公开(公告)号：US20050151007A1

公开(公告)日：2005-07-14

申请号：US10770130

申请日：2004-02-03

申请人： David Cadogan ,  David Graziosi ,  Grant Lee ,  Stephen Scarborough ,  Timothy Smith

发明人： David Cadogan ,  David Graziosi ,  Grant Lee ,  Stephen Scarborough ,  Timothy Smith

IPC分类号： B64C20060101 ,  B64C3/00 ,  B64C3/56 ,  B64C39/02

CPC分类号： B64C39/024 ,  B64C3/56 ,  B64C2201/105

摘要： A novel design and construction method for an inflatable, rigidizable wing for a terrestrial or planetary flying vehicle. The wing is caused to deploy from an initially packed condition and to assume its functional shape by means of an inflation gas. After inflation, the wing is rigidized by any of several means, such that the inflation gas is no longer required. The composite wing is fabricated from a base reinforcement material, often a fabric, which is coated with a polymer resin that hardens when exposed to a curing mechanism. Several activation mechanisms exist by which to initiate rigidization of such a structure, including elevated temperature, ultraviolet light, and chemical constituents of the inflation gas. The resultant wing has fundamental advantages compared to existing inflatable wings, including improved stiffness, and reduced susceptibility to structural failure in response to puncture.

摘要翻译： 一种用于陆地或行星飞行器的可充气，可固定翼的新颖设计和施工方法。 使机翼从初始包装状态部署，并通过充气气体承担其功能形状。 在膨胀之后，机翼通过几种手段中的任何一种来固定，使得不再需要膨胀气体。 复合翼片由基底增强材料制成，通常是织物，其涂覆有当暴露于固化机构时硬化的聚合物树脂。 存在几种启动机制，其通过其启动这种结构的刚性化，包括升高的温度，紫外线和膨胀气体的化学成分。 所得到的翼片与现有的充气翼相比具有基本的优点，包括改善的刚度，以及降低响应于穿刺的结构失效的敏感性。

公开(公告)号：US4247061A

公开(公告)日：1981-01-27

申请号：US923834

申请日：1978-07-12

申请人： William A. Kuczynski ,  John Marshall, II, deceased

发明人： William A. Kuczynski ,  John Marshall, II, deceased

IPC分类号： B64C27/06 ,  B64C20060101 ,  B64C1/16 ,  B64C1/26 ,  B64C5/10 ,  B64C9/02 ,  B64C9/08 ,  B64C27/00 ,  B64C27/04 ,  F16F15/00 ,  F16F15/04

CPC分类号： B64C1/00 ,  B64C1/16 ,  B64C1/26 ,  B64C27/00 ,  B64C27/04 ,  B64C27/06 ,  B64C5/10 ,  B64C9/02 ,  B64C9/08 ,  F16F15/02

摘要： A helicopter stabilator having naturally high response to the main rotor wake excitation frequency in roll and yaw stabilator vibratory modes is selectively mounted so as to be detuned therefrom in antisymmetric stabilator vibratory modes without adversely affecting symmetric stabilator vibratory modes, stabilator vertical stiffness, or stabilator pitch stiffness.

摘要翻译： 选择性地安装在滚动和偏航稳定器振动模式中对主转子唤醒激励频率具有自然高响应的直升机稳定器，以便以反对称稳定器振动模式与其失谐，而不会不利地影响对称稳定器振动模式，稳定器垂直刚度或稳定器音调 刚性。

公开(公告)号：US4534524A

公开(公告)日：1985-08-13

申请号：US539119

申请日：1983-10-05

申请人： Allyn M. Aldrich

发明人： Allyn M. Aldrich

IPC分类号： B64C20060101 ,  B64C11/32 ,  B64C27/58 ,  B64C27/59 ,  B64C27/72 ,  B64C27/605

CPC分类号： B64C27/58 ,  B64C11/32

摘要： A helicopter blade position and control mechanism including a hollow rotor shaft for mounting a plurality of rotor blades with provision for pitch adjustment. A control shaft is disposed within the rotor shaft and is rotatable relative thereto and is associated with actuators for the blades such that the pitch of the blades is changed when the control shaft rotates relative to the rotor shaft. A planetary gear assembly interconnects the control shaft and a source of power fixed to the helicopter fuselage and is such that when an input to the planetary gear assembly is quiescent, the control shaft will rotate in the same direction and at the same rate as the rotor shaft to maintain a desired blade pitch. Conversely, when an input is placed on the planetary gear system, relative rotation between the control shaft and the rotor shaft will occur to provide the desired adjustment in blade pitch. The system allows accurate blade position feedback signals to be taken from a feedback device stationarily mounted on the fuselage.

