Results 61 to 70 of about 9,371 (228)
Low loss injector for liquid propellant rocket engines [PDF]
, 1986 A low pressure loss injector element is disclosed for the main combustion chamber of a rocket engine which includes a lox post terminating in a cylindrical barrel. Received within the barrel is a lox plug which is threaded in the lox post and includes an
Vonpragenau, G. L.
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In Situ Methanation on Mars: A Process Concept Study on the Impact of H2/CO2 and Recycle Ratio
Chemie Ingenieur Technik, Volume 98, Issue 4, Page 156-164, April 2026.The rocket propellant methane can be produced on Mars by in situ resource utilization. The H2/CO2 ratio is decisive, and excess H2 is favored for providing sufficient propellant purity. The operation mode—with or without recycling of unreacted reactants—depends on the resource availability of the selected landing site. Abstract For return missions from
Franz Braun +4 more
wiley +1 more source
The hard start phenomena in hypergolic engines. Volume 1: Bibliography [PDF]
A bibliography of reports pertaining to the hard start phenomenon in attitude control rocket engines on Apollo spacecraft is presented. Some of the subjects discussed are; (1) combustion of hydrazine, (2) one dimensional theory of liquid fuel rocket ...
Miron, Y., Perlee, H. E.
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Computer simulation of high-frequency combustion instability and its supression [PDF]
, 1968 Program for simulation of gas motion illustrates the effects of some of the variables on the combustion chambers of liquid propellant rocket engines.
Bucher, R. E.
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Small Methods, Volume 10, Issue 8, 22 April 2026.This study introduces an in situ UV torsional force spectroscopy method to track how polymers harden under UV light. The technique maps stiffness and energy loss beneath the surface in real time. It reveals how cross‐linking develops and identifies regions with different mechanical behavior, helping optimize UV curing processes in polymer materials ...
Marvin Hoffer +6 more
wiley +1 more source
Open Physics, 2016 Hydrocarbon fuel has been widely used in air-breathing scramjets and liquid rocket engines as coolant and propellant. However, possible heat transfer deterioration and threats from local high heat flux area in scramjet make heat transfer enhancement ...
Jiang Yuguang +4 more
doaj +1 more source
Launch vehicle performance using metallized propellants [PDF]
Metallized propellant propulsion systems are considered as replacements for the solid rocket boosters and liquid sustainer stages on the current launch vehicles: both the Space Transportation System (STS) and the Titan 4.
Palaszewski, Bryan A., Powell, Richard
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, 1964 Space program - high thrust boosters with greater payload capabilities, superior guidance and control, and astronaut ...
Dean, J. +4 more
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Journal of Aerospace Technology and Management, 2011 The main objective of this work was to present the specifi cation of an experimental fi ring test stand for liquid rocket engines (LRE) and develop a program for control and acquisition of data.
Emerson Andrade Santos +3 more
doaj
Prospects for the mastery of space and the basic problems which must be solved in developing systems for both manned and cargo spacecraft are examined. The achievements and flaws of rocket boosters are discussed as well as the use of reusable spacecraft.
Chekalin, S. V., Grishin, S. D.
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