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. 发明申请

US20030053912A1 Shape memory alloy device and control method 有权
公开(公告)号：US20030053912A1
公开(公告)日：2003-03-20
申请号：US10217351
申请日：2002-08-10
申请人： The Boeing Company
发明人： A. Dean Jacot , Robert T. Ruggeri , Dan J. Clingman
IPC分类号： B63H003/10
CPC分类号： F03G7/065 , B64C11/44 , B64C2027/7288
摘要： A preferred rotary actuator includes an actuator assembly having a torque tube formed of a shape memory alloy (SMA), a superelastic NiTinol return spring associated with the torque tube and adapted to bias the torque tube toward an initial position, and a torque tube heating element, especially a thermoelectric device, for switching the SMA to cause rotation to an object connected to the actuator or to generate a torque upon that object. The torque tube (24) includes a proximal end (32) and a distal end (34). The return spring and torque tube are connected at their ends, with the torque tube being pretwisted while in a martensitic state relative to the spring. Activation of the heating element causes the torque tube to enter an austenitic state in which it returns to its previous untwisted configuration. Removal of heat allows the torque tube to return to a martensitic state, when the return spring retwists the torque tube. A unique locking assembly 22 is used with the preferred actuator assembly. A helicopter blade twist rotation system for a rotorcraft blade 200 having a blade root 202 and a tip 204 includes a SMA rotary actuator 18 located within the blade near the blade root, and a passive torque tube (206) located within the blade and having a proximal end connected to the rotary actuator and a distal end connected to the blade near to the blade tip.

2. 发明申请

US20040255583A1 CONTROL SYSTEM FOR A TURBO-CHARGED DIESEL AIRCRAFT ENGINE 失效
标题翻译：涡轮增压柴油机发动机的控制系统
公开(公告)号：US20040255583A1
公开(公告)日：2004-12-23
申请号：US10600450
申请日：2003-06-23
申请人： TOYOTA JIDOSHA KABUSHIKI KAISHA
发明人： Yukio Otake
IPC分类号： F02B033/44 , B63H003/10
CPC分类号： F02M59/447 , B64D31/00 , F02B37/00 , F02D1/065
摘要： In the control system for a turbo-charged diesel aircraft engine, a target value for a fuel injection amount is determined by the stroke of a throttle lever. A boost compensator determines the maximum limit for the fuel injection amount in accordance with the boost pressure of the engine in order to suppress the formation of exhaust smoke. The actual fuel injection amount is set at the target value or the maximum limit whichever is smaller. An electronic control unit (ECU) calculates an increase rate of the stroke of the throttle lever based on an output of the stroke sensor disposed near the throttle lever. The ECU determines that the current operating condition of the aircraft requires a rapid increase in the engine output power when the increase rate of the stroke is larger than a predetermined value and increases the maximum limit determined by the boost compensator.
摘要翻译：在涡轮增压柴油飞机发动机的控制系统中，燃料喷射量的目标值由节流杆的行程确定。增压补偿器根据发动机的增压压力来确定燃料喷射量的最大极限，以抑制排烟的形成。将实际燃料喷射量设定为目标值或最大极限，以较小者为准。电子控制单元（ECU）基于设置在油门杆附近的行程传感器的输出来计算节气门杆的行程的增加率。当行程的增加速度大于预定值并且增加由升压补偿器确定的最大极限值时，ECU确定飞机的当前操作状态需要发动机输出功率的快速增加。

3. 发明申请

US20040031267A1 CONTROL SYSTEM FOR A TURBO-CHARGED DIESEL AIRCRAFT ENGINE 失效
标题翻译：涡轮增压柴油机发动机的控制系统
公开(公告)号：US20040031267A1
公开(公告)日：2004-02-19
申请号：US10219494
申请日：2002-08-16
申请人： TOYOTA JIDOSHA KABUSHIKI KAISHA
发明人： Yukio Otake
IPC分类号： F02D023/00 , F04D029/26 , F04D029/18 , B64C011/30 , F01D007/00 , B63H003/10
CPC分类号： F02D1/065 , B64C11/303 , B64C11/305 , B64D27/04 , B64D31/14 , F02C9/48 , F02D23/02 , F02D31/001 , F02D41/0007 , F02D41/021 , F02D2250/38 , F05D2270/05 , Y02T10/144
摘要： In the control system for a turbo-charged diesel aircraft engine, the engine speed and the fuel injection amount are controlled by a single control lever in such a manner that the engine speed and the fuel injection amount maintain a predetermined fixed relationship in which the fuel injection amount is always smaller than a smoke limit amount. The control system further includes a boost compensator, that restricts the fuel injection amount to a value less than a boost pressure fuel limit determined by the boost pressure of the engine, and an altitude compensator that restricts the fuel injection amount to the value less than an altitude fuel limit.
摘要翻译：在用于涡轮增压柴油飞机发动机的控制系统中，发动机转速和燃料喷射量由单个控制杆控制，使得发动机转速和燃料喷射量保持预定的固定关系，其中燃料喷射量总是小于烟雾限制量。控制系统还包括升压补偿器，其将燃料喷射量限制为小于由发动机的增压压力确定的增压压力燃料极限的值;以及高度补偿器，其将燃料喷射量限制为小于高空燃油限制。

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