Term refers to liquid propellant engines used in ballistic missiles; basic unit is thrust chamber, in which pressure is maintained, and propulsive thrust produced, by continuous combustion of propellants; calculations show that of available propellant combinations, best performance is obtained with liquid oxygen and kerosene type fuel; thrust chamber heat transfer and combustion inefficiency; injector design; combustion instability and starting and control problems.
Performance problems in large rocket engines
Roy Aeronautical Soc -- J
Royal Aeronautical Society -- Journal ; 64 , n 591 ; p 131-140
1960
10 pages
Article (Journal)
English
© Metadata Copyright Elsevier B. V. All rights reserved.
Rocket Engines and Ecological Problems
British Library Conference Proceedings | 1995
|Engineering Index Backfile | 1957
|Engineering Index Backfile | 1957
|Engineering Index Backfile | 1957
|NTIS | 1968
|