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Actuating cylinder for telex shield with redundancy structure and implementation method of redundancy

An actuator and redundancy technology, applied in the chassis and other directions, can solve the problem that the structure design of the actuator of the telex shield is rarely involved, and achieves the possibility of reducing the possibility of high-level hazard, weight reduction, and overall structure. simple effect

Active Publication Date: 2016-05-25
南京唯宇智能装备有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At present, most domestic aircraft fender actuating cylinders use hydraulic actuating cylinders, and there is little involvement in the design of the redundant structure of the fender fender actuating cylinder

Method used

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  • Actuating cylinder for telex shield with redundancy structure and implementation method of redundancy

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Embodiment Construction

[0013] The present invention will be described in further detail below in conjunction with the accompanying drawings.

[0014] A fly-by-wire shield actuator with a redundant structure, based on a motor-driven shield actuator, one end of the shield actuator is connected to the aircraft body, the other end is connected to the shield through a connector 13, and the left end of the motor 3 is connected to the Reducer 2, the right end is connected to brake 4, reducer 2 is connected to clutch 6 through synchronous belt 1, clutch 6 is connected to screw transmission mechanism, and screw transmission mechanism drives connector 13; The leading screw nut 7 on the bar 10, the leading screw nut 7 overcoat push rod 8, and the end of the push rod 8 is screwed with the connector 13.

[0015] The clutch 6 has a fixed mechanical interface. The fixed mechanical interface has a hole at the joint between the clutch 6 and the lead screw 10. The lead screw 10 is connected with the clutch 6. The fix...

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Abstract

A fly-by-wire shield actuator with a redundant structure, based on the motor-driven shield actuator, one end of the shield actuator is connected to the aircraft body, and the other end is connected to the shield through a connector. It is characterized in that: the motor The left end is connected to the reducer, and the right end is connected to the brake. The reducer is connected to the clutch through the synchronous belt, the clutch is connected to the screw transmission mechanism, and the screw transmission mechanism drives the connector; the screw transmission mechanism includes a lead screw and a lead screw nut set on the lead screw , the lead screw nut is covered with a push rod, and the end of the push rod is screwed with the connector. When the motor breaks down, the clutch is released, the screw transmission mechanism is separated from the motor drive, and the screw can rotate freely. With the help of the lowering force of the aircraft prop, the actuator of the telex shield is pulled out to realize the emergency lowering of the shield.

Description

technical field [0001] The invention relates to the technical field of double redundancy, in particular to a redundancy structure and a redundancy realization method of an electric transmission guard plate actuator. Background technique [0002] In order to meet the requirements of the new generation of all-electric aircraft, a series of measures have been taken in China to realize the all-electric retraction of the landing gear. Existing fender actuating cylinders use hydraulic pressure as a power source. This hydraulic actuating cylinder has low efficiency and heavy weight, which is not conducive to further improvement of aircraft performance. Using the fly-by-wire shield as the actuator can avoid the above-mentioned unfavorable factors, thereby improving the performance of the aircraft. [0003] The function of the actuator of the fly-by-wire shield is that when the plane is about to land, the actuator of the fly-by-wire shield stretches out to open the shield of the lan...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C25/24
Inventor 田威宿馨文张霖李羊
Owner 南京唯宇智能装备有限公司
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