Separation trajectory safety evaluation platform based on embedded neural network data prediction

WU Anping; LIN Jingzhou; WANG Yan; ZOU Dongyang; XIE Futian

doi:10.7638/kqdlxxb-2024.0076

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Separation trajectory safety evaluation platform based on embedded neural network data prediction

更新时间：2026-05-28

- Separation trajectory safety evaluation platform based on embedded neural network data prediction
- Vol. 43, Issue 3, Pages: 42-50(2025)
- 作者机构：
  
  1. 中国空气动力研究与发展中心超高速空气动力研究所,绵阳,621000
  2. 飞行器流体物理全国重点实验室,绵阳,621000
  3. 南京航空航天大学航空学院,南京,210016
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2024.0076
  CLC： V211.3
- Published：2025
- 稿件说明：
移动端阅览
吴岸平, 林敬周, 王岩, 等. 基于嵌入式神经网络数据预测的多体分离安全评估平台[J]. 空气动力学学报, 2025, 43(3): 42−50.

WU Anping, LIN Jingzhou, WANG Yan, et al. Separation trajectory safety evaluation platform based on embedded neural network data prediction[J]. 2025, 43(3): 42-50.
吴岸平, 林敬周, 王岩, 等. 基于嵌入式神经网络数据预测的多体分离安全评估平台[J]. 空气动力学学报, 2025, 43(3): 42−50. DOI： 10.7638/kqdlxxb-2024.0076

WU Anping, LIN Jingzhou, WANG Yan, et al. Separation trajectory safety evaluation platform based on embedded neural network data prediction[J]. 2025, 43(3): 42-50. DOI： 10.7638/kqdlxxb-2024.0076.

摘要

针对高速飞行器头罩分离等高动态多体分离问题，开展气动特性智能预测与分离轨迹仿真模拟研究，为分离系统设计、分离窗口选择、分离方案优化与评估提供技术支撑。选取典型状态点进行数值模拟计算和网格测力风洞试验，建立气动数据库。采用融合高、低保真度数据的嵌入式神经网络进行学习训练，并结合遗传算法对神经网络结构进行优化，得到的气动力系数预测结果相较网格测力试验结果误差小于5%。在此基础上，采用四阶龙格-库塔法求解飞行器六自由度运动方程，建立了基于神经网络训练结果的分离轨迹仿真模拟方法。通过在不同初始分离条件下开展蒙特卡罗分析和灵敏度分析，评估了影响分离安全的主要因素。研究结果表明，与风洞CTS模拟轨迹结果相比，平台分离轨迹预测可靠，成本代价较低，可快速提升轨迹模拟能力，为分离方案设计提供有力支撑。

Abstract

Aiming at the high dynamic multi-body separation problem of hypersonic vehicle

intelligent prediction of aerodynamic characteristics and simulations of separation trajectory were carried out

which provided technical support for separation system design

separation window selection

separation scheme optimization and evaluation. Typical states were selected to carry out numerical simulations and grid force measurement in wind tunnel tests

thus an aerodynamic database was established. Embedded neural network with high and low fidelity data was used for the learning and training processes

and the structure of neural network was optimized by the genetic algorithm

leading to the error between the predicted aerodynamic coefficients and those of the grid force measurement less than 5%. The fourth-order Runge-Kutta method was used to solve the six-degree-of-freedom motion equation of aircraft

and the separation trajectory simulation method based on neural network training results was established. The Monte Carlo analysis and sensitivity analysis were carried out under different initial separation conditions to evaluate the main factors affecting separation safety. Compared with the capture trajectory system (CTS) simulation results in wind tunnel

the platform is reliable in separation trajectory prediction

and the cost is low

which can quickly improve the trajectory simulation ability and better support the separation scheme design.

关键词

Keywords

references

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