摘要翻译： 一种直升机叶片位置和控制机构，包括用于安装多个转子叶片的中空转子轴，用于调节桨距。 控制轴设置在转子轴内并且可相对于其转动并与叶片的致动器相关联，使得当控制轴相对于转子轴转动时叶片的间距改变。 行星齿轮组件将控制轴和固定到直升机机身的动力源相互连接，并且使得当行星齿轮组件的输入静止时，控制轴将以与转子相同的方向和速度旋转 轴以保持期望的叶片间距。 相反，当输入被放置在行星齿轮系统上时，将发生控制轴和转子轴之间的相对旋转以提供叶片间距期望的调节。 该系统允许从固定安装在机身上的反馈装置获取精确的刀片位置反馈信号。

公开(公告)号：US20050151001A1

公开(公告)日：2005-07-14

申请号：US10871028

申请日：2004-06-21

申请人： Arthur Loper

发明人： Arthur Loper

IPC分类号： B64C20060101 ,  B64C27/22

CPC分类号： B64C27/26 ,  B64C27/14 ,  B64C2027/8281

摘要： The compound helicopter is a hybrid combination of a helicopter and a fixed wing aircraft. A conventional helicopter is modified with a nose-mounted tractor propeller to provide thrust for forward flight. Wings are added to provide lift during forward flight. With the propeller providing thrust and the wings lift during forward flight, the helicopter rotor blades are unloaded during cruising flight to allow increased forward speed by avoiding limitations of conventional helicopters, including retreating rotor blade stall and maximum rotor blade tip speeds. A single powerplant drives both the main rotor and the nose-mounted propeller. The compound helicopter employs high aspect ratio wings with large flaps that may be extended to reduce vertical drag during vertical flight and hovering operations.

摘要翻译： 复合直升机是直升机和固定翼飞机的混合组合。 传统的直升机用鼻梁式拖拉机螺旋桨改装，以提供向前飞行的推力。 在向前飞行期间添加翼来提供电梯。 螺旋桨在向前飞行期间提供推力和机翼升力，直升机转子叶片在巡航飞行期间卸载，以避免传统直升机的限制，包括撤回转子叶片失速和最大转子叶片叶尖速度，从而提高向前速度。 单个动力装置驱动主转子和鼻安装的螺旋桨。 复合式直升机采用高长宽比的翼片，可以扩展大型翼片，以减少垂直飞行和悬停操作中的垂直阻力。

公开(公告)号：US5314143A

公开(公告)日：1994-05-24

申请号：US59716

申请日：1993-05-12

申请人： David Luria

发明人： David Luria

IPC分类号： B64C20060101 ,  B64D11/00 ,  B64D11/04

CPC分类号： B64D11/0007 ,  B64D11/00 ,  B64C2001/0027

摘要： An aircraft cabin construction includes a cart-storage compartment in the space between the ceiling of the passenger compartment and the upper fuselage wall for storing food-serving wheeled carts; and an elevator having a platform and a drive for lowering the carts from the cart-storage compartment to the deck of the passenger compartment, and for raising the carts from the deck to the cart-storage compartment.

摘要翻译： 飞机机舱结构包括在乘客舱的天花板和上部机身壁之间的空间中的用于储存食用轮式推车的车辆储存舱; 以及具有平台和驱动器的升降机，用于将推车从小车存放隔间降下到乘客舱的甲板上，并用于将货车从甲板升起至推车储存舱。

公开(公告)号：US5897078A

公开(公告)日：1999-04-27

申请号：US756154

申请日：1996-11-26

申请人： Robert W. Burnham ,  Michael F. Fitzpatrick ,  Dennis A. Muilenberg ,  Joseph K. Schoebelen ,  Laurence B. Trollen

发明人： Robert W. Burnham ,  Michael F. Fitzpatrick ,  Dennis A. Muilenberg ,  Joseph K. Schoebelen ,  Laurence B. Trollen

IPC分类号： B64C20060101 ,  B64C1/00 ,  B64C1/06 ,  B64C29/00

CPC分类号： B64C1/0009 ,  B64C1/061 ,  B64C29/00 ,  B64C29/0066 ,  B64C2039/105

摘要： A modular approach to the manufacture of high performance military aircraft allows different aircraft to be manufactured at affordable cost and with high part number commonality. An aircraft so constructed includes a delta wing; a forebody section, including a cockpit, which is mounted to the front of the wing; and a propulsion system support frame mounted beneath the forebody section and the underside of the wing. The propulsion system is supported within this frame. The aircraft can also include an aftbody section mounted to the aft end of the wing, which includes a 2-D variable thrust vectoring nozzle and a pair of canted vertical tails. The forebody section includes a chin inlet below the cockpit. The wing is preferably constructed using thermoplastic welding.

