CN-121990175-A - Nose landing gear performance test system

CN121990175ACN 121990175 ACN121990175 ACN 121990175ACN-121990175-A

Abstract

The invention discloses a performance test system of a nose landing gear, which relates to the field of aircraft test and comprises an upper computer, a lower computer PLC and a hydraulic control module, wherein the upper computer is used for sending a retraction speed curve and an angle displacement value to the lower computer PLC, the hydraulic control module comprises an oil source module, an angle displacement sensor and a proportional reversing valve, the angle displacement sensor is used for acquiring rotation angles of a turning actuator cylinder and a retraction actuator cylinder, determining the variation of flow of the corresponding actuator cylinder according to the rotation angles, converting the variation into the angle displacement value, the lower computer PLC is used for converting the retraction speed curve and the angle displacement value into angle control signals and adjusting the angle control signals according to the angle displacement value of the angle displacement sensor, and the proportional reversing valve is used for adjusting the proportional angles when the angle control signals are received so as to control the flow of the retraction actuator cylinder, the left turning actuator cylinder and the right turning actuator cylinder and perform retraction action, left turning action or right turning action under different speeds of the nose landing gear.

Inventors

BIAN JUANGE
LI ZHE
ZHAO GANG
ZHAO MENGWEN

Assignees

西安航空职业技术学院

Dates

Publication Date: 20260508
Application Date: 20260205

Claims (6)

1. The nose landing gear performance test system is characterized by comprising an upper computer, a lower computer PLC and a hydraulic control module; The upper computer is used for sending a preset winding and unwinding speed curve and an angle displacement value to the lower computer PLC; The hydraulic control module comprises an oil source module, an angular displacement sensor and a proportional reversing valve, wherein the angular displacement sensor is respectively and electrically connected with the turning actuator cylinder and the retractable actuator cylinder and is used for acquiring the rotation angles of the turning actuator cylinder and the retractable actuator cylinder in real time, and determining the corresponding variable quantity of the flow of the turning actuator cylinder and the retractable actuator cylinder according to the rotation angles and converting the variable quantity of the flow into an angular displacement value; the lower computer PLC is used for converting a preset winding and unwinding speed curve and an angle displacement value into an angle control signal and adjusting the angle control signal in real time according to the angle displacement value of the angle displacement sensor; The proportional reversing valve is connected with the oil source module, the turning actuator cylinder and the retraction actuator cylinder respectively in a pipeline connection mode, and is used for performing proportional angle adjustment when receiving an angle control signal from the lower computer PLC so as to control and adjust the flow of the retraction actuator cylinder, the left turning actuator cylinder and the right turning actuator cylinder of the front landing gear, so that retraction movement, left turning movement or right turning movement of the front landing gear at different speeds can be performed.
2. The nose landing gear performance test system of claim 1, further comprising a monitoring module electrically connected to the upper computer, comprising a test control module, a communication module, and a status monitoring module; the test control module comprises a data acquisition module and an output control module, and is used for acquiring instructions of the upper computer and determining state information of each channel; the communication module is used for uploading the test data acquired by the data acquisition module to the upper computer; The state monitoring module is used for analyzing the instruction from the upper computer, comparing the acquired test data with the preset out-of-tolerance parameter, and stopping the test when the test data exceeds the preset out-of-tolerance parameter.
3. The nose landing gear performance test system according to claim 1, wherein the hydraulic control module further comprises a proportional overflow valve, the proportional overflow valve is connected with the oil source module, the turning actuator cylinder and the retraction actuator cylinder respectively through a pipeline connection mode, and the proportional reversing valve is used for adjusting the opening degree when receiving a pressure control signal from the lower computer PLC so as to control and adjust the pressures of the retraction actuator cylinder, the left turning actuator cylinder and the right turning actuator cylinder of the nose landing gear, so as to perform retraction movement, left turning movement or right turning movement of the nose landing gear under different loads.
4. The nose landing gear performance test system of claim 1, wherein the hydraulic control module is designed with an integrated valve block, and the operation mode of the hydraulic control module comprises a manual mode and an automatic mode, wherein the manual mode is operated by a physical button, the automatic mode is controlled by an upper computer, and the upper computer is a touch screen.
5. The nose landing gear performance test system of claim 1, wherein the hydraulic control module is equipped with a high pressure supplemental pump and a hand pump for tightness testing and emergency operation.
6. The nose landing gear performance test system of claim 1, further comprising a frame module for positioning the nose landing gear by employing digital mass transfer and laser testing techniques to mount the nose landing gear on the test stand.

