RBCC动力天地往返飞行器气动/推进一体化精细解析建模研究

The unique airframe/propulsion integrated design and wide speed, large airspace flight characteristics, have resulted in the model for RBCC-Powered transportation vehicle is more complicated than it for general air-breathing hypersonic vehicle and more challenge to Overall design and control system analysis. This project takes the RBCC-Powered transportation vehicle as the research object, Based on theoretical analysis, numerical simulation and nonlinear parameter identification technology, this project selects the RBCC-Powered transportation vehicle as the research object, mainly performs research in three aspects: 1) Establish the integrated Refinement aerodynamic analysis model containing physical mechanism; 2) Research on full modes performance analysis model for RBCC; 3) Explore the coupling model for the airframe/propulsion integration, which can be used to wide speed, large airspace flight envelope. Through research of the project, the integration aerodynamic analysis model, RBCC performance analysis model and aerodynamic/propulsion integration coupling model are established. These models taking into account the physical details such as the leading edge passivation, viscous interference, mode conversion and so on , have analytical expression, contain physical mechanism and have high accuracy. The research results can provide theoretical basis and technical support for the overall and control system design for the RBCC-powered transportation vehicle. Has a good academic value and engineering application prospects.

由于机身/RBCC动力一体化设计以及宽速域、大空域的天地往返飞行特点，RBCC天地往返飞行器比一般吸气式高超声速飞行器的模型更为复杂，使得RBCC天地往返飞行器建模成为总体及控制系统分析中遇到的严重挑战之一。本项目以RBCC天地往返飞行器为研究对象，综合应用理论分析及推导、数值模拟、非线性参数辨识等技术，重点开展三方面的研究：1）建立内涵物理机理的一体化气动精细解析模型；2）研究RBCC全模态性能分析模型；3）探究适应宽速域、大空域飞行包线的气动/RBCC动力一体化耦合建模技术。通过本项目的研究，将建立满足宽速域、大空域天地往返要求的气动、推进及气动/推进一体化耦合模型，该模型具有解析表达式，考虑了诸如前缘钝化、粘性干扰、模态转换等物理细节，内涵物理机理，且具有较高精度。研究成果可为RBCC天地往返飞行器总体及其控制系统设计提供理论依据和技术支持，具有较好的学术价值和工程应用前景。

以典型的RBCC组合动力天地往返飞行器为对象，针对宽域飞行、气动/推进耦合特性以及组合动力多模态的特点，通过理论推导、高精度数值模拟以及风洞试验初步建立了RBCC组合动力天地往返飞行器的气动/推进一体化精细理论模型。主要成果包括：1）建立了较为精细的双模态冲压发动机准一维流耦合理论模型，涵盖了马赫数从2.5到10 的双模态冲压发动机的精细准一维流模型；具有较快的计算效率，单个状态计算的时间相比CFD数值模拟提升了近300倍；具有较高的计算精度，与高精度模型及试验数据对比均方误差不超过20%；具有较大的应用前景，已经应用于航天科技、航天科工、中航工业相关单位的预研项目，取得了较好的应用效果。2）建立了超/高超声速飞行器的气动力快速计算模型。具有较宽的使用范围，能够适应于马赫数大于2，飞行高度60km以内的任意复杂外形的气动力快速计算；具有较高的计算效率，单个状态计算的时间相比CFD数值模拟提升了近300倍；具有较高的计算精度，与三维数字模拟对比，计算误差不超过20%；具有较低的网格量，针对复杂的外形网格不超过3000个，而需要同样计算精度的CFD数值计算的网格至少几十万量，减小了计算人员的工作量；具有较大的应用前景，该项成果已经应用于航天科技、航天科工、中航工业相关单位的预研项目，取得了较好的应用效果，取得了较好的应用效果。.在本项目的支持下，发表学术论文20篇以上，SCI检索论文8篇，出版了国内第一本气动/推进一体化理论建模的学术专著，相关成果作为主要科技创新分别获得了2017年军队科技进步二等奖1项，2020年的军队科技进步二等奖 1项，培养了硕博研究生8名，协助培养本科生8名。