基于爬升减速机动的大迎角偏离敏感性试飞技术  

A Flight Test Method for Departure Sensitivity at High Angle of Attack Based on Decelerated Climbing Maneuver

作　　者：方自力[1] 何太 李吉宽 樊力[1] FANG Zili;HE Tai;LI Jikuan;FAN Li(Chinese Flight Test Establishment,Xi’an 710089,China;Airforce Test Pilot School,Xi’an 710089,China)

机构地区：[1]中国飞行试验研究院,西安710089 [2]空军试飞员学校,西安710089

出　　处：《空军工程大学学报》2023年第1期76-81,共6页Journal of Air Force Engineering University

摘　　要：为防止飞机意外进入大迎角失速尾旋状态,现代电传飞机通常采用左边界保护控制策略。但在使用中,仍然难以避免由于飞行速度超出左边界后“掉入”大迎角状态的现象。为全面评估飞机的左边界飞行安全,必须通过试飞验证飞机大迎角偏离敏感性。采用传统的平飞失速和收敛转弯等试飞方法,难以解决飞机超出左边界后“掉入”大迎角状态后的偏离敏感性评估问题。针对某型飞机迎角限制和抗尾旋控制律的特点,提出了基于爬升减速机动的大迎角偏离敏感性评估方法,采用飞行仿真技术开发了大迎角偏离敏感性试飞动作,建立了在迎角限制和抗尾旋控制律的综合作用下飞机大迎角偏离敏感性和尾旋阻抗程度的评估程序,并且在某型飞机上进行了应用和验证,全面评估了某型飞机的大迎角偏离敏感性和尾旋阻抗程度,为该型机的左边界飞行安全提供了有效的支持。In order to prevent an aircraft from falling accidentally into stall/spin status in the process of flying at a high angle of attack,the modern fly-by-wire combat aircraft in the flight control system is usually is adopted by left boundary protection module.However,such a phenomenon is difficult to stop during use.To insure flight safety,the departure sensitivity in flying at a high angle of attack needs to be evaluated by flight testing.Traditional level-flight speed and convergent-turn methods are unable to fully evaluate the aircraft departure sensitivity.According to the demonstration requirement of aircraft high angle of attack departure sensitivity and spin resistance,an evaluation method based on deceleration climbing maneuver is proposed.A set of flight test maneuvers are developed by flight simulation.Moreover,the flight test procedure is built to evaluate high angle of attack departure sensitivity and spin resistance of modern aircraft with angle of attack limit and anti-spin control law.The method and procedure are validated on a certain type of aircraft.The result show that the method and procedure could satisfy the aircraft with the demonstration requirement.

关 键 词：迎角限制 抗尾旋 爬升减速机动 偏离敏感性 

分 类 号：V217.32[航空宇航科学与技术—航空宇航推进理论与工程]