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公开(公告)号：US20090218440A1
公开(公告)日：2009-09-03
申请号：US12393157
申请日：2009-02-26
CPC分类号： B64C25/405 , B64C25/50 , Y02T50/823
摘要： The invention relates to a powered wheel system for an aircraft, comprising at least one undercarriage with several rotatably held wheels, with the powered wheel system comprising two or more motors of which in each case at least one motor is coupled to at least one of the wheels, and comprising at least one control device that is coupled to the motors. A control device is equipped to control operation of the motors independently of each other as far as their respective rotary speeds and direction of rotation are concerned, so that the system is able, among other things, to effect taxiing; by means of rotary speed differentials on different motors to be able to steer the aircraft; prior to landing to bring the wheel circumference speeds to landing speed; and to boost the undercarriage brakes of the aircraft. Furthermore, by means of an improvement of the system according to the invention, the rotary speeds of the wheels may be determined with precision. The invention furthermore relates to a method for driving wheels of an aircraft.
摘要翻译： 本发明涉及一种用于飞行器的动力轮系统，其包括至少一个具有多个可旋转地保持的轮的底盘系统，该动力轮系统包括两个或更多个马达，在每个情况下，至少一个马达与至少一个马达 车轮，并且包括耦合到电动机的至少一个控制装置。 控制装置被配置为只要其各自的旋转速度和旋转方向彼此独立地控制电动机的操作，使得该系统能够实现滑行; 通过不同电机上的转速差能够引导飞机; 在着陆前将车轮的圆周速度提升到着陆速度; 并加强飞机的起落架刹车。 此外，通过根据本发明的系统的改进，可以精确地确定车轮的转速。 本发明还涉及一种用于驱动飞行器的轮子的方法。
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公开(公告)号：US08517303B2
公开(公告)日：2013-08-27
申请号：US12393157
申请日：2009-02-26
IPC分类号： B64C25/50
CPC分类号： B64C25/405 , B64C25/50 , Y02T50/823
摘要： The invention relates to a powered wheel system for an aircraft, comprising at least one undercarriage with several rotatably held wheels, with the powered wheel system comprising two or more motors of which in each case at least one motor is coupled to at least one of the wheels, and comprising at least one control device that is coupled to the motors. A control device is equipped to control operation of the motors independently of each other as far as their respective rotary speeds and direction of rotation are concerned, so that the system is able, among other things, to effect taxiing; by means of rotary speed differentials on different motors to be able to steer the aircraft; prior to landing to bring the wheel circumference speeds to landing speed; and to boost the undercarriage brakes of the aircraft. Furthermore, by means of an improvement of the system according to the invention, the rotary speeds of the wheels may be determined with precision. The invention furthermore relates to a method for driving wheels of an aircraft.
摘要翻译： 本发明涉及一种用于飞行器的动力轮系统，其包括至少一个具有多个可旋转地保持的轮的底盘系统，该动力轮系统包括两个或更多个马达，在每个情况下，至少一个马达与至少一个马达 车轮，并且包括耦合到电动机的至少一个控制装置。 控制装置被配置为只要其各自的旋转速度和旋转方向彼此独立地控制电动机的操作，使得该系统能够实现滑行; 通过不同电机上的转速差能够引导飞机; 在着陆前将车轮的圆周速度提升到着陆速度; 并加强飞机的起落架刹车。 此外，通过根据本发明的系统的改进，可以精确地确定车轮的转速。 本发明还涉及一种用于驱动飞行器的轮子的方法。
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公开(公告)号：US20120055183A1
公开(公告)日：2012-03-08
申请号：US13258841
申请日：2010-04-19
CPC分类号： B60H3/024 , B64D13/08 , B64D2013/0662 , B64D2041/005 , Y02T50/56 , Y02T90/36
摘要： A system for cooling a space in a vehicle comprises a sorption wheel, at least one heat exchanger, at least a first humidifier unit and at least one fuel cell, wherein the sorption wheel is adapted for drying ambient air and for conveying dried process air to the downstream heat exchanger and the heat exchanger is adapted for cooling process air, with the heat exchanger being connected to the first humidifier unit for humidifying cooled process air, and wherein the fuel cell is connected to the sorption wheel and adapted for making available fuel cell exhaust air for regenerating the sorption wheel and water to be introduced into the first humidifier unit. Since the utilization of fuel cells is increasingly considered in modern vehicles and, in particular, commercial aircraft, the system according to the invention makes it possible to realize a symbiotic relationship between already installed fuel cells and cooling systems in vehicles, in which the further use of the waste products heat and humidity leads to fuel savings. In addition, an evaporative cooling method is presented, in which a fuel cell serves for supplying heat and water.
