Abstract
An integrated analysis method for a rocket-augmented turbine-based combined cycle (TBCC) engine is proposed based on the trajectory optimization method of the Gauss pseudospectral. The efficiency and energy of the vehicles with and without the rocket are analyzed. Introducing an appropriate rocket to assist the TBCC-powered vehicle will reduce the total energy consumption of drag, and increase the vehicle efficiency in the transonic and the mode transition. It results in an increase in the total efficiency despite a reduction in engine efficiency. Therefore, introducing a rocket as the auxiliary power is not only a practical solution to enable flight over a wide-speed range when the TBCC is incapable but also probably an economical scheme when the the TBCC meets the requirements of thrust. When the vehicle drag is low, the rocket works for a short time and its optimal relative thrust is small. Thus, the TBCC combined with a booster rocket will be a more simple and suitable scheme. When the vehicle drag is high, the operating time of the rocket is long and the optimal relative thrust is large. The specific impulse has a significant impact on the flight time and the total fuel consumption. Accordingly, the combination form for the rocket-based combined cycle (RBCC) engines and the turbine will be more appropriate to obtain higher economic performance.
Highlights
Turbine-based combined cycle (TBCC) engines are believed to be a promising means of power for wide-speed range hypersonic vehicles [1]
The “rocket-augmented turbine-based combined cycle (TBCC)” concept has been proposed as a near-term solution, where the rockets are used as auxiliary power for thrust augmentation when extra thrust is needed
201.6 kg of fuel is saved during the transition, which improves the economic performance of the TBCC vehicle even with the additional mode transition, which improves the economic performance of the TBCC vehicle even with the fuel consumption resulting from the drag of the rocket
Summary
Turbine-based combined cycle (TBCC) engines are believed to be a promising means of power for wide-speed range hypersonic vehicles [1]. Several technical issues with TBCC engines still exist, such as “Thrust Pinch”, so the engines are incapable of providing sufficient thrust for acceleration during transonic and mode transition [3] To resolve this problem, the “rocket-augmented TBCC” concept has been proposed as a near-term solution, where the rockets are used as auxiliary power for thrust augmentation when extra thrust is needed. The rocket-matching analysis based on trajectory optimization is necessary for the integrated design of the rocket-augmented TBCC. The Gauss pseudospectral method could be directly used to evaluate the integrated design of a rocket-augmented TBCC under different rocket schemes, and the results from trajectory optimization could be used for choosing the appropriate combination form for rockets and TBCCs for vehicle systems.
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