Stage separation scheme design for tandem-configured hypersonic vehicle based on numerical virtual flight
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摘要:
串联式高超声速飞行器在与助推器分离过程中存在非线性多体干扰和姿态易失稳等问题，严重影响飞行安全性与可靠性，传统分离仿真方法难以精准捕捉这一复杂动态过程。为此提出了面向串联高超飞行器级间分离的数值虚拟飞行方法，构建气动-运动-控制耦合仿真平台，在马赫数为10的速度下对不同的分离方案进行设计评估，综合考虑初始分离姿态、分离机构作动与分离控制策略等因素，实现了级间分离的高精度仿真与方案评估。研究结果表明：迎角为4°时初始姿态可使两级接近配平，提升分离初期稳定性；采用液压撑杆分离机构较自由分离，在0.2 s时刻可使级间相对轴向距离增加0.49 m，并将级间相对俯仰角降低约52%；此外，采用非线性动态逆控制系统可显著提升分离过程的姿态稳定性，在高增益控制参数下使主级俯仰角波动幅度较无控状态降低约90%。最终方案满足了安全分离指标，为两级分离方案设计提供了可靠的数据支撑。
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关键词:
- 串联式高超声速飞行器 /
- 两级分离方案 /
- 气动-运动-控制耦合 /
- 数值虚拟飞行 /
- 非线性动态逆
Abstract:Tandem hypersonic vehicles suffer from nonlinear multibody interference and attitude instability during booster separation, which seriously affect flight safety and reliability. Conventional separation simulation methods have difficulty in capturing this complex dynamic process accurately. A Numerical Virtual Flight method for tandem hypersonic vehicle stage separation was proposed, and an aerodynamics-motion-control coupled simulation platform was established. Different separation schemes were designed and evaluated at Mach 10 by considering the initial separation attitude, separation-mechanism actuation, and separation control strategy. The results showed that an initial angle of attack of 4° brought the two stages close to trim and improved the initial separation stability. Compared with free separation, the hydraulic strut separation mechanism increased the relative axial distance between the two stages by 0.49 m at 0.2 s and reduced the relative pitch angle by about 52%. The nonlinear dynamic inversion control system further improved attitude stability during separation; under high-gain control parameters, the pitch-angle fluctuation amplitude of the main stage was reduced by about 90% compared with the uncontrolled case. The final scheme satisfies the safe-separation criteria and provides reliable data support for two-stage separation scheme design.
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图 1 串联式布局飞行器几何布局与尺寸（单位: m）
Figure 1. Geometric information of the tandem-configuration hypersonic flight vehicle （unit: m）
图 2 串联式布局高超声速飞行器内流道与导流槽形状
Figure 2. Illustration of the internal channel of the main stage and diversion groove of the booster
图 3 串联式布局高超声速飞行器级间分离过程
Figure 3. Stage separation process of the tandem-configuration hypersonic flight vehicle
图 4 CFD/RBD/FCS耦合的数值虚拟飞行仿真流程
Figure 4. CFD/RBD/FCS coupled numerical virtual flight simulation flowchart
图 8 AEDC多体分离标模几何尺寸图（单位：m）
Figure 8. Geometric information of the AEDC multi-body separation standard model （unit：m）
图 9 AEDC多体分离数值仿真与实验数据对比
Figure 9. Comparison between numerical simulation and experimental data of the AEDC multi-body separation
图 11 HBS标模数值仿真与实验数据对比
Figure 11. Comparison between numerical simulation and experimental data of the HBS standard model
图 12 主级与助推级静态气动特性
Figure 12. Static aerodynamic characteristics of the main stage and booster
图 13 主级与助推级过载随迎角变化示意图
Figure 13. Variation of load factors with angle of attack for the main stage and booster
图 15 不同分离机构作用下的级间运动参数
Figure 15. Interstage motion parameters under different separation mechanisms
图 16 不同分离机构作用下的压力云图
Figure 16. Pressure contours under different separation mechanisms
图 17 不同控制方法下的运动参数
Figure 17. Interstage motion parameters under different control methods
表 1 串联布局高超声速飞行器基本参数
Table 1. Basic parameters of the tandem-configuration hypersonic flight vehicle
参数 主级 助推级 参考面积/m2 7.3 7.2 参考长度/m 3.5 5.5 质量/kg 1800 1600 重心位置/m （2.6, 0, 0） （8.0, 0, 0） 转动惯量/（kg·m2） 1400 2762 
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表 2 网格无关性验证算例
Table 2. Grid-independence verification case
网格量/万 相对误差/% 升力系数 阻力系数 432 3.41 1.24 654 1.72 0.71 862 0.16 0.11 1287
