| Article ID | Journal | Published Year | Pages | File Type |
|---|---|---|---|---|
| 1718838 | Aerospace Science and Technology | 2007 | 6 Pages |
Abstract
The review of research avenues for working processes (ignition, combustion, etc.) in hybrid rocket engines (HRE), for thermal protection and power characteristics is stated. Based on conducted design and exploratory studies and design developments, the reasonable fields of application of HRE to launch systems for orbit insertion of payload are determined.
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Aerospace Engineering
