CN-122009518-A - Aileron deflection multi-parameter interaction and calibration method and system in aircraft structural strength test

CN122009518ACN 122009518 ACN122009518 ACN 122009518ACN-122009518-A

Abstract

The invention discloses an aileron deflection multi-parameter interaction and calibration method and system in an aircraft structural strength test, and belongs to the technical field of aircraft structural strength tests. The method comprises the steps of collecting and conditioning displacement and angle signals by an aileron deflection control system, connecting the signals to a coordinated loading control system, carrying out displacement-angle calibration in the aileron deflection control system, respectively carrying out displacement calibration and angle calibration between two systems, and realizing emergency signal interaction and synchronous triggering. According to the invention, through multi-parameter interaction and two-stage calibration between systems, the acquisition errors of sensors and the acquisition deviation between systems are corrected, the high-precision data synchronization and monitoring of the aileron deflection control system and the coordinated loading control system are realized, and the safety and control precision of a structural strength test are greatly improved through the linkage of digital emergency signals.

Inventors

MAO SHUANG
LIN JIFENG
ZHANG YONGXING
LIN FENG
ZHANG WEIWEN
ZHANG YONGLI
ZHANG YUZHE

Assignees

中国飞机强度研究所

Dates

Publication Date: 20260512
Application Date: 20260128

Claims (10)

1. The multi-parameter interaction and calibration method for aileron deflection in the aircraft structural strength test is characterized by comprising the following steps: s1, an aileron deflection control system acquires displacement and angle signals and carries out signal conditioning; S2, accessing the conditioned displacement and angle signals into a coordinated loading control system; s3, performing displacement-angle calibration in the aileron deflection control system to correct the gain and zero position of the displacement sensor; s4, performing displacement calibration between the aileron deflection control system and the coordinated loading control system to correct acquisition gain and zero point of a displacement signal of the coordinated loading control system; s5, calibrating the angle between the aileron deflection control system and the coordinated loading control system to correct acquisition gain and zero point of the angle signal of the coordinated loading control system; and S6, respectively setting protection limit values of displacement and angle in the aileron deflection control system and the coordinated loading control system to realize test safety monitoring, and establishing an emergency signal interaction link between the aileron deflection control system and the coordinated loading control system so that when any system triggers emergency action, emergency response of the other system can be synchronously triggered through the link.
2. The method of claim 1, wherein in step S1, the displacement signal is collected by an LVDT displacement sensor and the angle signal is collected by an inclination sensor, and wherein the aileron deflection control system provides AC excitation for the LVDT displacement sensor and DC voltage excitation for the inclination sensor.
3. The method of claim 2, wherein the signal conditioning in step S1 comprises converting the AC signal output by the LVDT displacement sensor into a DC voltage signal and isolating the DC signal output by the tilt sensor.
4. The method according to claim 1, wherein step S2 specifically comprises the steps of accessing the conditioned direct current voltage signal into an analog input channel of the coordinated loading control system, setting theoretical gain for displacement signals for acquisition, configuring a virtual input channel for angle signals, and compiling a linear calculation formula to convert the voltage signal into an angle value.
5. The method according to claim 2, wherein the displacement-angle calibration in step S3 comprises: s31, taking the inclination angle sensor as a reference, determining the middle position of the aileron as a zero position and zeroing the inclination angle sensor; S32, deflecting the aileron, and recording the corresponding relation between the displacement value of the LVDT displacement sensor and the angle value of the inclination sensor; and S33, correcting the gain and zero position of the LVDT displacement sensor according to the recorded displacement-angle relation and against the theoretical linear relation.
6. The method according to claim 1, wherein the calibration of the displacement between the aileron deflection control system and the coordinated loading control system in step S4 comprises: S41, deflecting the aileron, and recording the displacement value of the aileron deflection control system calibrated in the step S3 and the displacement value acquired by the coordinated loading control system; S42, performing linear fitting on the two groups of displacement values, and determining gain correction rate and zero correction amount of displacement acquisition of the coordinated loading control system; S43, correcting the gain and zero point of the displacement channel in the coordinated loading control system according to the gain correction rate and the zero point correction amount.
7. The method of claim 4, wherein the angle calibration between the aileron deflection control system and the coordinated loading control system of step S5 specifically comprises: s51, deflecting the aileron to a zero position, and zeroing the inclination angle sensor in the coordination loading control system; s52, deflecting the aileron to a plurality of different non-zero angle positions, and recording angle values respectively corresponding to the aileron deflection control system and the coordinated loading control system at each position; and S53, performing linear fitting on the two groups of angle values, determining the gain correction rate and the zero correction amount for the angle acquisition of the coordinated loading control system, and correcting.
8. The method according to claim 1, wherein the emergency signal interaction in step S6 specifically includes setting upper and lower protection limits of displacement and angle in the aileron deflection control system and the coordinated loading control system respectively, triggering an emergency protection action by itself when any system detects overrun, and simultaneously, the aileron deflection control system sends an emergency instruction to the coordinated loading control system through a digital signal to trigger the coordinated loading control system to synchronize emergency.
9. An aileron deflection multi-parameter interaction and calibration system for use in an aircraft structural strength test for implementing the method of any of claims 1-8, comprising: the aileron deflection control system is configured to collect and condition displacement and angle signals and is internally provided with a displacement-angle calibration module; a coordinated loading control system configured to receive displacement and angle signals from the aileron deflection control system; the signal interaction module is connected between the aileron deflection control system and the coordinated loading control system and is used for transmitting analog quantity signals and digital quantity emergency signals; the signal interaction module comprises an analog quantity interaction channel and a digital quantity emergency channel; The analog quantity interaction channel is used for transmitting the displacement and angle direct current voltage signals conditioned by the aileron deflection control system to the coordinated loading control system; the digital emergency channel is used for transmitting an emergency trigger signal from the aileron deflection control system to the coordinated loading control system; The coordinated load control system is configured to perform displacement calibration and angle calibration with the aileron deflection control system based on displacement and angle signals received through the analog interaction channel, and is configured to perform an emergency action in linkage with the aileron deflection control system in response to an emergency trigger signal received through the digital emergency channel.
10. The system of claim 9, wherein the coordinated load control system further comprises a calibration module; the calibration module is configured to calculate and correct the gain and zero point of the self-displacement acquisition channel according to the reference displacement value acquired from the aileron deflection control system and the self-acquired displacement value when the displacement calibration is carried out; when the angle is calibrated, the gain and the zero point of the self angle calculation channel are calculated and corrected according to the reference angle value acquired from the aileron deflection control system and the self calculated angle value.

