飞机起飞着陆性能仿真与分析  

Simulation and Analysis for Airplanes' Performance of Takeoff and Landing

作　　者：林可心[1] 岑国平[1] 李乐[2] 刘钢[3] 

机构地区：[1]空军工程大学航空航天工程学院 [2]空军第一空防工程处 [3]94543部队

出　　处：《空军工程大学学报（自然科学版）》2012年第4期21-25,共5页Journal of Air Force Engineering University(Natural Science Edition)

摘　　要：为真实反映飞机起飞着陆的滑跑过程,记录了某型飞机的速度、加速度传感器现场数据,建立了飞机起飞着陆滑跑过程的微分方程并进行了解算;基于飞机滑跑过程的微分方程采用Simulink对飞机起降性能进行建模和仿真,记录数据、理论结果和仿真结果三者对比验证了所建立的仿真模型是有效的。基于该模型对该飞机滑跑过程进行仿真分析,结果表明起飞和不放阻力伞着陆过程可近似为匀加速直线运动过程,放阻力伞着陆过程则比较复杂。最后,研究3个主要参数对滑跑距离的影响,结果表明滑跑距离与机场海拔和风速呈近似线性关系,与迎角呈非线性关系且在迎角为8°时存在极小值点。For analyzing the takeoff and landing process of airplane accurately and finding the basis of the runway length design, the differential equations for takeoff and landing running process are established and resolved. The running performance model is built by Simulink program based on the differential equations. The Simulation model is validated to be effective by the contrast in speed and acceleration data, the theoretic results and the simulation results. The running process of the airplane is analyzed by using the model ; the results show that the takeoff process and landing process without drogue parachute could be approximately considered as a uniformly accelerated rectilin- ear motion, the landing process with drogue parachute is relatively complicated. Finally, the affections of three main factors are studied and the results show that the relationships between running length and airfield altitude or wind speed are approximately linear, the relationship between running length and attack angle is nonlinear and the minimum point of running length appears at the attack angle of 8°. The analysis of airplane running state can be taken as basis for runway length and taxiway high speed exit position design.

关 键 词：飞机起降性能 微分方程 匀加速直线运动 

分 类 号：V212.13[航空宇航科学与技术—航空宇航推进理论与工程]