Optimum Nozzle Angle of a Micro Solid-propellant Thruster
SCIE
SCOPUS
- Title
- Optimum Nozzle Angle of a Micro Solid-propellant Thruster
- Authors
- Inho Kim; Lee, JW; Choi, MK; S.J. Kwon
- Date Issued
- 2011-08
- Publisher
- Taylor and Francis
- Abstract
- The characteristics of supersonic flow field and thrust for a micronozzle used in a microthruster were analyzed numerically to determine the optimum nozzle geometry. Typical parameter values are 300 mu m throat diameter, 10 bar and 1000 K for stagnation conditions, and 1-100 ms for combustion completion. The effects of the boundary layer, heat loss, and unsteady stagnation conditions were considered. Thrust was much more dependent on the nozzle expansion angle than the area ratio or length. Optimum nozzle expansion angle for maximum thrust was close to 30 degrees for a planar 2D nozzle and 25 degrees for a 2D axisymmetric nozzle.
- Keywords
- micro solid-propellant thruster; micronozzle; optimum angle; SPRAY PROCESS; PERFORMANCE
- URI
- https://oasis.postech.ac.kr/handle/2014.oak/16765
- DOI
- 10.1080/15567265.2011.597491
- ISSN
- 1556-7265
- Article Type
- Article
- Citation
- NANOSCALE AND MICROSCALE THERMOPHYSICAL ENGINEERING, vol. 15, no. 3, page. 165 - 178, 2011-08
- Files in This Item:
- There are no files associated with this item.
Items in DSpace are protected by copyright, with all rights reserved, unless otherwise indicated.