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

doi:10.7527/S1000-6893.2024.30874

Abstract

Abstract:

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 requirements and considers aerodynamics， trajectory， and control. Firstly， an optimization method for the geometric parameters 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） equations， the aerodynamic characteristics of the selected shape is obtained. With the obtained aerodynamic data， a mapping model from geometric parameters to aerodynamic characteristics is constructed. Subsequently， based on the existing 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 constructed 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 Rejection Control （ADRC） technology is used evaluate trajectory controllability， achieving two-layer multidisciplinary optimization 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 proposed method.

Key words: airframe/propulsion integrated, hypersonic vehicle, multidisciplinary design optimization, trajectory optimization, aerodynamic optimization

CLC Number:

V211.48

Feng QU, Qing WANG, Shaowen CHENG, Kaiqiang WANG. Aerodynamic shape optimization design of airframe/propulsion integrated hypersonic aircraft with aerodynamics/trajectory/ control coupling[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(4): 130874.

Figures/Tables 18

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参数	数值
机长/m	23
机高/m	5.5
翼展/m	10
参考面积/m²	92.49
空重/kg	10 000
起飞总重/kg	20 000

参数	前体长度L/m	前体宽度W/m	尾喷管高宽比H∶B
外形参数初值	5	1.6	1.92
外形参数设计优化范围	［4，5.5］	［1.2，1.8］	［1，1.92］

工况	数值
攻角/（°）	-3，0，3，6，9，12
马赫数	0.2，0.8，1，1.1，1.5，2， 2.5，3，3.5，4，5，6
飞行高度/km	0，3，5，6，10，15， 16，18，20，22，25，27.5
舵偏角/（°）	-20，-15，-10，-5，0，5，10，15，20

爬升过程	第1阶段	第2阶段	第3阶段
飞行高度/m	［200，15 000］	［15 000，22 000］	［22 000，27 500］
飞行速度	Ma=［0.4，2］	Ma=［2，3.5］	Ma=［3.5，6］
发动机工作状态	涡轮喷气发动机	涡轮喷气发动机，超燃冲压发动机	超燃冲压发动机

参数	初始构型	优化构型
前体长度/m	5	4.5
前体宽度/m	1.6	1.4
尾喷管高宽比	1.92	1.51
航程/km	2 064.89	2 663.39

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

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飞行阶段	质量流量/（kg·s^-1）
飞行阶段	初始构型	优化构型	相对变化量/%
爬升第3阶段	-6.49	-6.53	+0.62
巡航段	-4.94	-3.36	-32.39

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