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1. 外观设计

USD687366S1 Pair of aircraft windows 有权
标题翻译：一对飞机窗户
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

2. 外观设计

USD644165S1 Aircraft with exterior surface ornamentation 有权
标题翻译：具有外表面装饰的飞机
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

3. 外观设计

USD681543S1 Aircraft fuselage lights 有权
标题翻译：飞机机身灯
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

4. 外观设计

USD674734S1 Aircraft with exterior surface ornamentation 有权
标题翻译：具有外表面装饰的飞机
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

5. 外观设计

USD687365S1 Aircraft windshield 有权
公开(公告)号：USD687365S1
公开(公告)日：2013-08-06
申请号：US29403112
申请日：2011-09-30
申请人： Junichi Kondo , Michimasa Fujino
设计人： Junichi Kondo , Michimasa Fujino

6. 发明授权

US07093792B2 Laminar-flow airfoil 有权
标题翻译：层流翼型
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。

7. 发明授权

US06834830B2 Main wing structure 有权
标题翻译：主翼结构
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。

8. 外观设计

USD469054S1 Airplane 失效
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

9. 发明授权

US6126118A Flow separator reducer 失效
标题翻译：流量分离器减速机
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。

10. 发明授权

US5435504A Aircraft 失效
标题翻译：飞机
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。

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