【作者】 程才凤；

【导师】 刘昶；

【作者基本信息】 南京航空航天大学 ， 流体力学， 2003， 硕士

【摘要】 本文介绍了军用标准MIL-STD-1797A提供的评估短周期俯仰响应特性的6种不同判据，依据这六种判据利用等效系统方法对某型飞机纵向短周期运动的飞行品质进行计算和分析，结果表明这6种判据既有着许多共同之处，也有许多不一致的特点。运用序列二次规划方法计算出满足Neal—Smith准则条件的驾驶员模型参数，然后将ω_sdT_θ2,S_sd,τ_θ准则映射到Neal-Smith准则，确定它们的一致区域和矛盾区域，对参数影响进行分析，评估其变化趋势，为新机设计、实验和试飞过程中更好地选择合适的飞行品质参数提供参考。最后介绍了战斗机中等幅度滚转姿态快速性的定义，应用欧拉法对19种飞机构形的滚转快速性进行了仿真计算，并且与地面模拟战斗机滚转攻击机动实验相比较，结果表明滚转姿态快速性与滚转模态时间常数、滚转操纵效能、副翼操纵速率和控制系统增益等密切相关，飞行品质标准MIL-STD-1797没有完全涵盖中等幅度滚转姿态变化的要求。更多还原

【Abstract】 This paper introduced six different methods which are given by MIL-STD-1797 offers for evaluating short-term pitch response. According to these methods, Flying qualities for aircraft short-term response are calculated and analyzed by equivalent system. The results indicate that there are both regions of agreement and regions of conflict in these methods. Sequential Quadratic Programming is used to solve the pilot modelin the Neal-Smith criterion. And then, the criteria of ωspTθ2,ζsp,τθ aremapped to Neal-Smith criteria for short-term pitch to determine regions of agreement and regions of conflict. In order to provide better selections for the parameters of flying qualities on the design of a new aircraft, an experiment and a test- fly, the effects and the varying trends of the parameters are analyzed and evaluated. Finally, Based on the definition of moderate amplitude roll attitude quickness criteria for fighter aircraft, The roll attitude quickness is calculated by Euler method for 19 types aircraft configurations in the paper. The results of the simulation calculation are compared with the pilots simulation experiment on aggressive maneuvering in roll, The conclusions are obtained that roll attitude quickness is closely related to the flying qualities, such as the roll-mode constant, the roll control sensitivity, aileron control effectiveness and control system augment etc. Requirements for moderate amplitude maneuvering roll attitude changes are not completely involved in MIL-STD-1797A.更多还原