摘要翻译： 制造高性能军用飞机的模块化方法使不同的飞机能够以合理的成本制造，并且具有高的部件号通用性。 这样构造的飞机包括三角翼; 前身部分，包括安装在机翼前部的驾驶舱; 以及安装在机翼前部和下侧的推进系统支撑框架。 在此框架内支持推进系统。 飞机还可以包括安装在机翼的后端的船体部分，其包括2-D可变推力矢量喷嘴和一对倾斜的垂直尾部。 前身部分包括驾驶舱下方的下巴入口。 翼优选地使用热塑性焊接构造。

公开(公告)号：US5381692A

公开(公告)日：1995-01-17

申请号：US987871

申请日：1992-12-09

申请人： Christopher L. Winslow ,  John A. Roncallo ,  William C. Boyce ,  Robert T. Bonitz ,  Bruce E. Zepke ,  Michael W. Hawman

发明人： Christopher L. Winslow ,  John A. Roncallo ,  William C. Boyce ,  Robert T. Bonitz ,  Bruce E. Zepke ,  Michael W. Hawman

IPC分类号： B64C20060101 ,  F16C19/52 ,  G01M13/00 ,  G01M13/04 ,  G05G1/00 ,  G05G3/00 ,  G08B21/00

CPC分类号： G01M13/045 ,  F16C19/525 ,  F16C19/527

摘要： A bearing assembly monitoring system provides continuous, real time monitoring of the operating condition of a powertrain support bearing assembly and real time alarm signals indicative of degradation and/or impending catastrophic failure thereof. One embodiment of the monitoring system includes a vibration sensing device, first and second primary temperature sensing devices, an ambient temperature sensing device, vibration and temperature signal processing subcircuits, and an alarm subsystem. The vibration sensing device monitors complex vibration signals emanating from the bearing assembly and provides signals corresponding thereto. The vibration signal processing circuit filters such complex vibration signals to provide a predetermined bandwidth thereof that are converted to stabilized DC voltage signals which are compared to reference voltages corresponding to higher than normal and excessive vibration levels. Exceedance of such reference voltages generates a corresponding vibration alarm signal. The temperature sensing devices monitor the operating and ambient temperatures of the bearing assembly and provide signals corresponding thereto. The temperature signal processing circuit converts such temperature signals to differential temperature signals which are compared to a reference voltage corresponding to a temperature differential indicative of impending catastrophic failure. Exceedance of the reference voltage generates a temperature alarm signal. The alarm subsystem is operative in response to the vibration and/or temperature alarm signals to provide a real time early warning of degradation and/or impending catastrophic failure of the bearing assembly.

摘要翻译： 轴承组件监控系统提供对动力系支撑轴承组件的操作状态的连续实时监控以及指示其退化和/或即将发生的灾难性故障的实时报警信号。 监测系统的一个实施例包括振动感测装置，第一和第二初级温度感测装置，环境温度感测装置，振动和温度信号处理子电路以及报警子系统。 振动感测装置监测从轴承组件发出的复杂振动信号并提供与其对应的信号。 振动信号处理电路对这些复合振动信号进行滤波，以提供其转换为稳定的直流电压信号的预定带宽，与稳定的直流电压信号进行比较，该参考电压对应于高于正常和过高的振荡电平。 超过这种参考电压会产生相应的振动报警信号。 温度感测装置监测轴承组件的工作温度和环境温度，并提供对应的信号。 温度信号处理电路将这样的温度信号转换成与对应于指示即将发生的灾难性故障的温度差的参考电压进行比较的差分温度信号。 超过参考电压会产生温度报警信号。 报警子系统响应于振动和/或温度报警信号而工作，以提供轴承组件的退化和/或即将发生的灾难性故障的实时早期警告。

公开(公告)号：US4609987A

公开(公告)日：1986-09-02

申请号：US473594

申请日：1983-03-09

申请人： Leonard M. Greene

发明人： Leonard M. Greene

IPC分类号： B64C13/18 ,  B64C20060101 ,  G05D1/06 ,  G05D1/08

CPC分类号： G05D1/0661

摘要： A system which provides an increased minimum aircraft pitch attitude during take-off or go-around operations in the event that an unsafe wind shear condition is encountered. A control signal from a wind shear warning system, indicative of a dangerous wind shear condition, is fed to a switching device which controls the velocity command signal to the flight director pitch control. This switching device, in response to the wind shear signal, changes the velocity command to a lower predetermined value, such that the attitude of the aircraft is automatically increased to handle the wind shear encounter.

摘要翻译： 在遇到不安全风切变条件的情况下，在起飞或复飞操作期间提供增加的最小飞行器俯仰姿态的系统。 来自风切变警报系统的指示危险风切变条件的控制信号被馈送到控制到飞行指示器俯仰控制的速度指令信号的开关装置。 该切换装置响应于风切变信号将速度指令改变到较低的预定值，使得飞行器的姿态自动增加以处理风切变相遇。