The invention belongs to the technical field of aircraft full-aircraft static tests, and particularly relates to an aircraft full-aircraft static test attitude sensing and adjusting method, which is characterized in that on the basis of calculating the gravity center of an inertia test load, when measuring and sensing the aircraft attitude and judging whether the aircraft attitude change exceeds a limit or not, calculating the adjusting quantity at an aircraft constraint point; the real and complete attitude of the aircraft in the test can be accurately obtained through adjustment of the actuator cylinder, the adjustment amount is obtained through calculation according to the actual measurement attitude theory, automatic closed-loop control can be achieved in the test, the aircraft attitude can be adjusted and controlled in the test in a high-precision and high-efficiency mode, the test loading precision can be improved, and accurate examination and verification of the structural strength can be achieved.
本申请属于飞机全机静力试验技术领域,具体涉及一种飞机全机静力试验姿态感知及其调节方法,设计在计算惯性试验载荷重心的基础上,测量感知飞机姿态,判断飞机姿态变化是否超过限定时,计算飞机约束点处调节量,以作动筒进行调节,可准确得到试验中飞机的真实完整姿态,调节量根据实测姿态理论计算得到,可以在试验中实现自动闭环控制,能够在试验中高精度、高效率的调节控制飞机姿态,提高试验加载精度,实现结构强度的精准考核与验证。
Attitude sensing and adjusting method for full-aircraft static test of aircraft
一种飞机全机静力试验姿态感知及其调节方法
2024-02-13
Patent
Electronic Resource
Chinese
IPC: | B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen / G01M TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES , Prüfen der statischen oder dynamischen Massenverteilung rotierender Teile von Maschinen oder Konstruktionen |
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