采用差尾控制策略的某型机横滚操纵性  

Roll Control Performance of a Type of Fighter using Differentially-controllable Horizontal Tail Control Strategy

作　　者：王子健[1] 陈勇[2] 徐彦军 

机构地区：[1]海军航空工程学院青岛分院,山东青岛266041 [2]海军装备部飞机办,北京100083 [3]海军航空兵学院教研部,辽宁葫芦岛125001

出　　处：《航空计算技术》2012年第5期84-86,共3页Aeronautical Computing Technique

摘　　要：某型战机所采用的气动布局使得其横侧安定性较大,与同代其他现役飞机相比横滚操纵性能较差,飞行员在做横滚机动动作时飞机掉高度现象明显。分析了其在低速和高速飞行时横滚机动性能差的原因,研究了增加差动平尾控制提高横滚操纵性的问题。建立了采用差动平尾后飞机稳定横滚的数学模型,并通过定量分析计算说明了增加差动平尾控制,可以使该型战机的横滚机动性能提高近30%,而不会削弱其安定性。Because of its special aerodynamic configuration,without use of differentially-controllable horizontal tail,the fighter has more roll stability than other type′s similar aircraft.So,phenomenon of losing altitude is very obvious when the aircraft is rolling.The reason why this type of fighter has poor roll maneuverability at low or high speed is analyzed detailly in this paper,and the feasibility to improve the roll control performance by using differentially-controllable horizontal tail is studied.In this paper a stable roll mathematics model using differential elevator is built,and results show that by using differential elevator control strategy,it′s roll maneuverability can be improved by 30 percent,while maintaining the original stability.

关 键 词：横滚 操纵性 安定性 差动平尾 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]