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基于牛顿迭代法的直升机配平算法简单、高效,但配平结果依赖于初始值。为减小对初始值的依赖,基于直升机飞行动力学模型,通过构造优化目标函数,将全机配平问题转化为优化问题,并针对非线性方程组全局最优解不唯一,将GA算法计算的配平较优解作为LM算法的初值,并构建解空间约束条件,提出一种基于GA/LM混合的优化配平算法。通过计算UH-60A直升机平飞状态和协调转弯状态的配平解,并与单一优化算法和飞行测试数据比较,验证了优化配平算法的准确性和高效性。计算结果表明,基于GA/LM混合的优化配平算法不仅继承了GA算法良好的全局收敛性,也继承了LM算法高效的局部寻优特点,是一种高效、全局最优的直升机配平算法。
The helicopter trim algorithm based on the Newton iteration method is simple and efficient, but the result of the trim depends on the initial value. In order to reduce the dependence on the initial value, based on the helicopter flight dynamics model, an optimization objective function is constructed, which transforms the full-machine trim problem into an optimization problem. For the non-linear system, the global optimal solution is not unique. The GA- Balancing the optimal solution as the initial value of the LM algorithm and constructing the constraints of the solution space, an optimization algorithm based on GA / LM hybrid is proposed. The accuracy and efficiency of the optimized trim algorithm are verified by comparing with the single optimization algorithm and the flight test data by calculating the balance solution of the flat flying state and the coordinated turning state of the UH-60A helicopter. The results show that the GA / LM hybrid algorithm not only inherits the good global convergence of GA algorithm but also inherits the efficient local optimization of LM algorithm. It is an efficient and globally optimal helicopter trim algorithm.