摘要翻译： 用于冷却车辆空间的系统包括吸附轮，至少一个热交换器，至少第一加湿器单元和至少一个燃料电池，其中所述吸附轮适于干燥环境空气并将干燥的工艺空气输送到 下游热交换器和热交换器适于冷却过程空气，其中热交换器连接到第一加湿器单元以加湿冷却的处理空气，并且其中燃料电池连接到吸附轮并适于制造可用的燃料电池 用于再生吸附轮的废气和要引入第一加湿器单元的水。 由于在现代车辆，特别是商用飞机中越来越多地考虑使用燃料电池，所以根据本发明的系统使得可以实现已经安装的燃料电池和车辆中的冷却系统之间的共生关系，其中进一步使用 的废物产生的热量和湿度导致节省燃料。 此外，提出了一种蒸发冷却方法，其中燃料电池用于供应热量和水。
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4.发明授权
公开(公告)号：US4765568A
公开(公告)日：1988-08-23
申请号：US94831
申请日：1987-09-09
申请人： Udo Carl , Homayoun Dilmaghani
发明人： Udo Carl , Homayoun Dilmaghani
CPC分类号： G05D1/0077 , B64C13/42 , B64C13/503 , Y02T50/44
摘要： A fly-by-wire control system for the elevator assemblies of an aircraft isquipped with a mechanical auxiliary control (8) and with a synchronizing coupling (10). The electrical control links connecting the controlling computers to the elevator drives are each equipped with an override mechanism (4,2). A mechanical cable link (9) of the auxiliary mechanical control (8) connects a pilot operated mechanical control member such as a pitch control wheel having a detent to the respective override mechanism. This combination makes sure that the pilot initiated control signals have performance priority over any other signals at all times. The synchronizing coupling (10) is arranged between the mechanical control links leading to the respective elevator flap drives to assure a symmetric flap deflection on both sides at high speed flight under failure conditions. Centering springs (12) assure a centered position of the flap if the respective flap side signal transmission linkage (4.4) is affected by a mechanical failure (rupture) at low speed.
摘要翻译： 用于飞行器的电梯组件的线控控制系统配备有机械辅助控制（8）和同步联轴器（10）。 将控制计算机连接到电梯驱动器的电气控制链路各配备有超控机构（4,2）。 辅助机械控制器（8）的机械电缆连杆（9）将诸如具有制动器的俯仰控制轮的先导操作的机械控制构件连接到相应的超越机构。 这种组合确保导频发起的控制信号始终具有优于任何其他信号的性能优先级。 同步联轴器（10）设置在通向相应电梯折翼驱动器的机械控制连杆之间，以确保在故障条件下高速飞行时两侧的对称翼片偏转。 如果相应的挡板侧信号传动联动装置（4.4）受到低速机械故障（破裂）的影响，定心弹簧（12）可确保挡板的中心位置。
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公开(公告)号：US4437631A
公开(公告)日：1984-03-20
申请号：US141008
申请日：1980-04-17
CPC分类号： B64C9/24
摘要： A leading edge slat of an aircraft wing is connected to the ends of two rods each of them being linked to a crank arm which, in turn, is swung over a particular angular range by means of a planetary gear being driven by a common shaft. Arcuate guide rails on the slat run in rolls which are journalled on the wing case.
摘要翻译： 飞机机翼的前缘板条连接到两个杆的端部，每个杆的端部连接到曲柄臂，曲柄臂通过由公共轴驱动的行星齿轮在特定的角度范围内摆动。 板条上的弧形导轨在卷轴上运行，这些导轨位于翼壳上。
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