Research on quasi-one-dimensional modeling and performance analysis of RBCC propulsion system
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Dong Zhang
Abstract
Quasi-one-dimensional model is the most effective way to realize the rapid iterative design of the overall scheme and control system of RBCC aircraft and has become a research hotspot. In the current research, the quasi-one-dimensional model of RBCC propulsion system is simplified. The model does not include physical characteristics such as wall heat transfer, boundary layer change, specific heat ratio change and transonic flow singularity, which makes the accuracy of the model low and cannot adapt to flight control in large airspace. A RBCC model with high accuracy and adaptability to wide-speed fly is established in this paper. Firstly, based on the laws of kinetic energy conservation and energy conservation, the thrust model of ejection mode is established. Secondly, the quasi-one-dimensional flow control equation is deduced, and the physical mechanism models of core flow area, transonic flow, pre-combustion shock train, heat release law and mixing efficiency are established. On this basis, the quasi-one-dimensional flow model of RBCC dual-mode ramjet is established. Thirdly, based on the law of momentum conservation, the mathematical model of rocket mode is deduced, and the thrust model of rocket mode is established. Finally, the accuracy of the quasi-one-dimensional model is verified by CFD numerical simulation and direct-connect experiment. Taking a typical RBCC launch vehicle as an example, the wide-speed performance of the RBCC propulsion system is calculated and analyzed.
Funding source: the National Natural Science Fund of China
Award Identifier / Grant number: 61903301
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Articles in the same Issue
- Frontmatter
- Natural frequency analysis of a functionally graded rotor-bearing system with a slant crack subjected to thermal gradients
- Evaluation of exit pattern factors of an annular aero gas turbine combustor at altitude off-design conditions
- Research on quasi-one-dimensional modeling and performance analysis of RBCC propulsion system
- Performance characteristics of flow in annular diffuser using CFD
- Control-oriented quasi-one dimensional modeling method for scramjet
- Effect of rotor–stator rim cavity flow on the turbine
- An improved aerodynamic performance optimization method of 3-D low Reynolds number rotor blade
- Hot gas ingestion in chute rim seal clearance of gas turbine
- An improved compact propulsion system model based on batch normalize deep neural network
- Study of the vortex chamber and its application for the development of novel measurement and control devices
- Effect of equivalence ratio on the detonation noise characteristics of pulse detonation engine
- Simulation and analysis of hot plume infrared signature based on SNB model
Articles in the same Issue
- Frontmatter
- Natural frequency analysis of a functionally graded rotor-bearing system with a slant crack subjected to thermal gradients
- Evaluation of exit pattern factors of an annular aero gas turbine combustor at altitude off-design conditions
- Research on quasi-one-dimensional modeling and performance analysis of RBCC propulsion system
- Performance characteristics of flow in annular diffuser using CFD
- Control-oriented quasi-one dimensional modeling method for scramjet
- Effect of rotor–stator rim cavity flow on the turbine
- An improved aerodynamic performance optimization method of 3-D low Reynolds number rotor blade
- Hot gas ingestion in chute rim seal clearance of gas turbine
- An improved compact propulsion system model based on batch normalize deep neural network
- Study of the vortex chamber and its application for the development of novel measurement and control devices
- Effect of equivalence ratio on the detonation noise characteristics of pulse detonation engine
- Simulation and analysis of hot plume infrared signature based on SNB model
