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Ground testing of satellite control thrusters at high altitude conditions

Organized by School of Mechatronic Engineering (UniMAP) & co-organized by The Institution of Engineering Malaysia (IEM), 11th - 13th October 2009 at Batu Feringhi, Penang, Malaysia.

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Bibliographic Details
Main Authors: Manikanda Kumaran, R, Sundararajan, T, David Dason, Raja Manohar, D
Other Authors: tsundar@iitm.ac.in
Format: Working Paper
Language:English
Published: Universiti Malaysia Perlis 2009
Subjects:
High altitude test facility
Large area ratio nozzles
Satellite thrusters
Second throat ejector- diffuser
Artificial satellites > Control systems
Ground support systems (Astronautics)
Online Access:http://dspace.unimap.edu.my/xmlui/handle/123456789/7171
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spelling my.unimap-71712013-12-06T09:44:44Z Ground testing of satellite control thrusters at high altitude conditions Manikanda Kumaran, R Sundararajan, T David Dason Raja Manohar, D tsundar@iitm.ac.in High altitude test facility Large area ratio nozzles Satellite thrusters Second throat ejector- diffuser Artificial satellites -- Control systems Ground support systems (Astronautics) Organized by School of Mechatronic Engineering (UniMAP) & co-organized by The Institution of Engineering Malaysia (IEM), 11th - 13th October 2009 at Batu Feringhi, Penang, Malaysia. Satellite control thrusters are designed to operate at upper atmosphere, where a low pressure environment prevails. During ground testing of such a thruster, the low pressure environment corresponding to the flight situation has to be produced in the vicinity of the rocket thruster with the help of an ejector- diffuser system. The ejector- diffuser may employ the momentum of the rocket exhaust gas and also those of high speed jets issuing from external ejectors, for evacuating the test chamber environment to low pressure. A series of shocks occurring in the diffuser portion aid in the sealing of the evacuated environment and for achieving gradual pressure recovery from the low vacuum level to atmospheric pressure. In the case of small thrusters used in satellite applications, the momentum of the rocket exhaust is too small to create the desired vacuum and a multistage ejector is required to share the evacuation load. In the current study, an attempt has been made to numerically investigate the performance of an ejector- diffuser employed to test large area ratio rocket thrusters. Initially, a decoupled steady state analysis has been carried out to analyze the performance of the multistage ejector system at no- flow and full flow conditions of the rocket motor. Later, simulation has been performed for the rocket motor coupled with the vacuum chamber and the diffuser system. The numerical predictions are validated with available in- house experimental data. 2009-11-04T07:53:20Z 2009-11-04T07:53:20Z 2009-10-11 Working Paper p.1c 1 - 1c 6 978-967-5415-07-4 http://hdl.handle.net/123456789/7171 en Proceeding of International Conference on Applications and Design in Mechanical Engineering 2009 (iCADME 2009) Universiti Malaysia Perlis
institution Universiti Malaysia Perlis
building UniMAP Library
collection Institutional Repository
continent Asia
country Malaysia
content_provider Universiti Malaysia Perlis
content_source UniMAP Library Digital Repository
url_provider http://dspace.unimap.edu.my/
language English
topic High altitude test facility
Large area ratio nozzles
Satellite thrusters
Second throat ejector- diffuser
Artificial satellites -- Control systems
Ground support systems (Astronautics)
spellingShingle High altitude test facility
Large area ratio nozzles
Satellite thrusters
Second throat ejector- diffuser
Artificial satellites -- Control systems
Ground support systems (Astronautics)
Manikanda Kumaran, R
Sundararajan, T
David Dason
Raja Manohar, D
Ground testing of satellite control thrusters at high altitude conditions
description Organized by School of Mechatronic Engineering (UniMAP) & co-organized by The Institution of Engineering Malaysia (IEM), 11th - 13th October 2009 at Batu Feringhi, Penang, Malaysia.
author2 tsundar@iitm.ac.in
author_facet tsundar@iitm.ac.in
Manikanda Kumaran, R
Sundararajan, T
David Dason
Raja Manohar, D
format Working Paper
author Manikanda Kumaran, R
Sundararajan, T
David Dason
Raja Manohar, D
author_sort Manikanda Kumaran, R
title Ground testing of satellite control thrusters at high altitude conditions
title_short Ground testing of satellite control thrusters at high altitude conditions
title_full Ground testing of satellite control thrusters at high altitude conditions
title_fullStr Ground testing of satellite control thrusters at high altitude conditions
title_full_unstemmed Ground testing of satellite control thrusters at high altitude conditions
title_sort ground testing of satellite control thrusters at high altitude conditions
publisher Universiti Malaysia Perlis
publishDate 2009
url http://dspace.unimap.edu.my/xmlui/handle/123456789/7171
_version_ 1643788727297769472
score 13.214268

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