Abstract Evaluating the climbing performance of rocket-based combined cycle (RBCC) powered aircraft has a guiding role for single-stage to orbit. This study establishes a new modularized thrust model of the RBCC engine for low speeds (Ma ∞ = 0.8–3) based on independent ramjet stream and pressure matching. The model can quickly estimate the quasi one-dimensional flow characteristics of secondary flow and primary flow at given runner geometry and operating conditions. Comparison with experimental results shows that the thrust model is correct. In this model, the influence of altitude, Mach number, and rocket flow on thrust and specific impulse is considered. The model was used to optimize the climbing trajectory of RBCC powered aircraft with a typical lifting-body. The comparison of RBCC propulsion and pure rocket propulsion shows that the former offers propellant saving advantages. During the climb, the RBCC powered aircraft needs to strictly control the air flow rate and ensure the pressure matching in the flow path to improve propulsion efficiency.
Highlights The calculation program can rapidly estimate engine thrust and specific impulse. Pressure mismatch occurs when primary flow increase within low flight Mach number. Flight altitude increase at low Mach numbers is beneficial for thrust enhancement. Air flow has a great influence on total thrust after the secondary flow is ignited. RBCC propulsion has advantages in fuel saving compared to pure rocket propulsion.
Climbing performance analysis of rocket-based combined cycle engine powered aircraft
Acta Astronautica ; 162 ; 135-144
2019-05-21
10 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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