专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US4679485A Ballistic tolerant dual load path ballscrew and ballscrew actuator 失效
标题翻译：防弹双负载路径滚珠丝杠和滚珠丝杠执行器
公开(公告)号：US4679485A
公开(公告)日：1987-07-14
申请号：US686983
申请日：1984-12-27
申请人： Jeffrey D. Nelson , John F. Scanlon
发明人： Jeffrey D. Nelson , John F. Scanlon
IPC分类号： B64C13/42 , F16H25/22 , F41H5/04 , F16H1/18
CPC分类号： F16H25/2204 , B64C13/42 , F16H25/205 , F41H5/0485 , F16H2025/249 , Y10T74/186 , Y10T74/18672 , Y10T74/19702
摘要： Ballscrew actuators are well known for use as a primary flight control actuator for operating a flight control surface. The operation of the ballscrew actuator is critical to the success of an aircraft mission; however, when the actuator is subject to ballistic fire a projectile hit which is not totally destructive can still render the actuator inoperable. Increasing the potential for operability of the ballscrew actuator after a projectile hit which is not totally destructive will increase the number of successful returns from aircraft missions.The ballistic tolerant dual load path ballscrew actuator has a selectively driven ballnut and a ballscrew drivingly connected to the ballnut. The ballscrew has an outer tubular member with an external helical ball groove providing a primary load path. An inner tubular member fits closely within and is fixed to the outer tubular member to provide a secondary load path upon cracking of the outer tubular member by a projectile passing through the outer tubular member. The inner tubular member is formed of ballistic tolerant composite material to maintain its structural integrity when contacted by a projectile which has passed through and caused cracking of the outer tubular member.
摘要翻译：滚珠丝杠执行器是众所周知的，用作操作飞行控制表面的主要飞行控制执行器。滚珠丝杠执行器的运行对于飞机任务的成功至关重要; 然而，当执行器受到弹道导弹击球时，不完全破坏性的射弹撞击仍然会使致动器无法操作。在不完全破坏性的弹丸撞击之后，增加滚珠丝杠执行器的可操作性的潜力将增加飞机任务的成功返回次数。防弹双重负载路径滚珠丝杠致动器具有选择性地驱动的滚珠丝杠和与滚珠丝杠驱动连接的滚珠丝杠。滚珠丝杠具有外管状构件，其具有提供主负载路径的外螺旋球槽。内部管状构件紧密地配合并固定到外部管状构件，以通过穿过外部管状构件的射弹破裂外部管状构件而提供次级负载路径。内部管状构件由防弹复合材料形成，以在与穿过外部管状构件的突出物接触时保持其结构完整性。

