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

舰载飞机前起落架弹射起飞突伸试验研究

¹ School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China
² National Key Laboratory of Strength and Structural Integrity, Xi'an 710065, China
³ Key Laboratory of Aeronautical Science and Technology for Structural Impact Dynamics, China Aircraft Strength Research Institute, Xi'an 710065, China
⁴ Key Laboratory of Vibration, Impact and Noise of Aircraft in Shaanxi Province, Xi'an 710065, China
⁵ Shenyang Aircraft Design Institute, Shenyang 110035, China

Received: 27 April 2024

Abstract

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.

摘要

起落架动力学试验是研制过程中验证结构参数特性是否符合设计要求的重要手段, 且对动态过程约束条件模拟精确与否将直接影响试验结果的有效性。针对固定翼舰载飞机弹射起飞过程的特点, 提出了一种舰载飞机前起落架弹射起飞突伸试验方法, 搭建了起落架弹射突伸试验测试系统, 并分别研究了在弹射起飞突伸过程中起落架关键部位载荷、加速度及缓冲器充填压力等设计参数的变化规律, 以及不同参数变化对起落架弹射起飞突伸性能的影响。试验结果表明, 起落架牵制释放及弹射突伸过程均会使结构受到较大冲击, 牵制释放过程造成上部质量垂向过载是起落架突伸时的2倍以上, 起落架缓冲器压力改变对此过程影响不大; 弹射突伸过程中加载速率与高压气腔充气压力对整个系统突伸能量影响较大, 而缓冲器充油量、轮胎充气压力等变化对突伸能量影响较小。