| Article ID | Journal | Published Year | Pages | File Type |
|---|---|---|---|---|
| 856762 | Procedia Engineering | 2015 | 7 Pages |
Abstract
This paper describes the designing process of rocket engine with thrust 25N for system of orientation and starting of spacecraft instead the prototype with burnout chamber defect that was not fixed during the development to completely exclude the burnout possibility. The new version of the engine has been designed and additional research with CFD-modeling has been performed to completely exclude burnout possibility.
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Physical Sciences and Engineering
Engineering
Engineering (General)
