摘要
飞行配平对飞行控制策略和算法起到至关重要的作用。传统对称完好飞机的飞行配平方法是纵侧向单独进行,分别利用各自的舵偏和推力进行迭代计算。当飞机由于机翼不对称损伤而发生纵横向运动强耦合时,不能保证配平的准确性和收敛性。针对单侧机翼不对称损伤飞机配平问题,首先置零运动方程加速度量得到配平方程,可从数学上提出了解决上述特殊构型飞机飞行配平的多维牛顿迭代方法,并从全局收敛性严格证明和实际情况中给出保证算法收敛的迭代初值选取方法。仿真结果表明,改进飞行配平方法能够有效地给出合适的迭代初值点,并便捷地计算出机翼不对称损伤飞机纵侧向运动强耦合下的全状态配平点集,具有较好的工程应用前景。
Flight trim plays a crucial role in flight control strategies and algorithms. The traditional flight trim of symmetric undamaged aircraft is that the longitudinal trim and lateral trim proceed iteratively utilizing decoupled con- trol surfaces and thrusts separately. It does not guarantee the accuracy and convergence of trim when the longitudinal and lateral motion modes are coupled strongly due to asymmetric damage. This paper aims at the flight trim problem of one side wing damaged asymmetric aircraft. Trim equations are obtained through making acceleration states be zeros in motion equations. Then multidimensional Newton iterative method is proposed to solve trim problem of this particular aircraft configuration. The method of choosing initial point for ensuring convergence is given by combining the global convergence＇ s proof and the actual situation. Simulation results show that this method can give appropriate initial points and calculate the all - state flight trim point set of wing-damaged asymmetric aircraft effectively and conveniently with better prospect of engineering application.
出处
《计算机仿真》
CSCD
北大核心
2014年第9期92-97,共6页
Computer Simulation
基金
国家自然基金(61201320)
总装预研项目(513250202)
关键词
飞行配平
单侧机翼不对称损伤
多维牛顿迭代
全局收敛性
Flight trim
One side wing damaged asymmetric
Multidimensional Newton iteration
Global convergence
