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公开(公告)号：US09751619B1
公开(公告)日：2017-09-05
申请号：US15377300
申请日：2016-12-13
申请人： John V. Howard
发明人： John V. Howard
CPC分类号： B64C27/12 , B64C1/0009 , B64C25/02 , B64C25/04 , B64C27/04 , B64C27/10 , B64C39/024 , B64C2025/325 , B64C2201/024 , B64C2201/108 , B64C2201/12 , B64C2201/128 , B64C2211/00 , B64D1/22 , Y02T50/12
摘要： An unmanned rotorcraft has a lift module having a propulsion system and coaxial rotors driven in rotation by the propulsion system. The rotorcraft includes a payload support system adapted to couple an external payload directly to the lift module. The rotorcraft is devoid of provisions for human passengers.
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公开(公告)号：US4643663A
公开(公告)日：1987-02-17
申请号：US797686
申请日：1985-11-13
CPC分类号： B29C43/14 , B29C43/04 , B29C43/54 , B29K2105/24
摘要： An apparatus for molding a plurality of articles of hardenable material such as plastic which requires each article to be maintained under heat and pressure for a cure interval. A molding press is utilized wherein there is placed a first open mold assembly having spaced die halves between supporting mold platens. At least one of the die halves has a resilient pressure pad between the die and the mold platen supporting the die half. The press is closed to maintain the mold platens in a first force applying position having a slight gap between the die halves and locking the platens in the first position. The mold assembly is removed while in its first locked position from the press and gas from the curing material is evacuated through the gap between the die halves while heating the material. The mold assembly in its first locked position is again placed in the press and the press is closed to unlock the mold assembly and apply and maintain a second molding force greater then the first molding force and sufficient to completely close the die halves to a second position for curing the material and compress the resilient pressure pad. The mold platens are locked in the second position whereby the pressure pad will apply internal forces against the dies to maintain the correct curing pressure in the event of shrinkage of the cured material. The mold assembly is removed from the press in its second locked position and the material is cured under pressure and at elevated temperatures for the correct time interval to form the article. Finally, the mold assembly is unlocked and the article is removed therefrom.
摘要翻译： 一种用于模制多个可硬化材料如塑料的制品的装置，其需要每个制品在加热和压力下保持固化间隔。 使用成型压力机，其中放置有在支撑模板之间具有间隔的半模的第一开放模具组件。 半模中的至少一个在模具和支撑半模之间的模板之间具有弹性压力垫。 压力机关闭以将模具压板保持在第一力施加位置，在模具半部之间具有轻微的间隙并将压板锁定在第一位置。 模具组件在从压机处于其第一锁定位置的同时被移除，并且来自固化材料的气体在加热材料的同时通过模具半部之间的间隙被抽空。 将模具组件处于其第一锁定位置再次放置在压力机中并且压力机关闭以解锁模具组件，并且施加并保持第二模制力大于第一模制力并且足以将模具半部完全封闭到第二位置 用于固化材料并压缩弹性压力垫。 模具压板被锁定在第二位置，由此压力垫将在模具的内部施加内力，以在固化材料收缩的情况下保持正确的固化压力。 模具组件在其第二锁定位置从压机中移除，并且材料在压力和升高的温度下固化正确的时间间隔以形成制品。 最后，模具组件被解锁并且物品被从中去除。
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公开(公告)号：US09498367B1
公开(公告)日：2016-11-22
申请号：US14644646
申请日：2015-03-11
申请人： John V Howard
发明人： John V Howard
IPC分类号： A61F5/042
CPC分类号： A61H1/0229 , A61F5/042 , A61H1/0222 , A61H1/0255 , A61H1/0292 , A61H33/00 , A61H33/02 , A61H2201/0111 , A61H2201/0115 , A61H2201/0157 , A61H2201/0192 , A61H2201/1215 , A61H2201/1253 , A61H2201/14 , A61H2201/1445 , A61H2201/149 , A61H2201/1623 , A61H2201/1635 , A61H2201/164 , A61H2201/1664 , A61H2201/1676 , A61H2203/02 , A61H2203/0406 , A61H2203/0443 , A61H2203/045 , A61H2205/081 , A61H2205/108
摘要： An apparatus for applying traction force to a spine of a user has a chassis with an upper surface. A user lies on the upper surface with the spine extending generally parallel to a longitudinal axis of the chassis. Two members extend from the chassis on opposing sides of the longitudinal axis, each member being positioned to engage an armpit. A lever is pivotally attached to the chassis for rotation about a lateral axis, and a pad coupled to the lever contacts a proximal portion of each upper leg when the leg is bent forward at a hip joint. A force applied to the lever is transmitted through the pad to each upper leg and opposed by the members, thereby applying traction force for decompressing the spine. The force may be applied by the arms of the user or by a motor.
