基于气动/轨迹/控制耦合的飞/发一体高超声速飞机气动外形优化设计  

Aerodynamic shape optimization design of airframe/propulsion integrated hypersonic aircraft with aerodynamics/trajectory/control coupling

作　　者：屈峰 王青 程少文 王开强[3] QU Feng;WANG Qing;CHENG Shaowen;WANG Kaiqiang(School of Aeronautics,Northwestern Polytechnical University,Xi’an 710072,China;National Key Laboratory of Aircraft Configuration Design,Xi’an 710072,China;China Academy of Space Technology,Beijing 100094,China)

机构地区：[1]西北工业大学航空学院,西安710072 [2]飞行器基础布局全国重点实验室,西安710072 [3]中国空间技术研究院,北京100094

出　　处：《航空学报》2025年第4期51-67,共17页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(11972308,52272378)。

摘　　要：针对吸气式高超声速飞机飞/发一体布局面临的多学科耦合问题,提出了一种基于飞行任务需求、考虑气动/轨迹/控制等学科的内外嵌套2层多学科优化设计方法。首先,以航程或航时等飞行性能为优化目标、飞行可控为约束、SQP为优化算法建立了外层飞行器外形参数优化方法。其次,采用RANS方法对选定外形开展气动特性评估,并基于所得气动数据建立了几何参数到气动特性的映射模型。随后,在基准动力数据(初始构型动力数据)的基础上,建立了考虑前体参数及尾喷管参数影响的冲压发动机推力模型。然后,以与外层相同的性能目标为优化目标、飞行可控为约束,选用直接打靶法、SQP算法分别作为轨迹离散策略与优化算法,建立了内层轨迹优化方法。最后,将内、外层优化相结合,并通过采用自抗扰控制技术开展飞行轨迹可控性评估,实现了适用于飞/发一体高超声速飞行器的内外嵌套2层多学科优化设计方法。以类SR-72高超声速飞机为对象,针对典型前体/进气道一体化参数和后体/尾喷管一体化参数,开展了以航程最优为目标的优化设计。优化结果表明:在整个飞行任务中,优化设计外形在初始外形基础上最大航程增大了28.98%,性能得到显著提升,验证了所提出的气动/轨迹/控制多学科优化设计方法的有效性。To address the multidisciplinary coupling problem faced by the air-breathing hypersonic airframe/propulsion integrated design,a two-layer multidisciplinary optimization design method is proposed based on flight mission require⁃ments and considers aerodynamics,trajectory,and control.Firstly,an optimization method for the geometric param⁃eters is established using sequential quadratic programming to optimize the flight performance such as flight range and duration,with controllability as the constraint.Then,by solving the Reynolds Average Navier-Stokes(RANS)equa⁃tions,the aerodynamic characteristics of the selected shape is obtained.With the obtained aerodynamic data,a map⁃ping model from geometric parameters to aerodynamic characteristics is constructed.Subsequently,based on the ex⁃isting dynamic data,a thrust model of the scramjet engine considering the influence of forebody parameters and nozzle parameters is established.After that,an internal trajectory optimization method is proposed.This method maintains the same optimization objective and constrain as geometric parameter optimization,and adopts the direct shooting method for discrete and the SQP algorithm for optimization.In addition,a control simulation model is con⁃structed based on,which was combined with the to establish an aerodynamic,trajectory and control integrated design method inner trajectory optimization and outer parameter optimization are combined and the Active Disturbance Rejec⁃tion Control(ADRC)technology is used evaluate trajectory controllability,achieving two-layer multidisciplinary optimi⁃zation for airframe/propulsion integrated design.Finally,optimization of the shape parameters and aircraft trajectory of the SR-72-like hypersonic vehicle are carried out to achieve the optimal range.The optimization results show that the maximum range is increased by 28.98%during the whole flight mission,demonstrating the effectiveness of the pro⁃posed method.

关 键 词：飞/发一体 高超声速飞行器 多学科优化设计 轨迹优化 气动优化 

分 类 号：V211.48[航空宇航科学与技术—航空宇航推进理论与工程]