Description

Nose landing gear performance test system Technical Field The invention relates to the technical field of aircraft testing, in particular to a nose landing gear performance testing system. Background Aircraft nose landing gear is one of the important components of an aircraft, whose performance directly affects the safety and reliability of take-off, landing and taxiing. In actual operation, the nose landing gear needs to deal with changeable and extreme working conditions, such as the movement of an actuator cylinder under different speed (such as low-speed sliding and high-speed turning) conditions, so as to test the key performances of turning, retraction and the like of the nose landing gear under different working conditions, and the traditional test equipment is difficult to fully simulate the complex working conditions, so that the test result has deviation from the actual use condition, and the performance of the nose landing gear cannot be accurately evaluated. Disclosure of Invention The invention provides a nose landing gear performance test system, which is used for solving the problems in the prior art, namely how to improve the performance simulation accuracy of an aircraft nose landing gear in the prior art; The upper computer is used for sending a preset winding and unwinding speed curve and an angle displacement value to the lower computer PLC; The hydraulic control module comprises an oil source module, an angular displacement sensor and a proportional reversing valve, wherein the angular displacement sensor is respectively and electrically connected with the turning actuator cylinder and the retractable actuator cylinder and is used for acquiring the rotation angles of the turning actuator cylinder and the retractable actuator cylinder in real time, and determining the corresponding variable quantity of the flow of the turning actuator cylinder and the retractable actuator cylinder according to the rotation angles and converting the variable quantity of the flow into an angular displacement value; the lower computer PLC is used for converting a preset winding and unwinding speed curve and an angle displacement value into an angle control signal and adjusting the angle control signal in real time according to the angle displacement value of the angle displacement sensor; The proportional reversing valve is connected with the oil source module, the turning actuator cylinder and the retraction actuator cylinder respectively in a pipeline connection mode, and is used for performing proportional angle adjustment when receiving an angle control signal from the lower computer PLC so as to control and adjust the flow of the retraction actuator cylinder, the left turning actuator cylinder and the right turning actuator cylinder of the front landing gear, so that retraction movement, left turning movement or right turning movement of the front landing gear at different speeds can be performed. The system also comprises a monitoring module, wherein the monitoring module is electrically connected with the upper computer and comprises a test control module, a communication module and a state monitoring module; the test control module comprises a data acquisition module and an output control module, and is used for acquiring instructions of the upper computer and determining state information of each channel; the communication module is used for uploading the test data acquired by the data acquisition module to the upper computer; The state monitoring module is used for analyzing the instruction from the upper computer, comparing the acquired test data with the preset out-of-tolerance parameter, and stopping the test when the test data exceeds the preset out-of-tolerance parameter. Optionally, the hydraulic control module further comprises a proportional overflow valve, the proportional overflow valve is connected with the oil source module, the turning actuator cylinder and the retraction actuator cylinder respectively in a pipeline connection mode, and the proportional reversing valve is used for adjusting the opening degree when receiving a pressure control signal from the lower computer PLC so as to control and adjust the pressures of the retraction actuator cylinder, the left turning actuator cylinder and the right turning actuator cylinder of the nose landing gear, so that retraction and retraction actions, left turning actions or right turning actions of the nose landing gear under different loads can be performed. Optionally, the hydraulic control module adopts an integrated valve block design, the operation mode of the hydraulic control module comprises a manual mode and an automatic mode, the manual mode is operated through a physical button, the automatic mode is controlled through an upper computer, and the upper computer is a touch screen. Optionally, the hydraulic control module is provided with a high-pressure oil supplementing pump and a hand pump for tightness test and emergency operat