Steady-state combustion of solid double-base and monopropellant rockets is investigated analytically; nonlinear differential equations describing motion of laminar two-dimensional, compressible, chemically reacting viscous fluid are intimately coupled with one-dimensional heat conduction equation of burning solid propellant, and one-dimensional, compressible, inviscid flow of combustion products through central core of propellant grain; applying numerical methods and using realistic rocket conditions as input yielded result that calculated propellant burning rates and wall temperatures fall within range of previously obtained experimental values.
Aerothermochemical analysis of solid propellant combustion
AIAA J
AIAA Journal ; 4 , n 12
1966
7 pages
Article (Journal)
English
© Metadata Copyright Elsevier B. V. All rights reserved.
Fundamentals of solid propellant combustion
TIBKAT | 1984
|Control of solid propellant combustion
Engineering Index Backfile | 1966
|