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表 3 分离运动控制方法
Table 3. Separation motion control methods
工况编号 控制方法 控制参数 1 开环 固定配平舵偏−0.26° 2 闭环 Kp=50, Kd=10 3 闭环 Kp=100, Kd=20
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[1] 宋威, 艾邦成. 多体空气动力学研究进展[J]. 力学学报, 2022, 54(6): 1461-1484. Song Wei, Ai Bangcheng. Research progress on multibody aerodynamics[J]. Chinese Journal of Theoretical and Applied Mechanics, 2022, 54(6): 1461-1484. (in Chinese doi: 10.6052/0459-1879-22-096Song Wei, Ai Bangcheng. Research progress on multibody aerodynamics[J]. Chinese Journal of Theoretical and Applied Mechanics, 2022, 54(6): 1461-1484. (in Chinese) doi: 10.6052/0459-1879-22-096 [2] 宋威, 艾邦成. 多体分离动力学研究进展[J]. 航空学报, 2022, 43(9): 025950. Song Wei, Ai Bangcheng. Multibody separation dynamics: review[J]. Acta Aeronautica et Astronautica Sinica, 2022, 43(9): 025950. (in ChineseSong Wei, Ai Bangcheng. Multibody separation dynamics: review[J]. Acta Aeronautica et Astronautica Sinica, 2022, 43(9): 025950. (in Chinese) [3] Blocker W, Ruebush D. X-43A stage separation system: a flight data evaluation: AIAA 2005-3335[R]. Capua, Italy: AIAA, 2005. [4] Marshall L, Bahm C, Corpening G, et al. Overview with results and lessons learned of the X-43A Mach 10 flight: AIAA2005-3336[R]. Capua, Italy: AIAA, 2005. [5] Davis M C, Sim A G, Rhode M, et al. Wind-tunnel results of the B-52B with the X-43A stack[J]. Journal of Spacecraft and Rockets, 2007, 44(4): 871-877. doi: 10.2514/6.2006-3850 [6] 林敬周, 王雄, 钟俊, 等. 高马赫数多体分离试验技术研究与应用[J]. 推进技术, 2020, 41(4): 925-933. Lin Jingzhou, Wang Xiong, Zhong Jun, et al. Investigation and application of high Mach number multi-body separation test technique[J]. Journal of Propulsion Technology, 2020, 41(4): 925-933. (in ChineseLin Jingzhou, Wang Xiong, Zhong Jun, et al. Investigation and application of high Mach number multi-body separation test technique[J]. Journal of Propulsion Technology, 2020, 41(4): 925-933. (in Chinese) [7] 宋威, 蒋增辉. 串联飞行器级间分离风洞自由飞试验[J]. 空气动力学学报, 2017, 35(5): 687-692. Song Wei, Jiang Zenghui. Wind tunnel free-flight test for stage separation of tandem layout vehicle[J]. Acta Aerodynamica Sinica, 2017, 35(5): 687-692. (in ChineseSong Wei, Jiang Zenghui. Wind tunnel free-flight test for stage separation of tandem layout vehicle[J]. Acta Aerodynamica Sinica, 2017, 35(5): 687-692. (in Chinese) [8] Liever P, Habchi S, Engelund W, et al. Stage separation analysis of the X-43A research vehicle: AIAA2004-4725[R]. Providence, US: AIAA, 2004. [9] 赵飞, 刘丽玲, 石泳, 等. 类X-43A飞行器高超声速分离仿真[J]. 航空学报, 2022, 43(5): 125171. Zhao Fei, Liu Liling, Shi Yong, et al. Hypersonic separation simulation of aerocraft similar to X-43A[J]. Acta Aeronautica et Astronautica Sinica, 2022, 43(5): 125171. (in ChineseZhao Fei, Liu Liling, Shi Yong, et al. Hypersonic separation simulation of aerocraft similar to X-43A[J]. Acta Aeronautica et Astronautica Sinica, 2022, 43(5): 125171. (in Chinese) [10] Zhang Laiping, Chang Xinghua, Ma Rong, et al. A CFD-based numerical virtual flight simulator and its application in control law design of a maneuverable missile model[J]. Chinese Journal of Aeronautics, 2019, 32(12): 2577-2591. doi: 10.1016/j.cja.2019.07.001 [11] Yan Lang, Chang Xinghua, Wang Nianhua, et al. Numerical virtual flight investigation for longitudinal maneuver of a generic fighter based on machine learning[J]. Physics of Fluids, 2024, 36(7): 077131. doi: 10.1063/5.0208437 [12] Guo Wenhua, Fu Jiawei, He Pengzhen, et al. Numerical investigation of stage separation control of tandem hypersonic vehicles based on lateral jet[J]. Aerospace, 2025, 12(4): 286. doi: 10.3390/aerospace12040286 [13] Bisek N J. High-fidelity simulations of the HIFiRE-6 flow path at angle of attack: AIAA2016-4276[R]. Washington DC, US: AIAA, 2016. [14] Bolender M, Staines J, Dolvin D. HIFiRE 6: an adaptive flight control experiment: AIAA2012-252[R]. Nashville, US: AIAA, 2012. [15] 杨胜江, 刘超逸. 