摘要
飞机的姿态参数是研究飞机飞行状态的重要依据,在特技飞行试验中尤为重要。目前飞行试验中飞机姿态参数的测量是由全姿态组合陀螺仪完成的。在大迎角、失速、尾旋等特技飞行试验中,机载陀螺仪输出的姿态参数经数据采集系统处理后与飞机真实飞行状态之间存在误差。通过研究飞机的飞行状态与姿态参数输出特点,分析了姿态参数测量误差存在的原因,利用换向器技术改变输出多值性的问题,并在特技飞行试验中对改进的方法进行了多次验证,以期对今后大迎角、失速、尾旋等高风险、高难度特技飞行试飞中姿态参数的测量起到借鉴与指导的作用,为保证新机试飞任务顺利完成、保障飞行员生命安全提供有效的参考依据。
Attitude parameters are important among the aircraft flight parameters, especially in the aerobatic test. Current flight test aircraft attitude parameters are measured by the combination of the whole attitude gyro. In the high angle of attack, stall, spin and other special flight tests, airborne attitude gyro output parameters processed by the data acquisition system differ with the true aircraft flight conditions. By analyzing the output characteristics of the aircraft＇s flight status and attitude parameters, errors in the attitude parameters of measurement and the output ambiguity, this paper proposes the stunt flying test methods for improving multisecond validation, and through the analysis of the measured curves, has verified the correctness of improved methods. They may be used for future tests for large angle of attack, stall, spin high-risk, difficult aerobatic flight parameters.
出处
《科技导报》
CAS
CSCD
北大核心
2009年第18期86-89,共4页
Science & Technology Review
关键词
特技飞行
姿态参数
测量
多值性
aerobatics
profile parameters
measurement
ambiguity
