Article ID Journal Published Year Pages File Type
1718838 Aerospace Science and Technology 2007 6 Pages PDF
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.

Related Topics
Physical Sciences and Engineering Engineering Aerospace Engineering