摘要
介绍了飞机做非常规机动—直接升力控制的方法，讨论了直接升力控制与飞机常规控制的兼容性，以及直接升为操纵控制策略。给出了某鸭式布局飞机直接升力控制律动态解耦过程。六自由度仿真计算结果表明：前向控制形式成功地避免了直接升力控制与常规控制增稳系统之间的干扰，实现了兼容；通过直接升力的开闭环控制以实现静态解耦和动态修正，满足了飞机的机动要求．
This paper detailedly introduces an aircraft active lift control method,and discusses the tactics of active lift control and its compatibility with conventional control. The procedure to determine dynamical decoupling of active lift control law is alsogiven for an aircraft with canards configuration. On this basis, we carry out the sixdegrees of freedom simulation calculation. The results of calculation show that forwardcontrol froms avoid successfully the interruption between active lift control and conventional control augmented system and relizes compatibility, and through the use of open-close loop control the active lift control realizes the static decoupling and dynamic correction in order to satisfy aircraft maneuverability requirements.
出处
《飞行力学》
CSCD
北大核心
1996年第2期48-53,共6页
Flight Dynamics
