基于参数化降阶模型和前视突风探测信息的飞机载荷减缓控制

Gust Load alleviation(GLA) deals with decreasing the overloads due to the gust by using the active control technology, by which, the decreased increment bending moment and the structural fatigue will be expected. GLA is a key technology in the development of a large aircraft in our country. This project takes the large transport aircraft as the object of the research, and focuses on the new GLA control based on the reduced-order model of the unsteady aerodynamic forces and the information from the measurement of the forward-looking gust. The contents are as follows. First, the reduced-order modeling methods of the feedback-like unsteady aerodynamics are studied based on the system theory and the characteristic structure of the fluids; Next, we will study the accurate computation method based on the two-way coupling of the gust and the lifting surface, and the reduced-order modeling method for the gust aerodynamic forces. Third, we will study the parameterized aeroservoelastic (ASE) modeling method based on interpolation of the equations in the state space. Fourth, the model prediction control (MPC) for GLA will be studied by considering the control surface deflection and deflection rate limits, and information of the gust provided by the on board Light Detection and Ranging (LIDAR) sensor. Finally, we will study the robust MPC for GLA by considering the uncertainties in the measurement of the gust velocity and the time delay in the control input. The aim of this project is to present a systemic solution on the modeling, analysis and synthesize problem of the GLA control system based on prior gust information, and provide the important theory and key technique bases for our country in the development of the large transport aircraft.

突风载荷减缓（GLA）研究如何利用主动控制技术减小突风引起的过载，达到减轻翼根增量弯矩和结构疲劳的目的，是我国大飞机研制中亟待解决的关键技术。本项目以大型运输类飞机为研究对象，研究基于高保真非定常气动力的降阶模型和前视突风探测信息的GLA控制新方法。内容包括：基于系统辨识和流场特征结构的反馈型非定常气动力降阶建模方法；突风与升力面双向耦合的突风气动力精确计算及降阶建模方法；基于状态空间模型插值的参数化气动伺服弹性模型的建立方法；基于机载激光雷达（LIDAR）探测的飞机前方突风场信息，同时考虑控制面偏转角度和角速度约束条件，研究GLA的模型预测控制（MPC）方法；考虑LIDAR测量突风速度和控制输入时间滞后的不确定性，研究GLA的鲁棒模型预测控制（RMPC）方法。本项目旨在解决基于先知突风信息的飞机GLA控制系统建模、分析与综合问题，为我国大型运输类飞机研制提供重要理论基础和关键技术储备。

本项目旨在根据飞机安装的机载激光雷达测量的飞机前方突风信息，建立大型运输类飞机气动弹性系统突风载荷减缓控制的新方法。在此基础上，发展了非定常气动力降阶建模方法和参变气动弹性系统建模方法，为我国大型运输类飞机飞控系统设计提供关键技术储备。. 突风载荷减缓控制系统设计需要非定常空气动力学模型。工程简化的偶极子网格法非定常空气动力模型适用的马赫数范围有限，对复杂构型精度有限。因此需要发展适用于复杂构型的和全马赫数范围内都适用的低维非定常空气动力模型。本项目提出了若干非定常气动力的降阶建模方法。本项目提出的降阶建模策略从建模方法上分为两大类：一类是基于系统辨识的降阶建模方法；另一类是基于本征正交分解的降阶建模方法；本项目提出的降阶建模策略从参数个数来说分为两类：一类是适用于一个飞行状态的非定常气动力降阶建模方法；另一类是适用于多个飞行状态的非定常气动力参数化降阶建模方法。. 飞机气动弹性系统本质上是一个参变气动弹性系统，参变系统的建模方法对发展LPV控制系统的设计至关重要。本项目提出了多参数大型LPV降阶系统的建模方法，建立了突风扰动下参变气动伺服弹性系统模型。数值仿真表明，本项目提出的这种参变气动伺服弹性系统建模方法是十分有效的。. 提出了基于前视突风探测信息的载荷减缓模型预测控制方法。基于飞机前方的先知突风场信息，提出了一种用来减缓大型运输机穿越突风场时引起的增量动态载荷的新的主动控制技术。数值模拟表明，在平稳和非平稳突风环境中，这种控制方法能有效降低飞机遭遇突风时产生的增量翼根弯矩，最高可减缓60%的翼根弯矩载荷。