Abstract
One of the most critical challenges for the turbine-based combined cycle (TBCC) propulsion system utilized in the next generation hypersonic aircraft lies in the efficient operation from Mach 0 to Mach 5. This results in a need to investigate the well matching of the hypersonic inlet and the TBCC engine along the wide flight regime. In order to get better installed performance of Mach 5 TBCC engine, Newton-Raphson algorithm is adopted to investigate the integrated optimization design of the multi-variable combination adjusting laws of inlet/TBCC engine in different flight sections which include the hypersonic cruise section, the climbing section of ramjet mode and the climbing section of turbofan mode. How to guarantee the variable geometries function of the inlet/engine efficiently along the wide flight regime is one of the most critical technology challenges. The innovation point of the paper lies in that it affords an integrated optimization design of the adjustable geometries of inlet and the control laws of TBCC engines, using the multi-dimensional Newton-Raphson algorithm, which can achieve lower fuel consumption and better installed performance along the wide operating range, which is beneficial for the conceptual design and performance research of Mach 5 TBCC propulsion system. Meanwhile, the integrated optimization design method could also be applied to the power systems of multiple adjustable mechanisms, in order to increase the energy efficiency.
Published Version
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