Acoustic data collected in static rocket tests are typically influenced by ground reflections, but have been difficult to account for. First, the rocket plume is an extended radiator whose directionality results from source correlation. Second, partial coherence of the ground interaction due to atmospheric turbulence can play a significant role, especially for larger propagation distances. In t...

Typical solid rocket motors (SRM) have advantage of their inherent simplicity and reliability, but they do not have the capability to change thrust profile like other propulsion system. Pintle technology is one of the means to achieve variable and programmable thrust. This paper describes a study of the static and dynamic characteristics of a pintle nozzle under the constant mass flow rate. The...

Abstract To meet the application requirements of high-precision and fast-response thrust vector control from a solid rocket motor, digital integrated servo controller for four brushless direct current motors was designed implemented. The hardware system proposed in this paper includes circuit module drive module. former mainly power conversion circuit, DSP A/D SPI communication interface SCI ci...

We have studied the ignition of liquid fuel and certain solid fuels by the photoignition of single wall carbon nanotubes (SWCNTs). Our investigation includes the effect of solid additives such as aluminum nano-particles and solid oxidizers such as ammonium perchlorate (AP) on the photoignition characteristics. We have shown that by mixing CNT with other nanoparticles and powdered material, the ...

A numerical simulation of the gas-dynamic processes in thrust vectorable nozzle solid rocket motor is considered. Construction a geometric model and generation computational mesh, reconstruction mesh at each time step are discussed. Calculations flowfield combustion products pre-nozzle chamber block carried out for various angles rotation. The distributions gas dynamic quantities volume corresp...

A method for the simulation of flows involving a disperse particle phase and a rarefied gas is extended for increased accuracy and efficiency in modeling the high altitude plume flow from a solid propellant rocket. First, a procedure is presented so that calculations involving the interphase transfer of momentum and energy may be avoided in regions where these calculations will have negligible ...