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1. 外观设计

USD342717S Aircraft 失效
公开(公告)号：USD342717S
公开(公告)日：1993-12-28
申请号：US1053
申请日：1992-10-29
申请人： Matthew N. Mrdeza , Daniel R. Rihn , Barnaby S. Wainfan
设计人： Matthew N. Mrdeza , Daniel R. Rihn , Barnaby S. Wainfan

2. 外观设计

USD495779S1 Spray gun apparatus 失效
标题翻译：喷枪装置
公开(公告)号：USD495779S1
公开(公告)日：2004-09-07
申请号：US29188226
申请日：2003-08-13
申请人： Clifford W. Turnbull , Matthew N. Mrdeza , David L. Stocks
设计人： Clifford W. Turnbull , Matthew N. Mrdeza , David L. Stocks

3. 发明授权

US5984231A Aircraft with variable forward-sweep wing 失效
标题翻译：具有可变前掠翼的飞机
公开(公告)号：US5984231A
公开(公告)日：1999-11-16
申请号：US100738
申请日：1998-06-19
申请人： Heinz A. Gerhardt , Kenneth Seho , Joan Nolan , Matthew N. Mrdeza
发明人： Heinz A. Gerhardt , Kenneth Seho , Joan Nolan , Matthew N. Mrdeza
IPC分类号： B64C3/40 , B64C5/04
CPC分类号： B64C5/04 , B64C3/40
摘要： An aircraft with a variable forward-sweep wing and the method of configuring the wing in an optimal position for a desired flight regime. The variable forward-sweep wing is positionable from an essentially unswept position to a full-forward sweep position. In the unswept position the wing is approximately orthogonal to a fuselage centerline, while in the full-forward sweep position the wing has approximately a delta wing planform. Moreover, as the wing position changes from the unswept position to the full-forward sweep position the trailing edge becomes the leading edge. In addition, the aforementioned apparatus may be used in a method to configure the aircraft for flight in a desired flight regime. This method includes moving the wing to an optimal position for the desired flight regime.
摘要翻译：具有可变向前扫掠翼的飞机以及将机翼配置在所需飞行状态的最佳位置的方法。可变向前扫掠翼可从基本上未被扫描的位置定位到全向扫掠位置。在未完成的位置，机翼大致垂直于机身中心线，而在全向扫掠位置，机翼具有大约三角形机翼平面图。此外，当翼位置从未扫描位置改变到全向扫掠位置时，后缘成为前缘。此外，上述装置可以用于以期望的飞行方式来配置飞行器的飞行方法。该方法包括将机翼移动到所需飞行状态的最佳位置。

4. 外观设计

USD365545S Airplane 失效
公开(公告)号：USD365545S
公开(公告)日：1995-12-26
申请号：US28199
申请日：1994-09-09
申请人： Barnaby S. Wainfan , Matthew N. Mrdeza
设计人： Barnaby S. Wainfan , Matthew N. Mrdeza

5. 发明授权

US07159423B1 Helmet locking device 有权
标题翻译：头盔锁定装置
公开(公告)号：US07159423B1
公开(公告)日：2007-01-09
申请号：US11015118
申请日：2004-11-18
申请人： Matthew N. Mrdeza , Joseph B. Gschweng
发明人： Matthew N. Mrdeza , Joseph B. Gschweng
IPC分类号： E05B69/00
CPC分类号： B62J11/005 , B62K21/26 , Y10T70/441 , Y10T70/5013 , Y10T70/5872 , Y10T74/20822
摘要： A motorcycle helmet lock securely grasps a metal strap ring (or D ring) of a helmet strap to prevent helmet theft. The helmet lock includes a groove suitable to accept the strap ring and a locking bolt to advance through the strap ring to secure the helmet. The lock may be an integral part of a motorcycle grip or foot peg, may bolt to a common accessory attachment interface of known motorcycle grips, or include an expanding portion which expands inside a tubular handlebar end to attach the helmet lock. The lock may further be used on any type of vehicle using handlebars for foot pegs.
摘要翻译：摩托车头盔锁牢固地抓住头盔皮带的金属吊环（或D型环），以防止头盔被盗。头盔锁包括适于接收带环的凹槽和锁定螺栓，以通过带环前进以固定头盔。锁可以是摩托车把手或脚钉的组成部分，可以螺栓连接到已知摩托车把手的公共附件附接界面，或者包括在管状把手端部内扩张以附接头盔锁的扩张部。锁可以进一步用在任何类型的车辆上，使用用于脚钉的把手。

6. 外观设计

USD505072S1 Spray gun trigger 失效
公开(公告)号：USD505072S1
公开(公告)日：2005-05-17
申请号：US29182636
申请日：2003-05-28
申请人： Clifford W. Turnbull , Matthew N. Mrdeza , David L. Stocks
设计人： Clifford W. Turnbull , Matthew N. Mrdeza , David L. Stocks

