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Numerical Simulations of Supersonic Flow in a Linear Aerospike Micronozzle
 

Summary: Numerical Simulations of Supersonic Flow in a
Linear Aerospike Micronozzle
A. Zili´c
D.L. Hitt
A.A. Alexeenko

School of Engineering, University of Vermont

School of Aeronautics & Astronautics, Purdue University
In this study, we numerically examine thrust performance of the linear aerospike nozzle
micro-thruster for various nozzle spike lengths and flow parameters in order to identify optimal
geometry(s) and operating conditions. Decomposed hydrogen-peroxide is used as the monopro-
pellant in the studies. Performance is characterized for different flow rates (Reynolds numbers)
and aerospike lengths, and the impact of micro-scale viscous forces is assessed. It is found that
2-D full micro-aerospike efficiencies can exceed axisymmetric micro-nozzle efficiencies by as
much as 10%; however, severe penalties are found to occur for truncated spikes at low Reynolds
numbers.
I. Introduction
In recent years significant research has been conducted in the area of micropropulsion systems for orbital
maneuvering of next-generation miniaturized satellites (`micro-', `nano-' and `pico-sats') having masses 10 kg or

  

Source: Alexeenko, Alina - School of Aeronautics and Astronautics, Purdue University

 

Collections: Engineering