 失效
公开(公告)号：JPH01254497A
公开(公告)日：1989-10-11
申请号：JP29591788
申请日：1988-11-22
申请人： JIYON EFU MAACHIN , JIEEMUZU DEII DOUROORIE , JIYOOJI W JIYURU , AANI RIRUMAAKU
发明人： JIYON EFU MAACHIN , JIEEMUZU DEII DOUROORIE , JIYOOJI DABURIYU JIYURU , AANI RIRUMAAKU
IPC分类号： A63H29/22 , B64C39/02 , B64C39/12 , B64D27/24
摘要： PURPOSE: To reduce a cost by providing the body of rectenna on the lower side of an aircraft, in the means for receiving and rectifying microwave energy, and making the principal dimension of the body have the dimension of a shape which is extending in horizontal being relatively shallow, and moreover at least actually avoiding the generation of lift due to the body. CONSTITUTION: A rectenna body 25 is designed so as to avoid the generation of lift and drag for widening a rectenna area, and for this purpose, has an eliptic cross section in a flow direction, and moreover has no sharp trailing edge so as to avoid the generation of lift. In wings 22, a high aspect ratio having proper efficiency in aerodynamics can be obtained by thus separating a lift surface region, that is, the wings 22, from the lens type body 25 of rectenna. Consequently power required to the flight of an aircraft can be considerably reduced without increasing a required power flux density in a microwave beam utilized for feeding its own power to the aircraft.

96. 发明专利

JPS58128999A IMPROVED AIRCRAFT 失效
公开(公告)号：JPS58128999A
公开(公告)日：1983-08-01
申请号：JP9293982
申请日：1982-05-31
申请人： INDEYUSUTORIE AERONOUTEIKE E M
发明人： ARETSUSANDORO MATSUZOONI
IPC分类号： B64C39/12

97. 发明专利

JPS5019000B1 失效
公开(公告)号：JPS5019000B1
公开(公告)日：1975-07-03
申请号：JP12115270
申请日：1970-12-29
IPC分类号： F42B10/02 , B64C5/04 , B64C23/06 , B64C39/12

98. 发明专利

JP4646543B2 For the movable wing of the aircraft, to operate the rotatable member device 有权
公开(公告)号：JP4646543B2
公开(公告)日：2011-03-09
申请号：JP2004133508
申请日：2004-04-28
申请人：ザ・ボーイング・カンパニーThe Boeing Company
发明人：ケリー・ティ・ジョーンズ
IPC分类号： B64C13/24 , B64C1/00 , B64C5/04 , B64C5/16 , B64C9/02 , B64C13/30 , B64C39/12
CPC分类号： B64C5/04 , B64C5/16 , B64C9/02 , B64C13/30 , B64C39/12

99. 发明专利

JP3947697B2 Glide kite airplane 有权
公开(公告)号：JP3947697B2
公开(公告)日：2007-07-25
申请号：JP2002275022
申请日：2002-09-20
申请人：隆二本庄
发明人：隆二本庄
IPC分类号： B64C31/06 , A63H27/08 , B64C29/00 , B64C39/12

100. 发明专利

JP2005319970A Flight vehicle, and mode switching method of flight vehicle 有权
标题翻译：飞行车辆和飞行器的模式切换方法
公开(公告)号：JP2005319970A
公开(公告)日：2005-11-17
申请号：JP2004141623
申请日：2004-05-11
申请人： Mitsubishi Heavy Ind Ltd , 三菱重工業株式会社
发明人： NAKAO MASAHIRO
IPC分类号： B64C27/22 , B64C27/10 , B64C29/00 , B64C39/12
摘要： PROBLEM TO BE SOLVED: To provide a flight vehicle having a long movable time and a broad operation range, and a mode switching method of the flight vehicle.
SOLUTION: The flight vehicle 1 comprises a columnar body 2 extending in the direction of a vehicle axis, a rotor blade 3 disposed in the columnar body 2 rotatably about the rotation axis parallel with the vehicle axis, a driving device for rotating and driving the rotor blade 3, a propelling device 13 for generating the thrust toward the nose, and a mode switching device for switching an operation form of this flight vehicle 1 to one of hovering mode or flight mode. The rotor blade 3 has a plurality of blades 3c arranged radially about the rotation axis with adjustable pitch. As the mode switching device, the flight vehicle has a fixing device for fixing positions about the rotation axis of the rotor blade 3 with respect to the body 2 in the flight mode, and a pitch angle adjusting device for turning the leading edge F of each blade 3c in the rotation direction of the rotor blade 3 in the hovering mode and turning the leading edge of each blade 3c to the nose side in the flight mode.
COPYRIGHT: (C)2006,JPO&NCIPI
摘要翻译：要解决的问题：提供一种具有漫长的可移动时间和宽的操作范围的飞行器以及飞行器的模式切换方法。解决方案：飞行器1包括沿着车辆轴线方向延伸的柱状体2，围绕平行于车辆轴线的旋转轴可旋转地设置在柱状体2中的转子叶片3，驱动转子叶片3，用于产生朝向鼻子的推力的推进装置13和用于将该飞行车辆1的操作形式切换成盘旋模式或飞行模式之一的模式切换装置。转子叶片3具有多个叶片3c，其以可调节的间距围绕旋转轴径向放置。作为模式切换装置，飞行器具有用于在飞行模式下相对于主体2固定围绕转子叶片3的旋转轴线的位置的定影装置，以及用于转动每个的前缘F的俯仰角调节装置在转子叶片3的旋转方向上以悬停模式旋转叶片3c，并且在飞行模式下将每个叶片3c的前缘转动到前端。版权所有（C）2006，JPO＆NCIPI

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