摘要翻译： 用于将牵引力施加到使用者的脊椎的装置具有带有上表面的底盘。 使用者位于上表面上，脊柱大致平行于底盘的纵向轴线延伸。 两个构件在纵向轴线的相对侧上从底盘延伸，每个构件被定位成接合腋窝。 杠杆枢转地附接到底盘以围绕横向轴线旋转，并且当腿部在髋关节处向前弯曲时，联接到杠杆的垫接触每个大腿的近端部分。 施加到杠杆的力通过垫传递到每个大腿并且由构件相对，从而施加用于减压脊柱的牵引力。 力可以由使用者的臂或电动机施加。
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公开(公告)号：US07950605B2
公开(公告)日：2011-05-31
申请号：US12568442
申请日：2009-09-28
IPC分类号： B64D27/00
CPC分类号： B64D27/26 , B64C27/14 , B64C27/28 , B64C29/0033 , B64D27/12 , B64D2027/266 , B64F5/60 , F02C7/20 , F02C7/36 , Y02T50/44 , Y02T50/671
摘要： A torsionally de-coupled engine mount system for use in tilt rotor aircraft applications is disclosed, in which an engine is mounted at its forward end to a prop rotor gear box by means of a forward mount that is a simple adapter fitting, and at its aft end to a pylon assembly by an aft mount that is a simple bi-pod fitting. The forward mount counteracts forces and moments in six degrees of freedom, but the aft mount only counteracts lateral and vertical loads. The contribution from the engine to the overall dynamic response of the aircraft is tuned by selectively tailoring the size, shape, weight, and material of the forward mount. The engine mount system torsionally de-couples the engines from the prop rotors, thereby preventing rotor torque from being induced into the engines. In addition, the contribution from the engines to the overall dynamic response of the aircraft can be tuned by selectively tailoring the size, shape, weight, and material of the forward mounts between the engines and the transmissions.
摘要翻译： 公开了一种用于倾斜转子飞机应用的扭转解耦发动机安装系统，其中发动机借助于作为简单的适配器配件的前悬架在其前端安装到支柱转子齿轮箱，并且在其 后端通过一个简单的双荚配件的尾座安装在塔架组件上。 前向安装抵消六自由度的力量和力矩，但是后部安装仅抵消横向和垂直载荷。 通过选择性地调整前悬架的尺寸，形状，重量和材料来调整发动机对飞机整体动态响应的贡献。 发动机安装系统使发动机与支承转子扭转地解耦，从而防止转子扭矩被引入发动机。 此外，可以通过选择性地调整发动机和变速器之间的前悬架的尺寸，形状，重量和材料来调节来自发动机对飞行器的整体动态响应的贡献。
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公开(公告)号：US06244538B1
公开(公告)日：2001-06-12
申请号：US09314399
申请日：1999-05-19
IPC分类号： B64C2552
CPC分类号： B64C25/52 , B64C2025/325
摘要： A skid landing gear for a helicopter, in which the directional stiffnesses of the cross members of the skid landing gear have been de-coupled from one another, such that optimization of the longitudinal stiffness of the cross members may be performed independently of the optimization of the vertical stiffness and fatigue life of the cross members. In order to de-couple the stiffnesses in the skid type landing gear, two approaches are employed. In the first approach, the skid landing gear has non-symmetric-section cross members and/or distribution of different materials within the cross-section for de-coupling the vertical stiffness of the cross members from the longitudinal stiffness, such that placement of the ground resonance frequency may be optimized, while retaining the vertical stiffness properties essential for optimizing vertical energy attenuation and fatigue life. In the second approach, mounting devices are employed that provide compliance in selected directions, thereby de-coupling the directional stiffnesses.