2. 发明授权

US4715262A Ballistic tolerant dual load path ballscrew and ballscrew actuator 失效
标题翻译：防弹双负载路径滚珠丝杠和滚珠丝杠执行器
公开(公告)号：US4715262A
公开(公告)日：1987-12-29
申请号：US805627
申请日：1985-12-06
申请人： Jeffrey D. Nelson , John F. Scanlon
发明人： Jeffrey D. Nelson , John F. Scanlon
IPC分类号： B64C13/42 , F16H25/22 , F41H5/04 , F41H5/00 , F16H1/20 , B64D7/00
CPC分类号： F16H25/205 , B64C13/42 , F16H25/2204 , F41H5/0485 , F16H2025/249 , Y10S428/911 , Y10T74/19781
摘要： Ballscrew actuators are well known for use as a primary flight control actuator for operating a flight control surface. The operation of the ballscrew actuator is critical to the success of an aircraft mission; however, when the actuator is subject to ballistic fire, a projectile hit which is not totally destructive can still render the actuator inoperable. Increasing the potential for operability of the ballscrew actuator after a projectile hit which is not totally destructive will increase the number of successful returns from aircraft missions.The ballistic tolerant dual load path ballscrew actuator has a selectively-driven ballnut and a ballscrew drivingly connected to the ballnut. The ballscrew has an outer tubular member with an external helical ball groove providing a primary load path. An inner tubular member fits closely within and is fixed to the outer tubular member to provide a secondary load path upon cracking of the outer tubular member by a projectile passing through the outer tubular member. The inner tubular member is formed of ballistic tolerant composite material to maintain its structural integrity when contacted by a projectile which has passed through and cause cracking of the outer tubular member. In one embodiment, the inner tubular member has an outer energy absorbing layer of a ceramic material. In another embodiment, the inner tubular member is preloaded in tension to prevent propagation of a circumferential crack in the outer tubular member and is constructed of wound fibers providing ballistic tolerance and strength in torsion and tension.
摘要翻译：滚珠丝杠执行器是众所周知的，用作操作飞行控制表面的主要飞行控制执行器。滚珠丝杠执行器的运行对于飞机任务的成功至关重要; 然而，当执行器受到弹道防火时，不完全破坏性的弹丸撞击仍然会使致动器无法操作。在不完全破坏性的弹丸撞击之后，增加滚珠丝杠执行器的可操作性的潜力将增加飞机任务的成功返回次数。防弹双重负载路径滚珠丝杠致动器具有选择性驱动的滚珠丝杠和滚珠丝杠驱动地连接到滚珠轴承。滚珠丝杠具有外管状构件，其具有提供主负载路径的外螺旋球槽。内部管状构件紧密地配合并固定到外部管状构件，以通过穿过外部管状构件的射弹破裂外部管状构件而提供次级负载路径。内部管状构件由防弹复合材料形成，以在与穿过外部管状构件的射弹接触时保持其结构完整性。在一个实施例中，内部管状构件具有陶瓷材料的外部能量吸收层。在另一个实施例中，内部管状构件被预加载在张力中以防止外部管状构件中周向裂纹的传播，并且由缠绕的纤维构成，其提供弹性公差和扭转和张力的强度。

3. 发明申请

US20100264724A1 Integrated power until as energy storage device for electrical power system 有权
标题翻译：集成电力直到作为电力系统的储能装置
公开(公告)号：US20100264724A1
公开(公告)日：2010-10-21
申请号：US12386202
申请日：2009-04-15
申请人： Jeffrey D. Nelson , Hayden M. Reeve
发明人： Jeffrey D. Nelson , Hayden M. Reeve
IPC分类号： H02J1/16 , B60L1/00
CPC分类号： H02J15/00 , F02N11/04 , Y10T307/522
摘要： A power unit connected to a power distribution bus operates in one of several modes to either store excess electrical energy from the power distribution or supply electrical energy to the power distribution bus to account for a detected demand/need. The power unit includes turbomachinery having components connected via a shaft, a generator connected to convert rotational energy associated with the turbomachinery to electrical energy for distribution on the bus, and a motor connected to convert electrical energy distributed by the bus to motive energy used to accelerate the turbomachinery components. A power controller monitors the voltage on the distribution bus. In response to excess voltage on the distribution bus, the power controller connects the motor to the bus to cause the excess electrical energy to be converted to motive energy that is used to accelerate the turbomachinery. In response to a voltage shortage on the distribution bus, the power controller connects the generator to the bus to convert rotational energy stored by the turbomachinery to electrical energy that is supplied to the bus.
摘要翻译：连接到配电总线的电力单元以多种模式之一运行，以便从配电中存储多余的电能或者将电能供应到配电总线以考虑检测到的需求/需求。动力单元包括具有通过轴连接的部件的涡轮机械，连接成将与涡轮机械相关联的旋转能量转换为电能以在总线上分配的发电机的发电机，以及连接以将总线分配的电能转换成用于加速的动能的电动机涡轮机组件。电源控制器监视分配总线上的电压。响应于分配总线上的过电压，功率控制器将电动机连接到总线，以使过多的电能转换成用于加速涡轮机械的动力。为了响应分配总线上的电压不足，功率控制器将发电机连接到总线，以将由涡轮机械存储的旋转能量转换成供给总线的电能。

