某型教练飞机尾旋特性试飞研究

为了解决某型教练机大迎角/失速/尾旋设计定型的技术难题,依据GJB3814《军用飞机失速/过失速/尾旋试飞验证要求》,开展了尾旋试飞技术研究,提出了符合军标验证要求的尾旋特性试飞方法,包括不同进入方法、不同改出方法、最佳改出方法以及改出过程中误操纵等。通过试飞发现：该飞机对偏离是敏感的,但对尾旋等过失速模态是阻抗的;该飞机存在＂过失速旋转＂、＂落叶飘＂、＂振荡正飞陡尾旋＂以及＂倒飞尾旋＂四种典型的过失速模态;＂三中立＂法可以较迅速改出发现的四种过失速模态,与失速改出方法具有同一性且不需要过多驾驶技巧,为试飞员推荐的最佳改出动作。

Flight Test Research of a Trainer＇s Spin Characteristics

In order to solve the technical problems of a trainer＇s high angle of attack/stall/spin certification test,spin test technique is studied according to Chinese military specification GJB-3814.. stall/post-stall/spin flight test demonstration requirements for military airplanes. A test method for spin characteristics is designed to satisfy the military specification, including different entry methods, different recovery methods and recommended recovery method and misapply in spin recovery etc. After the flight test, It is found that the aircraft is sensitive to departure but impedance to post-stall mode such as spin, there are four typical post-stall modes which include post-stall gyration, like-leaf-falling mode, erect-steep-oscillatory spin and inverted spin, and three-controls-neu- tral method is the recommended recovery method, which could recover from the four post-stall modes, and do not need too much pilot＇s skills and technique because of possessing the same method to recover stall.