摘要翻译： 用于直升机的防滑起落架，其中滑行起落架的横向构件的方向刚度已经彼此脱离，使得横向构件的纵向刚度的优化可以独立于优化 横梁的垂直刚度和疲劳寿命。 为了解除滑行式起落架中的刚度，采用了两种方法。 在第一种方法中，防滑起落架具有不对称剖面的横向构件和/或横截面内的不同材料的分布，用于将横向构件的垂直刚度与纵向刚度解耦合，从而使 可以优化地面共振频率，同时保持垂直强度特性对于优化垂直能量衰减和疲劳寿命至关重要。 在第二种方法中，采用在所选方向上提供柔性的安装装置，从而解除方向刚度。
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公开(公告)号：US10112707B1
公开(公告)日：2018-10-30
申请号：US15491701
申请日：2017-04-19
申请人： John V. Howard
发明人： John V. Howard
摘要： An unmanned rotorcraft has a lift module having a propulsion system and coaxial rotors driven in rotation by the propulsion system. The rotorcraft includes a payload support system adapted to couple an external payload directly to the lift module. The rotorcraft is devoid of provisions for human passengers.
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7.发明授权Remotely controlled co-axial rotorcraft for heavy-lift aerial-crane operations 有权用于重型起重机操作的遥控同轴旋翼航空器公开(公告)号：US09517838B1
公开(公告)日：2016-12-13
申请号：US14872885
申请日：2015-10-01
申请人： John V. Howard
发明人： John V. Howard
CPC分类号： B64C27/12 , B64C1/0009 , B64C25/02 , B64C25/04 , B64C27/04 , B64C27/10 , B64C39/024 , B64C2025/325 , B64C2201/024 , B64C2201/108 , B64C2201/12 , B64C2201/128 , B64C2211/00 , B64D1/22 , Y02T50/12
摘要： A helicopter has a lift module having a propulsion system and at least one rotor driven in rotation by the propulsion system. A payload support system is adapted to couple an external payload directly to the lift module. The helicopter is devoid of provisions for human passengers.
摘要翻译： 直升机具有升降机模块，其具有推进系统和至少一个由推进系统驱动旋转的转子。 有效载荷支持系统适于将外部有效负载直接耦合到电梯模块。 直升机没有为人员提供配备。
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公开(公告)号：US20100012775A1
公开(公告)日：2010-01-21
申请号：US12568442
申请日：2009-09-28
CPC分类号： B64D27/26 , B64C27/14 , B64C27/28 , B64C29/0033 , B64D27/12 , B64D2027/266 , B64F5/60 , F02C7/20 , F02C7/36 , Y02T50/44 , Y02T50/671
摘要： A torsionally de-coupled engine mount system for use in tilt rotor aircraft applications is disclosed, in which an engine is mounted at its forward end to a prop rotor gear box by means of a forward mount that is a simple adapter fitting, and at its aft end to a pylon assembly by an aft mount that is a simple bi-pod fitting. The forward mount counteracts forces and moments in six degrees of freedom, but the aft mount only counteracts lateral and vertical loads. The contribution from the engine to the overall dynamic response of the aircraft is tuned by selectively tailoring the size, shape, weight, and material of the forward mount. The engine mount system torsionally de-couples the engines from the prop rotors, thereby preventing rotor torque from being induced into the engines. In addition, the contribution from the engines to the overall dynamic response of the aircraft can be tuned by selectively tailoring the size, shape, weight, and material of the forward mounts between the engines and the transmissions.