7. 发明授权

US5961068A Aerodynamic control effector 失效
标题翻译：气动控制效应器
公开(公告)号：US5961068A
公开(公告)日：1999-10-05
申请号：US956559
申请日：1997-10-23
申请人： Barnaby S. Wainfan , Matthew N. Mrdeza
发明人： Barnaby S. Wainfan , Matthew N. Mrdeza
IPC分类号： B64C3/10 , B64C5/02 , B64C9/02 , B64C1/00 , B64C5/06 , B64C9/00
CPC分类号： B64C3/10 , B64C5/02 , B64C9/02
摘要： An aerodynamic control system for an aircraft comprises a pair of low-aspect-ratio strakes integral with the fuselage, each of the strakes being substantially co-planar with an associated one of the wings and extending between a leading region generally blended with the trailing edge of the wing, a trailing edge and an outer edge. An aft airfoil is pivotally mounted to the trailing edge of each of the strakes movable between an extreme positive angle of attack position and an extreme negative angle of attack position. The aft airfoil includes an inner airfoil member which is laterally coextensive with said trailing edge of said associated strake and an outer airfoil member integral with the inner airfoil member which extends laterally beyond the outer edge of the associated strake. In one embodiment, the outer and inner airfoil members are substantially co-planar. In other embodiments, the outer airfoil member may be canted either upwardly or downwardly with respect to the inner airfoil member. In still other embodiments, the trailing edges of the strakes may either extend substantially perpendicular to the longitudinal axis of the fuselage, or extend forwardly or rearwardly with increasing distance away from the fuselage. Also, the strakes may have the construction of chines which are smoothly blended with the outer surface of the fuselage.
摘要翻译：一种用于飞行器的空气动力学控制系统包括一对与机身一体的低纵横比的滑轮，每个翼片与相关联的一个翼部基本上共面，并且在通常与后缘的翼，后缘和外边缘。后翼形件可枢转地安装在每个条带的后缘之间，可在极限正角攻击位置与极端负角攻击位置之间移动。后翼型件包括与所述相关的行星架的所述后缘横向共同延伸的内部翼型件，以及与所述内部翼型件成一体的外部翼型件，所述外部翼型件横向延伸超过相关的行李架的外边缘。在一个实施例中，外部和内部翼型构件基本上共面。在其它实施例中，外翼型构件可以相对于内翼型构件向上或向下倾斜。在其他实施例中，斜面的后缘可以基本上垂直于机身的纵向轴线延伸，或者以距离机身增加的距离向前或向后延伸。此外，该横带可以具有与机身的外表面平滑混合的中心构造。

8. 发明授权

US5366180A High-lift device for aircraft 失效
标题翻译：飞机高架设备
公开(公告)号：US5366180A
公开(公告)日：1994-11-22
申请号：US85441
申请日：1993-06-30
申请人： Barnaby S. Wainfan , Matthew N. Mrdeza
发明人： Barnaby S. Wainfan , Matthew N. Mrdeza
IPC分类号： B64C5/04 , B64C5/12 , B64C39/08
CPC分类号： B64C39/08 , B64C5/04 , B64C5/12
摘要： High lift producing apparatus for an aircraft includes a pair of foreplanes, one for each side of the aircraft, each foreplane extending between a root end at the fuselage and a distant tip end. Wings are mounted on the fuselage aft of the foreplanes and, intermediate the wings and the foreplanes, are a pair of strakes which are generally coplanar with their associated foreplanes and strakes, a leading edge of each strake being substantially coincident with a trailing edge of its associated foreplane, and a trailing edge of each strake being substantially coincident with a leading edge of its associated wing. The span of the strakes is smaller than the span of the foreplanes at the location of intersection of said strake and said foreplane. Each foreplane may be pivotally mounted on the fuselage at its root end on a stationary hinge axis which is substantially parallel with the longitudinal axis of the aircraft. The foreplanes are thereby movable between inactive positions flush with a contoured outer surface of the fuselage and deployed positions at which tip ends are distant from the fuselage. The foreplanes may also be pivotally mounted on lateral axes for control purposes. In one instance, the foreplanes can be simultaneously moved in the same direction about their associated lateral axes to achieve pitch control of the aircraft; in other instances, they can be independently moved about their associated lateral axes to achieve either yaw control or roll control.
摘要翻译：用于飞行器的高升力产生装置包括一对前翼，一个用于飞行器的每一侧，每个前翼在机身的根端和远端之间延伸。翅膀安装在前翼的机身后部，并且在机翼和前平面之间，是一对通常与其相关联的前平面和斜面共面的斜条，每个斜条的前缘基本上与其前缘相重合相关联的前平面，并且每个条带的后缘基本上与其相关翼的前缘重合。在所述板条和所述前板的交叉位置处，所述跨距的跨度小于所述前平面的跨度。每个前平面可以在其根部处以固定的铰链轴线枢转地安装在机身上，固定的铰链轴线基本上与飞行器的纵向轴线平行。因此，前平面可在与机身的轮廓外表面齐平的非活动位置之间移动，并且展开位置，其末端远离机身。为了控制目的，前平面也可以枢转地安装在横轴上。在一种情况下，前平面可以沿着相关联的横向轴线在相同的方向上同时移动，以实现飞机的俯仰控制; 在其他情况下，它们可以独立地围绕其相关联的横向轴线移动，以实现偏航控制或侧倾控制。

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