| Popis: |
This paper comprises the methodology applied for the performance assessment of a throttleable ducted rocket (TDR) powered lower tier interceptor achieving average flight Mach numbers in the vicinity of M > 5. Contrary to conventional ground-to-air systems, that are accelerated by a solid propellant rocket motor and go into cruise flight after rocket motor tail-off, a TDR driven system provides a continuous thrust profile that depends on the flight conditions and a controlled injection of fuel into the combustion chamber. Whereas the flight conditions determine the physical stability of the system by the air intake performance, the efficiency of the combustion process within the combustion chamber determines the thrust generation and the required air intake performance in form of total pressure recovery for a given captured air mass flow. After a short description of the motor and its functionality, the simulation methodology and its validation measures are discussed. Finally, the operational potential of such a system is discussed by an analysis of the motor performance along hypothetical trajectories. |