摘要翻译： 公开了一种用于倾斜转子飞机应用的扭转解耦发动机安装系统，其中发动机借助于作为简单的适配器配件的前悬架在其前端安装到支柱转子齿轮箱，并且在其 后端通过一个简单的双荚配件的尾座安装在塔架组件上。 前向安装抵消六自由度的力量和力矩，但是后部安装仅抵消横向和垂直载荷。 通过选择性地调整前悬架的尺寸，形状，重量和材料来调整发动机对飞机整体动态响应的贡献。 发动机安装系统使发动机与支承转子扭转地解耦，从而防止转子扭矩被引入发动机。 此外，可以通过选择性地调整发动机和变速器之间的前悬架的尺寸，形状，重量和材料来调节来自发动机对飞行器的整体动态响应的贡献。
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公开(公告)号：US07594623B2
公开(公告)日：2009-09-29
申请号：US10528213
申请日：2002-09-17
IPC分类号： B64D27/00
CPC分类号： B64D27/26 , B64C27/14 , B64C27/28 , B64C29/0033 , B64D27/12 , B64D2027/266 , B64F5/60 , F02C7/20 , F02C7/36 , Y02T50/44 , Y02T50/671
摘要： A torsionally de-coupled engine mount system (13) for use in tilt rotor aircraft (11) applications is disclosed, in which an engine is mounted at its forward end to a prop rotor gear box by means of a forward mount (303) that is a simple adapter fitting, and at its aft end to a pylon assembly by an aft mount (305) that is a simple bi-pod fitting. The forward mount (303) counteracts forces and moments in six degrees of freedom, but the aft mount (305) only counteracts lateral and vertical loads. The contribution from the engine to the overall dynamic response of the aircraft is tuned by selectively tailoring the size, shape, weight, and material of the forward mount (303). The engine mount system torsionally de-couples the engines from the prop rotors, thereby preventing rotor torque from being induced into the engines. In addition, the contribution from the engines to the overall dynamic response of the aircraft can be tuned by selectively tailoring the size, shape, weight, and material of the forward mounts between the engines and the transmissions.
摘要翻译： 公开了一种用于倾斜转子飞机（11）应用中的扭转解耦发动机安装系统（13），其中发动机借助于前部安装件（303）在其前端安装到支柱转子齿轮箱， 是一个简单的适配器配件，并在其后端通过一个简单的双荚配件的尾座（305）连接到一个塔架组件。 前支架（303）在六自由度上抵抗力和力矩，但是后部安装座（305）仅抵消横向和垂直载荷。 通过选择性地调整前悬架（303）的尺寸，形状，重量和材料来调节从发动机到飞行器整体动态响应的贡献。 发动机安装系统使发动机与支承转子扭转地解耦，从而防止转子扭矩被引入发动机。 此外，可以通过选择性地调整发动机和变速器之间的前悬架的尺寸，形状，重量和材料来调节来自发动机对飞行器的整体动态响应的贡献。
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公开(公告)号：US4336868A
公开(公告)日：1982-06-29
申请号：US91880
申请日：1979-11-07
CPC分类号： B64D25/00 , B64C25/60 , F16F7/12 , B64C2025/325
摘要： High velocity impact landing forces are attenuated in apparatus (10) utilizing an energy absorbing tube (12) of composite fibrous material, that is, a fiber reinforced plastic. The energy absorbing tube (12) is disposed in force transmitting relation between an anvil (14) disposed at one end and structure (16) for applying a force to the opposite end of the tube (12) to provide force attenuating apparatus. The tube (12) is progressively crushed onto the anvil (14) by the force applying structure (16) to dissipate energy. The force attenuating apparatus (10) is used in an energy absorbing seat (20) to provide occupant protection against high impact forces. Other uses of the force attenuating apparatus (10) is in a landing gear mechanism (76) and a vehicle bumper system (89).
摘要翻译： 使用复合纤维材料的能量吸收管（12），即纤维增强塑料，设备（10）中的高速冲击着陆力减弱。 能量吸收管（12）设置成在一端设置的砧座（14）和用于向管（12）的另一端施加力的结构（16）之间的力传递关系，以提供力衰减装置。 管（12）通过施力结构（16）逐渐压碎到砧座（14）上以消散能量。 力衰减装置（10）用于能量吸收座（20）中，以提供乘员保护免受高冲击力。 力衰减装置（10）的其他用途在起落架机构（76）和车辆保险杠系统（89）中。
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