摘要
纵向力矩特性的优劣影响失速攻角及最大升力系数的使用,对飞机的安全性及经济性起着重要作用。国内外飞机设计规范及适航条例对飞机的操稳及失速特性作了明确的规定和要求。从CCAR-25运输类飞机适航条例对失速特性要求的角度出发,研究民机的纵向力矩特性,并从理论上推导俯仰力矩允许的上仰幅度公式,从风洞试验数据分析俯仰力矩上仰的原因。结论表明为满足适航要求的减速率及杆力为正,俯仰力矩可以允许一定量值的上仰,但幅度不可过大;平尾当地动压的减小使得其对俯仰力矩贡献减小;平尾对纵向力矩贡献的减小是俯仰力矩上仰的主要因素。
The quality of civil aircraft pitching moment characteristics affects the stall angle and the maximum coefficient of lift. It plays an important role in aircraft＇ s safety and economy performance. Aircraft maneuverability/ stability and stall characteristics are strictly required by design specifications and airworthiness standards home and abroad. This paper gave a theoretical deduction of the allowable ＂pitch up＂ magnitude and analyzed the cause of ＂ pitch up＂ by wind tunnel data. The results show that to meet the airworthiness requirements of deceleration rate and positive stick force, ＂pitch up＂ is allowed but the magnitude is restricted. The decrease of local dynamic pressure of horizontal tail makes the pitching moment contribution decrease. The decrease of pitching moment contribution of horizontal tail is the primary cause to ＂pitch up＇.
出处
《民用飞机设计与研究》
2015年第4期13-15,72,共4页
Civil Aircraft Design & Research
关键词
上仰
失速特性
操纵性
俯仰力矩
pitch up
stall characteristics
maneuverability
pitching moment
