Experimental study on catapult take-off and sudden extension of carrier-based aircraft's nose landing gear

The landing gear dynamics test is an important means to verify whether the structural parameter characteristics meet the design requirements in the research and development process, and the simulation accuracy of the dynamic process constraint conditions will have a great impact on the test results. Based on the characteristics of the catapult take-off process of the fixed-wing carrier-based aircraft, a catapult take-off sudden extension test method for the carrier-based aircraft's front landing gear is proposed, and a landing gear catapult extension test system is built. The variation laws of design parameters such as the load, acceleration, and buffer filling pressure of the key parts of the landing gear in the catapult take-off sudden extension process is studied, as well as the impact of different parameter changes on the performance of the landing gear catapult take-off sudden extension. The test results show that both the release of the landing gear restraint and the catapult extension process will cause greater impact on the structure. The vertical overload of the upper mass caused by the release of the restraint is more than twice that of the landing gear extension, and the change of the landing gear buffer pressure has slight influence on this process. In the catapult extension process, the loading method and the inflation pressure of the high-pressure cavity determine the extension energy of the entire system, while the oil filling volume of the buffer and the tire inflation pressure have little effect on the extension energy.