Turbocharged solid propellant ramjet (TSPR) is the combination of solid propellant gas generator air turbo ramjet (ATR)with solid ramjet, is cycle of augmented ATR, the parametric performance calculation were carried out for TSPR, The effects of independent design parameters including parameters of compressor and turbine and propellants were studied and the preferred compressor, turbine and propellants were obtained for TSPR; The operation envelop of TSPR and ATR were obtain under the preferred component limitation, the results shows that TSPR offers wide speed-altitude operation envelope, high specific thrust, high specific impulse, it is combining the advantages of the ATR and solid ramjet, and suitable for tactical missiles application meets potential requirements for boosting and cruising.
The design and characteristic analysis of the single-stage centrifugal compressor were performed to meet the requirements of the integral performance of a certain solid propellant air turbo rocket (SPATR). Based on the limitation of the geometry and aerodynamic demands, the impeller and diffuser were designed and optimized by considering the disc friction loss and the flow quality. A theoretical approach was applied to evaluate feasibility and primary aerodynamic performance of the compressor. Focused on the operation performance of the compressor, the detailed flow structure in the compressor was investigated by using numerical simulation. The results show that the total pressure ratio and isentropic efficiency of the compressor in design point are 3.5 and 0.78 respectively, which meets the design demands. The compressor has excellent aerodynamic characteristics during the starting procedure or under the partial loading condition. The position of flow separation and the reason of flow loss are analyzed to conduct further optimization.
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