Modeling Of Series Parallel Hybrid TBCC Aeroengine With Symmetrical Thrust Configuration

As the technological commanding heights of the aerospace field in the 21st century,hypersonic aircraft will bring revolutionary breakthroughs to aerospace technology.The research on the power device required by hypersonic aircraft—the combined cycle power engine can achieve hypersonic flight the essential.With the development of related research,the idea of making a variety of combined propulsion devices work in their respective optimal ranges to obtain the best propulsion effect has prompted various combined cycle power engines to be proposed,with turbojet Turbine-based combined cycle engines with engines as the main feature have received extensive attention from various aviation powers due to their good engineering application prospects.The multi-channel turbo-jet ramjet combined engine solution is based on the turbine engine and integrates ramjet and rocket engines.It has high technological maturity,good inlet flow regulation and starting performance,and short development cycle.It provides another way for the development of TBCC in my country.Development path.Based on this scheme,this research realizes the modeling of serial-parallel hybrid TBCC aeroengine with symmetrical thrust layout.Domestic research on TBCC modeling lacks high-fidelity component-level models,and there are more complex coupling relationships in the TBCC engine.Based on the existing conditions,this research starts from the structure of each subsystem of the combined engine and completes the main tasks as follows:(1)According to the physical structure characteristics of the engine and the principle of aerodynamics and thermodynamics,the T-MATS module is used to establish the component-level model of the turbojet engine and the speed control system,and the component-level performance model of the sub-combustion ramjet is built according to the shock wave principle.And analyze its characteristics;(2)Based on the characteristics of the serial-parallel-parallel layout,an integrated component-level model of the scramjet was established,the mixed-compression inlet design was designed and the characteristics of the scramjet were analyzed,and the problem of avoiding the thrust gap was proposed.The sub-combustion stamping mode and the ejection mode are established.According to the analysis of the manifold of the combined air inlet device in the XTER scheme,the TBCC model is established;(3)Determine the flight conditions of the aircraft and the working range of each mode of the engine according to the background of the subject,establish the complete model of the combined cycle engine according to the working coupling relationship of each subsystem,and finally set the mode switching rules according to the working characteristics of each subsystem.Correlation analysis of modal switching characteristics.In summary,this article applies the component-level modeling method to build the performance model of the combined cycle engine subsystem components,and builds the complete model of the combined cycle engine with complex coupling relationships.It provides a suitable platform for the TBCC control algorithm and provides a suitable platform for TBCC mode switching.And optimization work is of great significance.