公开(公告)号：US6126118A

公开(公告)日：2000-10-03

申请号：US853273

申请日：1997-05-09

申请人： Michimasa Fujino ,  Yuichi Kawamura

发明人： Michimasa Fujino ,  Yuichi Kawamura

IPC分类号： B64C21/10 ,  B64C23/06 ,  F15D1/12

CPC分类号： B64D29/02 ,  B64C23/06 ,  B64C7/02 ,  Y02T50/162

摘要： A flow separation reducer comprises a vane which prevents an airflow from being separated in a flow interference region where a plurality of members, such as a main wing and a pylon, are joined to each other. The vane is disposed in a location where the airflow along a surface of one of the members develops a minimum negative pressure. The vane has a predetermined angle of attack with respect to the airflow for generating a vortex downstream of the vane with respect to the airflow and causing a circulation around the vane to reduce the speed of the airflow in the location.

摘要翻译： 流动分离减速器包括：叶片，其防止气流在诸如主翼和塔架的多个构件彼此接合的流动干涉区域中分离。 叶片设置在沿着其中一个构件的表面的气流产生最小负压的位置。 叶片相对于气流具有预定的迎角，用于相对于气流产生叶片下游的涡流，并引起叶片周围的循环，以降低该位置的气流速度。

公开(公告)号：US06308913B1

公开(公告)日：2001-10-30

申请号：US09264894

申请日：1999-03-09

申请人： Michimasa Fujino ,  Yuichi Kawamura

发明人： Michimasa Fujino ,  Yuichi Kawamura

IPC分类号： B64C138

CPC分类号： B64D29/02 ,  B64D27/18 ,  Y02T50/44

摘要： It is an object of the present invention to reduce the wave resistance by disposing a fluid element such as an engine nacelle in a predetermined position on the upper surface of the main wing, and positively superposing the air flow generated by the fluid element onto the air flow on the upper surface of the main wing, thereby reducing the peak of the negative pressure on the upper surface of the main wing to retard the generation of a shock wave. If the engine nacelle is disposed on the upper surface of the main wing, and the longitudinal position of the front end of the engine nacelle is established in a range of 63% to 100% from the front end of a wing chord of the main wing (see b and i in FIG. 9), a shock wave is generated on the upper surface of the main wing in a range of transonic speed to inhibit an increase in wave resistance, whereby the cruising speed can be increased, while avoiding an increase in amount of fuel consumed. If the front end of the engine nacelle is in front of a position corresponding to 63% of the wing chord (see e and f in FIG. 9), a shock wave inhibiting effect is not exhibited, and the wave resistance is increased.

摘要翻译： 本发明的目的是通过将诸如发动机舱的流体元件设置在主翼的上表面上的预定位置来降低波阻，并且将由流体元件产生的空气流积极地叠加到空气上 在主翼的上表面上流动，从而减小主翼上表面上的负压峰值，以阻止冲击波的产生。 如果发动机舱设置在主翼的上表面上，并且发动机舱的前端的纵向位置从主翼的翼弦的前端建立在63％至100％的范围内 （参见图9中的b和i），在跨音速的范围内在主翼的上表面产生冲击波，以抑制波阻的增加，从而可以提高巡航速度，同时避免增加 燃料消耗量。 如果发动机机舱的前端位于对应于翼和弦的63％的位置的前方（参见图9中的e和f），则不会发挥冲击波抑制效果，并且波阻增加。

公开(公告)号：USD687366S1

公开(公告)日：2013-08-06

申请号：US29403115

申请日：2011-09-30

申请人： Michimasa Fujino ,  Junichi Kondo ,  Chris Osborne

设计人： Michimasa Fujino ,  Junichi Kondo ,  Chris Osborne

公开(公告)号：US07093792B2

公开(公告)日：2006-08-22

申请号：US10373694

申请日：2003-02-27

申请人： Michimasa Fujino ,  Yoshinori Wariishi

发明人： Michimasa Fujino ,  Yoshinori Wariishi

IPC分类号： B64C3/14

CPC分类号： B64C3/14 ,  B64C2003/149 ,  Y02T50/12

摘要： An upper wing surface of a laminar-flow airfoil for decreasing an undesirable head-lowering pitching moment around an aerodynamic center of the airfoil. The upper wing surface includes: a convex front profile portion extending from a leading edge to a largest-thickness point located corresponding to 38% of a wing chord length. A convex central profile portion extends from the largest-thickness point to a position corresponding to 90% of the wing chord length at which a value obtained by dividing a thicknesswise difference between the position and the largest-thickness point by a distance in a direction of the wing chord from the largest-thickness point is equal to or smaller than 0.12. A concave rear profile portion extends from a position corresponding to 95% of the wing chord length to the trailing edge. The rear profile portion forms a pressure gradient is steeper than that formed by the central profile portion.

