Engineering Commons^™

Hole-Type Aerospike Compound Nozzle Thrust Vectoring, Stanley Ikuo Beebe

Master's Theses

Compound aerospike nozzles were designed and tested as part of an ongoing

experimental study to determine the feasibility of thrust vectoring an aerospike

nozzle with the addition of a secondary port. Earlier phases of the study have

indicated that a compound aerospike nozzle could provide sufficient thrust

vectoring. The addition of a hole-type secondary port was found to provide

effective thrust vectoring.

Experiments were carried out to determine the effects of secondary port size,

secondary port inlet geometry and compound aerospike nozzle chamber

pressure. Results show good predictability, axisymmetric flow, and emphasize

the importance of a radius on secondary port …

Simulation Of An Oxidizer-Cooled Hybrid Rocket Throat: Methodology Validation For Design Of A Cooled Aerospike Nozzle, Peter Alexander Brennen

Master's Theses

A study was undertaken to create a finite element model of a cooled throat converging/diverging rocket nozzle to be used as a tool in designing a cooled aerospike nozzle. Using ABAQUS, a simplified 2D axisymmetric model was created featuring only the copper throat and stainless steel support ring, which were brazed together for the experimental test firings. This analysis was a sequentially coupled thermal/mechanical model. The steady state thermal data matched closely to experimental data. The subsequent mechanical model predicted a life of over 300 cycles using the Manson-Halford fatigue life criteria. A mesh convergence study was performed to establish …