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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。
In order to solve the technical problem of a high-angle-of-attack / stall / tail rotation design and fixing of a trainer aircraft, a tail rotor test flight technology research was conducted according to GJB3814 “Verification of Stall / Stall / Tail Rotation Test of Military Aircraft” Validation of the tail spin test methods, including different access methods, different methods to change, the best way to change out and misremeal the process of change. Through the flight test, it was found that the aircraft is sensitive to the deviation, but it is impenetrable to the overrun modes such as the tail rotation. The aircraft has “swerving past stalling speed”, “ Spin ”and“ inverted spin ”four typical stall mode;“ three neutral ”method can be more quickly re-found the four stall mode found stalling with stalling method has the same identity And do not need too much driving skills for test pilots recommended the best move out.