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Electric and gas heterogeneous redundant unmanned aerial vehicle undercarriage folding and unfolding actuator cylinder and working method

A landing gear and unmanned aerial vehicle technology, applied in the field of aircraft landing gear, can solve problems such as redundancy, and achieve the effect of improving reliability

Pending Publication Date: 2021-11-19
XIAN MICROELECTRONICS TECH INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to overcome the shortcomings of the above-mentioned prior art that both the hydraulic and electric retractable cylinders of the UAV landing gear have certain limitations, and provide a kind of electrical and pneumatic heterogeneous redundant UAV landing gear retractable Actuator

Method used

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  • Electric and gas heterogeneous redundant unmanned aerial vehicle undercarriage folding and unfolding actuator cylinder and working method
  • Electric and gas heterogeneous redundant unmanned aerial vehicle undercarriage folding and unfolding actuator cylinder and working method

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0034] An electrical and pneumatic heterogeneous redundant unmanned aerial vehicle landing gear retractable actuator, such as figure 2 As shown, including electric unit and pneumatic unit;

[0035] The electric unit comprises a chassis 15, in which a controller 8, a motor 9, an air motor 10 and a transmission assembly are installed, and a first electrical connector 1, a push rod 7 and a position switch 14 are also installed on the chassis 15, and the controller 8 and The motor 9 is electrically connected, and the push rod 7 is connected with the landing gear of the external drone;

[0036] The pneumatic unit includes a gas cylinder 4, a solenoid valve 5, a constant pressure valve 6 and a second electrical connector 2. The second electrical connector 2 is installed on one side of the gas cylinder 4. The constant pressure valve 6 and the air motor 10 pass through a gas hose 3, the solenoid valve 5 is electrically connected to the second electrical connector 2;

[0037] The fi...

Embodiment 2

[0039] Except for the following content, all the other content is the same as embodiment 1.

[0040] The pneumatic unit also includes a constant pressure valve 6, which is installed at one end of the solenoid valve 5;

[0041] The air inlet of the air motor 10 is opened on the side of the first electrical connector 1 , and the air inlet of the air motor 10 is connected to the air outlet of the constant pressure valve 6 through the gas hose 3 .

Embodiment 3

[0043] Except for the following content, all the other content is the same as embodiment 1.

[0044] The transmission assembly includes a gear 11, a worm gear 12 and a ball screw pair 13; the output end of the gear 11 is connected with the worm gear 12, the other end of the worm gear 12 is connected with the ball screw pair 13, and the other end of the ball screw pair 13 is connected with the pusher The rod 7 is connected; the input end of the gear 11 is connected with the motor 9 and the air motor 10 respectively. In-place switch 14 is provided with four, and the two ends of push rod 7 start and end travel respectively are installed 2. MC nylon buffer rings are respectively placed at both ends of the push rod 14 . The motor 9 is a brushless DC motor.

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Abstract

The invention discloses an electric and gas heterogeneous redundant unmanned aerial vehicle undercarriage folding and unfolding actuator cylinder and a working method, belongs to the technical field of aircraft undercarriages. The actuator cylinder takes an electric unit as a main working channel and a pneumatic unit as an emergency auxiliary channel. Under the normal working condition, a controller controls a motor to rotate after receiving an instruction, the motor drives a push rod to move in the direction required by the instruction through a transmission assembly so as to drive an undercarriage to move till the undercarriage reaches the target position, the motor is controlled to stop rotating, and the undercarriage is locked in place. When the electric unit breaks down, a flying pipe computer starts an emergency discharge source, an electromagnetic valve opens a gas cylinder to output high-pressure gas, a pneumatic motor starts to work, a pneumatic motor drives the push rod to move through the transmission assembly, and then the undercarriage is driven to move. According to the device, when the electric unit breaks down, the pneumatic unit drives the undercarriage to move, and the problems that a hydraulic actuator cylinder is large in size, low in efficiency and poor in maintainability, and an electric actuator cylinder is low in reliability are effectively solved.

Description

technical field [0001] The invention belongs to the technical field of aircraft landing gear, and relates to a retractable actuator and a working method for an electric and pneumatic heterogeneous redundant unmanned aerial vehicle landing gear. Background technique [0002] The landing gear retractable actuator is an important part of the landing gear of the UAV, and its working reliability directly affects the safe takeoff, taxiing, landing and flight performance of the UAV. [0003] Most of the existing UAV landing gear adopts a single hydraulic or electric power source for retracting and retracting, and a hydraulic or electric cylinder as the main actuator for retracting and retracting systems. Although the hydraulic retractable system is mature in technology, its components are of high quality, high energy consumption, low efficiency, complicated pipelines, and long maintenance time. Compared with the hydraulic retractable system, the electric retractable system has the...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C25/22B64C25/24
CPCB64C25/22B64C25/24
Inventor 赵亚妮李桐窦森
Owner XIAN MICROELECTRONICS TECH INST
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