大众科技
大衆科技
대음과기
DAZHONG KEJI
2013年
11期
87-90
,共4页
非定常气动力%尾旋%仿真%六自由度方程
非定常氣動力%尾鏇%倣真%六自由度方程
비정상기동력%미선%방진%륙자유도방정
Spin%unsteady aerodynamic model%simulation%six-degree-freedom nonlinear equations
通过改造非定常气动力的数学模型，对经典六自由度方程进行改进，提出一种新颖的全量气动力六自由度方程，计算飞机飞行轨迹。以某型飞机大攻角大振幅动态风洞试验结果为样本数据建立数学模型，进行尾旋仿真计算，分析飞机尾旋各阶段的非定常气动力特性。
通過改造非定常氣動力的數學模型，對經典六自由度方程進行改進，提齣一種新穎的全量氣動力六自由度方程，計算飛機飛行軌跡。以某型飛機大攻角大振幅動態風洞試驗結果為樣本數據建立數學模型，進行尾鏇倣真計算，分析飛機尾鏇各階段的非定常氣動力特性。
통과개조비정상기동력적수학모형，대경전륙자유도방정진행개진，제출일충신영적전량기동력륙자유도방정，계산비궤비행궤적。이모형비궤대공각대진폭동태풍동시험결과위양본수거건립수학모형，진행미선방진계산，분석비궤미선각계단적비정상기동력특성。
By transforming the unsteady aerodynamic model to improve the classic six-degree-freedom nonlinear equations, a novel equation with total aerodynamic forces is proposed to calculate the flight path of the aircraft. A mathematical model is built to simulate the spin motion of aircraft, by using the wind tunnel test of the large amplitude motion as the sample data. The simulation illustrates the characteristics of unsteady aerodynamic in each stage of spin.
