摘要
舵面偏转除了能够提供保证飞机稳定飞行的配平力矩,还将改变飞机的升阻比,从而影响其续航性能。在基于飞机质点假设的传统航迹优化方法的基础上,研究了飞机的升阻特性对其续航性能的影响:在上升段、巡航段及下降段前期增大升阻比,在下降段后期减小升阻比,有利于提高飞机的续航性能;提出了基于舵面配平的续航飞行航迹优化方法,以获得更接近于发挥飞机实际潜力的最优航迹与最大航程。对于多操纵面布局飞机,通过该方法能够确定其最优舵面组合配平规律。算例飞机的优化结果表明:相比单一舵面配平,最优舵面组合配平能够使算例飞机的总航程最大提高7.5%。
Besides providing balancing moment for stable flight,control surface deflection will change the lift-drag ratio of the airplane,which affects the endurance performance of the airplane. Based on the traditional flight trajectory optimization which assumes that the airplane is a particle,the effects of lift-drag characteristic on aircraft endurance performance are analyzed. Increasing lift-drag ratio at climb segment,cruise segment and earlier descent segment,and decreasing lift-drag ratio at later descent segment will improve the endurance performance of the airplane. In order to obtain the optimum flight trajectory and range closer to the actual potential of airplane,a trajectory optimization method of aircraft endurance flight based upon control surface trimming is proposed. Through this method,the optimum combined trimming mode of control surfaces can be obtained for multi-control surface airplane. The optimization result of a type of aircraft indicates that,compared to single trimming modes of control surface,the optimum combined trimming mode increases the total range by 7. 5% at most for the example airplane.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
2016年第1期79-86,共8页
Journal of Beijing University of Aeronautics and Astronautics
关键词
航迹优化
续航性能
升阻比
舵面配平
总能量原理
trajectory optimization
endurance performance
lift-drag ratio
control surface trimming
total energy theory
