Design of aircraft flight loaded safety monitoring system based on the strain approach

Flight loads during aircraft flight testing determine flight safety. However, in actual flight testing, load flight tests are often arranged in the middle to late stages of the test. The load data is not obtained for some risky subjects or test points close to the boundary in the early stage. It is difficult to immediately detect load over-limit problems or flight anomalies that occur during the flight, but the specific position can only be found after processing the data after the flight. In previous flights, the structural safety monitoring measured the strain strength at the relatively weak parts of the design. This approach can only see the local strength and lacks the monitoring and collection of the overall load. This paper proposes a civil aircraft flight load monitoring system based on the strain method to monitor the loads of the main wing surface and main control surface of the test aircraft. Compared with the certification load flight test, it reduces part of the workload, can initially obtain the overall flight load of the aircraft, carry out load safety monitoring in the flight of early risk subjects, realize the structural safety monitoring of flight loads, and play a role in early exploration and guidance for the civil aircraft certification load flight test.