Flight Control Law Clearance Using Optimal Control Theory
Flight Control Law Clearance Using Optimal Control Theory
复制标题
使用最优控制理论的飞行控制律间隙
DOI：
10.2514/1.c033517
复制
发表时间：
2016
影响因子：
2.2
通讯作者：
J. Ben
中科院分区：
文献类型：
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作者：
Avriel A. Herrmann;J. Ben
本研究探讨应用最佳控制技术的有效性，飞行控制律的间隙问题，这是一个挑战，确保安全的飞机的飞行控制系统的所有允许的输入。选择的具体准则是迎角极限超过准则，并构造了两种不同的代价函数来精确描述它。利用研究环境中的气动数据模型（Aero-Data Model in a Research Environment）来获得真实的气动力系数，建立了纵向短周期模型。证明了一般系统在状态无界时存在bang-bang最坏情况输入，在一个或多个状态有界时存在可能的bang-奇异-bang最坏情况输入。这些结果进行了验证与模拟使用通用伪谱最优控制软件。在物理领域，这些结果转化为致动器速率限制问题;因此，有限的升降舵偏转和升降舵偏转速率可能导致更极端的最坏情况下的性能。
This study explores the effectiveness of applying optimal control techniques to the flight control law clearance problem, which is the challenge of ensuring the safety of an aircraft’s flight control system for all allowable inputs. The specific criterion chosen was the angle-of-attack limit exceeding criterion, and two different cost functions were constructed that accurately describe it. Using Aero-Data Model in a Research Environment to obtain realistic aerodynamic coefficients, a longitudinal short-period model was developed. It was proven that the general system has a bang-bang worst-case input when the states are unbounded, and a possible bang-singular-bang worst-case input when one or more states are bounded. These results were validated with simulations using General Pseudospectral Optimal Control Software. In the physical domain these results translate into actuator rate limiting issues; thus, limited elevator deflection and rate of elevator deflection can lead to even more extreme worst-case per...