English (United Kingdom)

https://curated-unify.zendy.io/wp-json/zendy-region/v1/featured_content/oa?rat=en

https://curated-unify.zendy.io/wp-json/zendy-region/v1/highlighted_journal/

Global: Zendy Plus annual

Presents the access of premium content as premium feature

Premium Content

Presents the keyphrase highlighting as premium feature

Keyphrase Highlighting

Presents the summarisation as premium feature

Summarisation

Insights

Presents the pdf analysis as premium feature

PDF Analysis

Presents the zaia usage as premium feature

ZAIA

Global: Zendy Plus monthly

Global: Zendy Tools annual

Global: Zendy Tools monthly

Global: Zendy Free Plan

Converging diverging micro nozzle is fundamentally intended for flowacceleration through the generation of kinetic energy for the advancedmicro-propulsion systems. Such supersonic micro nozzles have significantapplications in the launching, propulsion and rapid directional control of themicro-satellites for a better maneuver. Micro scale analysis of such flowdevices is extended to the rarefied flow regime. Present study has addressedthrust vectoring in a planar converging-diverging supersonic micro nozzle bythe bypass mass injection technique. Direct Simulation Monte Carlo (DSMC)method has been used for numerical modelling. Primary focus is given on thethrust vectoring control of the micro nozzle with a throat height of 20 micrometer and an expansion ratio of 1.7. For the secondary injection, a rectangularchannel of 5 different bypass widths (2 - 12 micro meter) is considered for twodifferent outlet pressures (Pout = 10 kPa and 40 kPa) while keeping the inletpressure (Pin) and temperature (Tin) fixed at 1 atm and 300 k respectively. Thephysical behavior of the micro nozzle is acknowledged through the analysis ofMach, pressure, temperature and density contours. Numerical results reveal thatthe secondary flow injection is adapted into the primary flow through theformation of a pressure bump in the diverging section. Moreover, the total massflow rate, secondary flow percentage, thrust force, the thrust coefficient andspecific impulse increase with the bypass channel width. A change in thrustdirection is obtained which in turn produces a considerable vectoring effect inthe supersonic micro nozzle. The vectoring angle for Pout of 40 kPa peaks at 6micro meter bypass channel whereas a gradual increase of the vectoring anglewith the bypass channel width is observed for Pout = 10 kPa.

Direct Simulation Monte Carlo Analysis on Thrust Vectoring of a Supersonic Micro Nozzle using Bypass Mass Injection