An Evaluation of Next Generation Rocket Engines for VT SSTO RLV

Observing that the majority of SSTO programs failed due to the propulsion system being far ahead of its time. Furthermore, acknowledging the that the private launch markets is increasingly dominated by partly reusable TSTOs. This thesis aims to evaluate whether next generation rocket engines make an SSTO viable within a foreseeable economical...

Designing and optimizing an aerospike micro-nozzle for the sub-mN range: A numerical study

Micro-propulsion technology is under rapid development and considerably extends the mission capabilities of small spacecraft. However, the flow in conventional nozzles on a microscale is relatively viscous, which, combined with the bounding nozzle walls, leads to low efficiencies. Aerospike nozzles, on the other hand, offer...

Numerical Investigation of the Effect of Base Bleed on Thrust of a Truncated Aerospike Nozzle in Off-design Conditions

Aerospike nozzles are known to produce more thrust than conventional convergent-divergent nozzles in off-design conditions because of their capability to adapt their boundaries to ambient conditions. However, the central plug of an ideal aerospike nozzle can be very long and heavy, and its sharp end is susceptible to deformation in high...