4. 发明授权

US08395274B2 Integrated power unit as energy storage device for electrical power system 有权
标题翻译：集成动力装置作为电力系统的储能装置
公开(公告)号：US08395274B2
公开(公告)日：2013-03-12
申请号：US12386202
申请日：2009-04-15
申请人： Jeffrey D. Nelson , Hayden M. Reeve
发明人： Jeffrey D. Nelson , Hayden M. Reeve
IPC分类号： F01D15/10
CPC分类号： H02J15/00 , F02N11/04 , Y10T307/522
摘要： A power unit connected to a power distribution bus operates in one of several modes to either store excess electrical energy from the power distribution or supply electrical energy to the power distribution bus to account for a detected demand/need. The power unit includes turbomachinery having components connected via a shaft, a generator connected to convert rotational energy associated with the turbomachinery to electrical energy for distribution on the bus, and a motor connected to convert electrical energy distributed by the bus to motive energy used to accelerate the turbomachinery components. A power controller monitors the voltage on the distribution bus. In response to excess voltage on the distribution bus, the power controller connects the motor to the bus to cause the excess electrical energy to be converted to motive energy that is used to accelerate the turbomachinery. In response to a voltage shortage on the distribution bus, the power controller connects the generator to the bus to convert rotational energy stored by the turbomachinery to electrical energy that is supplied to the bus.
摘要翻译：连接到配电总线的电力单元以多种模式之一运行，以便从配电中存储多余的电能或者将电能供应到配电总线以考虑检测到的需求/需求。动力单元包括具有通过轴连接的部件的涡轮机械，连接成将与涡轮机械相关联的旋转能量转换为电能以在总线上分配的发电机的发电机，以及连接以将总线分配的电能转换成用于加速的动能的电动机涡轮机组件。电源控制器监视分配总线上的电压。响应于分配总线上的过电压，功率控制器将电动机连接到总线，以使过多的电能转换成用于加速涡轮机械的动力。为了响应分配总线上的电压不足，功率控制器将发电机连接到总线，以将由涡轮机械存储的旋转能量转换成供给总线的电能。

5. 发明授权

US5899411A Aircraft electrical system providing emergency power and electric starting of propulsion engines 失效
标题翻译：飞机电气系统提供应急电力和电动起动的推进发动机
公开(公告)号：US5899411A
公开(公告)日：1999-05-04
申请号：US589235
申请日：1996-01-22
申请人： Thomas S. Latos , Jeffrey D. Nelson , Gary E. Dickes
发明人： Thomas S. Latos , Jeffrey D. Nelson , Gary E. Dickes
IPC分类号： B64D33/00 , H02J7/14
CPC分类号： B64D33/00 , H02J7/1415 , H02J7/1423 , F05B2220/50
摘要： An aircraft is provided that includes one or more engines, an air-driven generator, and a start-circuit for operably connecting an electrical output of the air driven generator for starting one or more of the engines while the aircraft is in flight. Various embodiments also provide apparatus for cross-ship electric starting of multiple engines while the aircraft is in flight or on the ground using: an electrical output of a generator attached to another engine; on-board batteries; an on board auxiliary power unit; or power received from a ground source. A single start-converter is utilized to supply power to AC starter-motors for electric starting of the aircraft's engines. In some embodiments, the engine is soft-started with the air driven generator, by controlling blade pitch in an air driven turbine driving the air driven generator, without the use of the start converter.
摘要翻译：提供了一种飞机，其包括一个或多个发动机，空气驱动发电机和起动电路，用于在飞行器飞行中可操作地连接用于起动一个或多个发动机的空气驱动发电机的电输出。各种实施例还提供了用于在飞行器处于飞行中或在地面上的多个发动机的交叉电启动的装置，其中：发电机的电输出连接到另一发动机; 车载电池; 船上辅助动力装置; 或从地源接收的功率。使用单个启动转换器为AC起动器电机供电，用于飞机发动机的电动启动。在一些实施例中，通过在不使用起动转换器的情况下控制驱动气动发电机的空气驱动涡轮机中的叶片间距，发动机与空气驱动发电机软启动。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式