Abstract
The control-oriented model for intake shock position dynamics in ramjet engine is presented. A typical ramjet engine consists of four parts, supersonic intake, subsonic diffuser, combustor, and supersonic nozzle. The parts are subdivided into nine internal sections depending on the distinguishing flow properties. The subsonic segment flow properties must be determined starting from the nozzle and then progressing upstream. The Mach number and mass flow rate are determined from the Mach number area relation for the nozzle and mass conservation, respectively. The total temperature is obtained by use of the Chemical Equilibrium with Applications (CEA) code and made into a tabular form as a function of equivalence ratio (EQ) and total temperature. The time lag between application of nozzle throat area control input and change in combustor pressure is accommodated in the nozzle actuation dynamics. Equilibrium flow models for the supersonic intake and the subsonic diffuser and combustor are matched at the terminal shock location in the duct.
| Original language | English |
|---|---|
| Pages (from-to) | 499-503 |
| Number of pages | 5 |
| Journal | Journal of Propulsion and Power |
| Volume | 27 |
| Issue number | 2 |
| DOIs | |
| State | Published - 2011 |