Assessment of aircraft flight controllers using nonlinear robustness analysis techniques
Assessment of aircraft flight controllers using nonlinear robustness analysis techniques
复制标题
使用非线性鲁棒性分析技术评估飞机飞行控制器
DOI：
10.1007/978-3-642-22627-4_19
复制
发表时间：
2012
影响因子：
3
通讯作者：
A. Packard
中科院分区：
文献类型：
--
作者：
P. Seiler;G. Balas;A. Packard
目前验证飞行控制律的实践依赖于应用线性分析工具来评估许多配平条件下的闭环系统稳定性和性能特性。非线性模拟被用来在线性分析中提供进一步的置信度，也用来揭示线性分析没有揭示的动态特性，例如极限环。本章回顾了可应用于由多项式动态方程描述的系统的非线性分析技术。所提出的方法是使用多项式模型来逼近飞机的动力学。然后，可以使用平方和优化技术来解决非线性分析。通过对F/A-18飞机和NASA通用运输模型飞机的非线性分析，验证了这些方法的适用性。这些非线性分析技术可以填补线性分析和非线性仿真之间的空白，从而为飞行控制律的性能提供额外的置信度。
The current practice to validate flight control laws relies on applying linear analysis tools to assess the closed loop stability and performance characteristics about many trim conditions. Nonlinear simulations are used to provide further confidence in the linear analyses and also to uncover dynamic characteristics, e.g. limit cycles, which are not revealed by the linear analysis. This chapter reviews nonlinear analysis techniques which can be applied to systems described by polynomial dynamic equations. The proposed approach is to approximate the aircraft dynamics using polynomial models. Nonlinear analyses can then be solved using sum-of-squares optimization techniques. The applicability of these methods is demonstrated with nonlinear analyses of an F/A-18 aircraft and NASA’s Generic Transport Model aircraft. These nonlinear analysis techniques can fill the gap between linear analysis and nonlinear simulations and hence used to provide additional confidence in the flight control law performance.