Attitude control method in full-machine static test

Abstract

The invention provides an attitude control method in full-machine static test. The attitude control method in the full-machine static test comprises the following steps of: steps 1, constraining a testing machine; step 2, calculating the heading of the main landing gear of the aircraft and the adjustment amount of the lateral position control actuator; step 3, measuring the actual rigid body deformation of the testing machine in a pre-test; step 4, linearly interpolating the adjustment amount of the main landing gear heading position control actuator and the adjustment amount of the lateral position control actuator to obtain each level adjustment amount and carry out the pre-test; step 5, correcting the parameters of the position control actuator, and inputting the corrected parameters into the control system of the position control actuator, wherein the position control actuator actively adjusts the attitude of the aircraft in real time through preset parameters in the test. According to the attitude control method in the full-machine static test, the attitude of the aircraft can be actively controlled, the test risk can be reduced, the technical level of the test can be improved, the attitude control of the large aircraft heading, lateral direction, and yaw can be conveniently realized, and the attitude control method has strong practicability.

Description

technical field [0001] The application belongs to the technical field of aircraft static test of the whole aircraft, in particular to an attitude control method in the static test of the whole aircraft. Background technique [0002] At present, in the static test of the whole machine, the support method of the testing machine generally adopts six degrees of freedom statically determinate support constraints, and the supporting parts choose the non-assessment parts with higher stiffness on the testing machine. According to the above-mentioned support design principles, the main support method during the static test of the whole machine is the statically determinate support of the landing gear, that is, the vertical displacement is constrained by the front landing gear, and the vertical displacement and yaw displacement are constrained by the left and right main landing gears. The drop frame constrains lateral displacement. Load sensors are installed on each support and restr...

AI Technical Summary

Problems solved by technology

At this time, in the static test of the whole aircraft, the large deformation of the landing gear due to the large flexibility of the aircraft wing will cause the attitude of the aircraft body to change easily, which will cause a slight change in the loading position of the test loading point and reduce the test loading accuracy.

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