美国高超声速飞行器级间分离控制技术研究[J]. 飞航导弹, 2014(11): 34-42. Yang Shengjiang, Liu Chaoyi. Research on control technology of stages separation for American hypersonic vehicle[J]. Aerodynamic Missile Journal, 2014(11): 34-42. (in ChineseYang Shengjiang, Liu Chaoyi. Research on control technology of stages separation for American hypersonic vehicle[J]. Aerodynamic Missile Journal, 2014(11): 34-42. (in Chinese) [16] Xiao Tianhang, Zhi Haolin, Deng Shuanghou, et al. Enhancement on parallel unstructured overset grid method for complex aerospace engineering applications[J]. Chinese Journal of Aeronautics, 2023, 36(1): 115-138. doi: 10.1016/j.cja.2022.07.015 [17] Zhi Haolin, Deng Shuanghou, Xiao Tianhang, et al. Enhancement on parallel wall distance calculation methodology for partitioned unstructured grid[J]. International Journal for Numerical Methods in Fluids, 2023, 95(4): 557-578. doi: 10.1002/fld.5161 [18] 秦帆. 飞行器机动飞行气动-运动-控制耦合数值模拟研究[D]. 南京: 南京航空航天大学, 2023. Qin Fan. CFD/6DOF/FCS coupling simulation of flight vehicle maneuver [D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2023. (in ChineseQin Fan. CFD/6DOF/FCS coupling simulation of flight vehicle maneuver [D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2023. (in Chinese) [19] Tian Shuling, Fu Jiawei, Chen Jiangtao. A numerical method for multi-body separation with collisions[J]. Aerospace Science and Technology, 2021, 109: 106426. doi: 10.1016/j.ast.2020.106426 [20] Menter F R. Two-equation eddy-viscosity turbulence models for engineering applications[J]. AIAA Journal, 1994, 32(8): 1598-1605. doi: 10.2514/3.12149 [21] Yoon S, Jameson A. Lower-upper symmetric-Gauss-seidel method for the Euler and navier-stokes equations[J]. AIAA Journal, 1988, 26(9): 1025-1026. doi: 10.2514/3.10007 [22] 刘世前. 现代飞机飞行动力学与控制[M]. 2版. 上海: 上海交通大学出版社, 2018: 151-158. Liu Shiqian. Flight dynamics and control of modern aircrafts[M]. 2nd ed. Shanghai: Shanghai Jiao Tong University Press, 2018: 151-158. (in ChineseLiu Shiqian. Flight dynamics and control of modern aircrafts[M]. 2nd ed. Shanghai: Shanghai Jiao Tong University Press, 2018: 151-158. (in Chinese) [23] Miller C. Nonlinear dynamic inversion baseline control law: architecture and performance predictions: AIAA2011-6467[R]. Portland, US: AIAA, 2011. [24] Da Costa R R, Chu Q P, Mulder J A. Reentry flight controller design using nonlinear dynamic inversion[J]. Journal of Spacecraft and Rockets, 2003, 40(1): 64-71. doi: 10.2514/2.3916 [25] Sieberling S, Chu Q P, Mulder J A. Robust flight control using incremental nonlinear dynamic inversion and angular acceleration prediction[J]. Journal of Guidance, Control, and Dynamics, 2010, 33(6): 1732-1742. doi: 10.2514/1.49978 [26] Snyder D, Koutsavdis E, Anttonen J. Transonic store separation using unstructured CFD with dynamic meshing: AIAA2003-3919[R]. Orlando, US: AIAA, 2003. [27] East R A, Hutt G R. Comparison of predictions and experimental data for hypersonic pitching motion stability[J]. Journal of Spacecraft and Rockets, 1988, 25(3): 225-233. doi: 10.2514/3.25975 [28] 姜权峰, 陈树生, 杨华, 等. 两级入轨航天器级间分离姿态精确控制[J]. 航空学报, 2024, 45(13): 129270. Jiang Quanfeng, Chen Shusheng, Yang Hua, et al. Precise control of interstage separation attitude of two-stage-to-orbit vehicle[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(13): 129270. (in Chinese doi: 10.7527/S1000-6893.2023.29270Jiang Quanfeng, Chen Shusheng, Yang Hua, et al. Precise control of interstage separation attitude of two-stage-to-orbit vehicle[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(13): 129270. (in Chinese) doi: 10.7527/S1000-6893.2023.29270 -
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