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Electric retracting-releasing device for pint-sized airplane undercarriage

A retractable device and technology for small aircraft, applied in the field of aircraft landing gear, can solve problems such as unsuitable weight, achieve the effects of reducing the type of power source, simplifying the structure, and reducing weight

Active Publication Date: 2009-12-09
XI'AN AIRCRAFT INTERNATIONAL
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The hydraulic system mentioned above includes not only power hydraulic components, but also corresponding hydraulic control components, hydraulic actuators and complex hydraulic pipelines. This complex and heavy mechanism is not suitable for small aircraft.

Method used

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  • Electric retracting-releasing device for pint-sized airplane undercarriage
  • Electric retracting-releasing device for pint-sized airplane undercarriage
  • Electric retracting-releasing device for pint-sized airplane undercarriage

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Embodiment Construction

[0023] The present invention will be further described below in conjunction with accompanying drawing:

[0024] The invention relates to an electromechanical integrated electric retractable device for landing gear of a small aircraft.

[0025] The circuit control part is composed of a main control module and a motor drive module. The main control module includes a single-chip microcomputer, a DC / DC module, an isolation amplifier, a debounce chip, a voltage adjustment and protection module, and a travel switch in place, such as figure 1 and figure 2 shown. The in-position travel switch is installed on the end cover of the piston barrel or on the connecting plate, such as Figure 4 shown. The motor driver module includes servo amplifier control units such as image 3 shown.

[0026] The entire main control module is concentrated on a printed circuit board with a small area, and the motor drive module is directly built into the motor. The motor drive module is the connecti...

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PUM

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Abstract

The invention discloses an electric retractable device for a landing chassis of a small plane, which consists of a circuit control part and a mechanical transmission execute part. The circuit control part mainly consists of a main controller module and an electric motor driving control module; the mechanical transmission part consists mainly of a piston cylinder, an electric motor, a speed reduction device that is connected with an output shaft of the electric motor, a linear displacement output device that is arranged in the piston cylinder and is connected with the output shaft of the speed reduction device, a linear displacement destination locking device and a piston subassembly that is connected with the linear displacement output device. The invention adopts the mechanical and electric integration, the whole device is simple, compact and reasonable in structure, reduces the varieties of the power source of the small planes and the weight of the plane; also the device can be well connected with a master control system of the plane and can be easily controlled by the program of the master control system of the plane.

Description

technical field [0001] The invention relates to an aircraft landing gear, in particular to a retractable device for a small aircraft landing gear. Background technique [0002] The traditional small aircraft landing gear retractable device is generally a hydraulic cylinder controlled by the aircraft hydraulic system, and its structure is mainly composed of piston cylinder, piston, piston rod and other components. The hydraulic retractable actuator is connected to the hydraulic system on the aircraft through the nozzle joint. When the landing gear needs to be retracted, the main control system of the aircraft sends a signal to the hydraulic control system to retract or lower the landing gear, and the aircraft hydraulic control system receives the signal. After the corresponding signal, the corresponding hydraulic control element is activated, and the hydraulic oil in the controlled hydraulic oil circuit enters the action chamber of the hydraulic cylinder, and the piston is mo...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C25/24G05B15/02G05D3/14
CPCY02T50/44Y02T50/40
Inventor 孙继勇金军邓晓山
Owner XI'AN AIRCRAFT INTERNATIONAL
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