Description

Aileron deflection multi-parameter interaction and calibration method and system in aircraft structural strength test Technical Field The invention relates to the technical field of aircraft structural strength tests, in particular to an aileron deflection multi-parameter interaction and calibration method and system in an aircraft structural strength test. Background In aircraft aileron structural strength testing, it is often necessary to control aileron deflection to a target angle prior to loading the airfoil. This process involves two independent control systems, the aileron yaw control system (responsible for angular actuation) and the coordinated loading control system (responsible for load application). At present, the two systems operate independently, and lack effective data interaction capability. In order to meet the requirements of high precision and high safety of the test, the two systems can synchronously and highly accurately collect and monitor various parameters such as displacement, angle and the like, and realize linkage protection. However, because the two systems are independently collected, factors such as sensor characteristics, signal conditioning circuits, collection card precision and the like can introduce an inter-system collection error, so that the actual values of the same parameters monitored by the two systems have deviation. The light deviation affects the accuracy of test data, and the heavy deviation may cause potential safety hazard due to asynchronous protection actions. The prior art lacks a systematic method capable of effectively realizing multi-parameter high-precision synchronous acquisition, error calibration and safety linkage between two independent control systems. Disclosure of Invention The invention aims to solve the problems of asynchronous parameter acquisition, large error and incapability of linkage of safety protection caused by independent operation of an aileron deflection control system and a coordinated loading control system in the prior art, and provides an aileron deflection multi-parameter interaction and calibration method and system in an aircraft structural strength test, which can realize double-system high-precision multi-parameter interaction, systematic calibration and emergency synchronous triggering. In order to achieve the above purpose, the invention adopts the following technical scheme: In a first aspect, the invention provides an aileron deflection multi-parameter interaction and calibration method in an aircraft structural strength test, and the core concept of the method is to construct a set of two-stage calibration system covering the intra-system calibration and inter-system calibration, and realize high-precision synchronization and safety linkage of multiple parameters such as displacement, angle, emergency signals and the like through an interaction channel of mixing analog quantity and digital quantity. The specific technology comprises the following steps: s1, an aileron deflection control system acquires displacement and angle signals and carries out signal conditioning; S2, accessing the conditioned displacement and angle signals into a coordinated loading control system; s3, performing displacement-angle calibration in the aileron deflection control system to correct the gain and zero position of the displacement sensor; s4, performing displacement calibration between the aileron deflection control system and the coordinated loading control system to correct acquisition gain and zero point of a displacement signal of the coordinated loading control system; s5, calibrating the angle between the aileron deflection control system and the coordinated loading control system to correct acquisition gain and zero point of the angle signal of the coordinated loading control system; and S6, respectively setting protection limit values of displacement and angle in the aileron deflection control system and the coordinated loading control system to realize test safety monitoring, and establishing an emergency signal interaction link between the aileron deflection control system and the coordinated loading control system so that when any system triggers emergency action, emergency response of the other system can be synchronously triggered through the link. Further, in step S1, the displacement signal is collected by an LVDT displacement sensor, the angle signal is collected by an inclination sensor, and the aileron deflection control system provides alternating current excitation for the LVDT displacement sensor and direct current voltage excitation for the inclination sensor. Further, the signal conditioning in the step S1 comprises the steps of converting an alternating current signal output by the LVDT displacement sensor into a direct current voltage signal and isolating and outputting the direct current signal output by the inclination sensor. Further, the step S2 specifically comprises the steps of accessing the conditioned