摘要翻译： 层流翼型的上翼面，用于减少围绕翼型的空气动力学中心的不希望的降低俯仰力矩。 上翼表面包括：从前缘延伸到对应于翼弦长度的38％的最大厚度点的凸形前轮廓部分。 凸起的中心轮廓部分从最大厚度点延伸到对应于翼弦长度的90％的位置，在该位置处，通过将位置和最大厚度点之间的厚度差除以距离 最大厚度点的翼和弦等于或小于0.12。 凹形后轮廓部分从对应于翼弦长度的95％的位置延伸到后缘。 后轮廓部分形成的压力梯度比由中心轮廓部分形成的压力梯度更陡。

公开(公告)号：US06834830B2

公开(公告)日：2004-12-28

申请号：US10373963

申请日：2003-02-27

申请人： Michimasa Fujino

发明人： Michimasa Fujino

IPC分类号： B64C300

CPC分类号： B64C3/28 ,  B64C3/14 ,  B64C2003/149 ,  Y02T50/12

摘要： A main wing structure comprises at least a leading edge structure and a wing central structure coupled to each other, and has a particular laminar-flow airfoil. The laminar-flow airfoil includes an upper wing surface, a lower wing surface, a leading edge and a trailing edge. The upper wing surface includes: a front profile portion which has a positive curvature radius, and which is provided to extend from the leading edge to a largest-thickness point located at 38% of a wing chord length; a central profile portion which has a positive curvature radius, and which is provided to extend from the largest-thickness point to the vicinity of a position corresponding to approximately 90% of the wing chord length at which a value obtained by dividing a thicknesswise difference between the position and the largest-thickness point by a distance in a direction of a wing chord from the largest-thickness point is equal to or smaller than 0.12; and a rear profile portion which has a negative curvature radius, and which is provided to extend from the vicinity of a position corresponding to approximately 95% of the wing chord length to the trailing edge. Coupled portions between the leading edge structure and the wing central structure are arranged at positions corresponding to approximately 20% of the wing chord length. Thus, it is possible to minimize an increase in drag due to a gap and a step between the coupled portions between the leading edge structure and the wing central structure.

摘要翻译： 主翼结构至少包括前缘结构和彼此连接的翼中心结构，并且具有特定的层流翼型。 层流翼型件包括上翼面，下翼面，前缘和后缘。 上翼面包括：前轮廓部分，其具有正的曲率半径，并且设置成从前缘延伸到位于翼弦长度的38％的最大厚度点; 具有正曲率半径的中心轮廓部分，并且被设置成从最大厚度点延伸到对应于翼弦长度的大约90％的位置附近，在该位置处， 距离最大厚度点的翼弦方向的位置和最大厚度点的距离等于或小于0.12; 以及具有负曲率半径的后轮廓部分，并且被设置成从对应于翼弦长度的大约95％的位置的附近延伸到后缘。 前缘结构和翼中心结构之间的耦合部分布置在对应于翼弦长度的大约20％的位置处。 因此，可以最小化由于前缘结构和翼中心结构之间的连接部分之间的间隙和台阶而引起的阻力的增加。

公开(公告)号：USD681543S1

公开(公告)日：2013-05-07

申请号：US29403104

申请日：2011-09-30

申请人： Michimasa Fujino ,  Greg John Geist ,  David Louis Krejsa ,  Chris Osborne

设计人： Michimasa Fujino ,  Greg John Geist ,  David Louis Krejsa ,  Chris Osborne

公开(公告)号：USD644165S1

公开(公告)日：2011-08-30

申请号：US29377039

申请日：2010-10-15

申请人： Michimasa Fujino ,  Chris Osborne

设计人： Michimasa Fujino ,  Chris Osborne

公开(公告)号：USD674734S1

公开(公告)日：2013-01-22

申请号：US29377021

申请日：2010-10-15

申请人： Michimasa Fujino ,  Chris Osborne

设计人： Michimasa Fujino ,  Chris Osborne

公开(公告)号：USD469054S1

公开(公告)日：2003-01-21

申请号：US29156659

申请日：2002-03-06

申请人： Michimasa Fujino

设计人： Michimasa Fujino

公开(公告)号：US5435504A

公开(公告)日：1995-07-25

申请号：US48691

申请日：1993-04-16

申请人： Kazuo Inoue ,  Michimasa Fujino ,  Yuva Otsuka ,  Tohru Fujihira

发明人： Kazuo Inoue ,  Michimasa Fujino ,  Yuva Otsuka ,  Tohru Fujihira

IPC分类号： B64C1/00 ,  B64C1/06 ,  B64C1/26 ,  B64C25/00

CPC分类号： B64C1/068 ,  B64C1/061 ,  B64C2001/0072 ,  Y02T50/433

摘要： An aircraft has an airframe including a fuselage having major structural members made of a composite material. The airframe also includes a sweepforward main wing mounted on top of the fuselage and a T or cruciform tail on the fuselage. The aircraft has no canard. The aircraft has a pair of main landing gear units attached to the fuselage below the main wing, the main landing gear units having short strut assemblies which allow the crew and passengers to get on and off the aircraft easily. The sweepforward main wing allows a wide and comfortable cabin space to be created in the fuselage.

摘要翻译： 飞机具有包括具有由复合材料制成的主要结构构件的机身的机身。 机身还包括安装在机身顶部的清扫主翼和机身上的T或十字形尾翼。 飞机没有胡子。 飞机有一对主起落架单元连接到主翼下方的机身，主起落架单元具有短的支柱组件，允许船员和乘客轻松上下飞机。 机身前后的主翼可以在机身中创建宽敞舒适的驾驶舱空间。