Results 111 to 120 of about 15,244 (236)

An experimental correlation of the nonreactive properties of injection schemes and combustion effects in a liquid-propellant rocket engine. Part II. Instrumentation, experimental apparatus, and experimental techniques [PDF]

open access: yes
Apparatus, techniques, and instrumentation for experimental correlation of nonreactive injection schemes and combustion effects in liquid propellant rocket ...
Clayton, R. M.   +2 more
core   +1 more source

Nonlinear combustion instability in liquid-propellant rocket motors Quarterly report [PDF]

open access: yes
Fluid dynamic pancake model and droplet evaporation and combustion analysis related to nonlinear combustion instability in liquid propellant rocket ...
Burstein, S. Z., Chinitz, W.
core   +1 more source

Refractory thrust chambers for spacecraft engines Final report [PDF]

open access: yes
Structural reliability tests on pyrolytic graphite and pyrolytic graphite alloys for use in liquid propellant rocket engine thrust chambers and ...
Campbell, J. G., Coulbert, C. D.
core   +1 more source

Recoverable single stage spacecraft booster Patent [PDF]

open access: yes, 1967
Recoverable, reusable single stage booster capable of injecting large payloads into circular earth ...
Bono, P.
core   +1 more source

A Reliable Method for Predicting the Specific Impulse of Chemical Propellants

open access: yesJournal of Aerospace Technology and Management, 2018
The specific impulse (Isp) is an important performance parameter that describes energy efficiency of propellant combustion and is intimately related to the rocket engine thrust.
Dany Frem
doaj  

Investigation of resin systems for improved ablative materials [PDF]

open access: yes
Resin systems for matrix material in ablative composite for liquid rocket combustion chambers using fluorine-containing ...
Burns, E. A.   +2 more
core   +1 more source

Nano-Iron as a Catalyst in Isocyanate-Free Rocket Propellants. [PDF]

open access: yesPolymers (Basel)
Chmielarek M   +2 more
europepmc   +1 more source

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