摘要
以某歼击机为例,按《军用飞机强度和刚度规范》要求,重点介绍了考虑飞机结构柔性和非线性气动力特性、气动载荷分布的飞行载荷计算方法和计算结果,并对柔性飞机的非线性气动力特性和气动载荷分布对飞行载荷计算状态和严重载荷设计情况选取的影响进行了对比和分析,确定了飞机严重载荷设计情况和设计载荷,从而得出一些具有实际工程参考价值的结论。分析表明,所提出的飞行载荷计算方法合理有效,计算结果合理可信。
According to the requirment of Military Aircraft Strenth and Rigidity Specification, the flight loads calculation methods and results by taking a fighter as an example have been introduced in this paper, considering aircraft construction flexibility, nonlinear aerodynamic characteristics and aerodynamic load distribution. The influence of nonlinear aerodynamic characteristics and load distribution of a flexible aircraft on the choices of flight loads calculating regimes and severe load cases has been compared and analysed, then the aircraft severe loads design cases and design loads have been decided, and some practical engineering solution have been also reached. The analysis presents that the introduced flight loads calculating method is reasonable and efficient and the result is believable.
出处
《飞行力学》
CSCD
2004年第4期85-88,共4页
Flight Dynamics
关键词
飞行载荷
载荷包线
静气动弹性
flight load
load envelope
static aeroelastics
