【作者】 张鑫；

【导师】 李玉龙；

【作者基本信息】 西北工业大学 ， 固体力学， 2007， 硕士

【摘要】 CTOL舰载机最显著的特点是弹射起飞和拦阻着舰，这也是其出事率高的原因。CTOL舰载机拦阻着舰时对舰载机产生很大的冲击载荷，影响飞行员和舰载机的安全。舰载机着舰挂索后的受力状态是飞机最复杂的受力状态，此时的数学模型是飞机最复杂的数学模型。准确而完整的数学建模是进行舰载机拦阻动力学分析的基础。在已知起落架参数的前提下，准确求解能减少为获得起落架载荷及能量吸收能力所需的地面测试，而且，能外推测试困难或飞行试验才能得到的设计条件。通过仿真计算，达到优化设计和缩短试验时间的目的。 为了探讨CTOL舰载机拦阻着舰过程动力学分析这一具有实用意义的问题，本文建立了舰载机拦阻着舰数学模型。在整个着舰过程中分了两个阶段：①舰载机与拦阻索啮合后没触舰飞行阶段；②触舰后的滑跑过程。该模型分为舰载机数学模型和甲板拦阻系统数学模型两个相互独立的部分，二者通过舰载机上安装的拦阻钩与跑道拦阻索的啮合点的运动联系起来。本文考虑了飞机拦阻着舰非对称飞行时飞机的动态响应，建立了六自由度运动方程。建立了比较完整的舰载机拦阻着舰数学模型，对舰载机及甲板拦阻系统数学模型较为详细。采用SIMULINK作为仿真工具，可以摆脱复杂的程序设计工作，使人们集中了更多的精力放在数学模型的建立及优化上。 本文以MK7-3拦阻系统为例，以MIL—STD—2066的试验曲线为基础，由文献中提供的经验公式及数据与图表，对原来空缺的飞机啮合时的情况做了计算，给出了载荷—行程曲线。并通过仿真计算与MIL—STD—2066中曲线及数据对比，对模型进行了仿真校验。根据对比，本文的数值仿真情况接近于MK7-3的实测情况。通过本文的仿真计算，得出决定拦阻机拦阻钩载荷的是飞机重量、啮合速度及拦阻系统本身的能量的吸收能力。在拦阻机确定时，飞机重量与啮合速度较小时，会出现前峰值；当重量与啮合速度较大时出现后峰值情况。飞行甲板宽度的增加会使拦阻钩载荷峰值发生时间延后。偏心时拦阻钩载荷峰值稍微降低，但是变化不大。飞机所偏方向的拦阻带最大拉力比对中的拦阻带拉力大，而飞机所背离方向的拦阻带最大拉力比对中时的拦阻带拉力小。更多还原

【Abstract】 The noticeable characteristic of the conventional take-off and landing of carrier aircrafts is catapult-assisted take-off and arrested deck-landing, which is the main reason of most carrier aircrafts’ accidents. When a CTOL carrier aircraft is arrested deck-landing, the serious dynamic impact loadings on the aircraft, which affect the pilots and aircrafts’ safety, will occur. After carrier aircraft contacts the cable ,the loading state of it will be the most complex. And at this time, the mathematical model of carrier aircraft is the most complex too. Precise and perfect mathematical model is the base to analyse the dynamic response of carrier aircraft arrested deck-landing. Exact analysis and solution can reduce the times of ground tests which the landing gears that some parameters are known need to know load on it and ability to absorb energy. Furthermore it can extrapolate the testing conditions as design conditions, which are difficult and satisfied through dangerous flying tests. Simulation is to optimize design and reduce the testing time.To study the significative problem dynamic response of carrier aircraft arrested deck-landing, this thesis builds its mathematical model. The whole arrested deck-landing process separates into two phases. The first is carrier aircraft that engaging the cable, but it dosen’t contact the deck. And the second is movement that it contacts the deck. This model divedes into two independent parts which are carrier aircraft and deck arresting gear system mathematical model. The two parts are connected by the point of the arresting hook of carrier aircraft that engages arresting cable. This thesis builds the six freedom motion equation considering dynamic response of aircraft arrested deck-landing flying unsymmetrically. Mathematical model of carrier aircraft arrested deck-landing is more perfectly, and mathematical model of carrier aircraft and deck arresting gear system are more detailed. Simulink is taken as a simulation tool ,which frees people from the boring programming work and lets people put more effort on the work to build mathematical model and optimize it.This thesis take the MK7-3 arresting gear system as example. According to testing curves of military standard 2066 which supplies some experiential formulas and data, calculations are did to those doesn’t exist in it and get curves of load versus stroke. Simulation values are compared with the data and curves of military standard 2066 and mathematical model is validated. The simulations values are close to the tests values of MK7-3 via comparison. The results of simulation更多还原