Results 161 to 170 of about 15,244 (236)

Modeling energy requirements for oxygen production on the Moon. [PDF]

Proc Natl Acad Sci U S A
Leger D, Ghaffari-Tabrizi F, Shaw M, Rasera J, Dickson D, Valentin B, Morlock A, Thoresen F, Cowley A.   +8 more
europepmc   +1 more source

3 months transit time to Mars for human missions using SpaceX Starship. [PDF]

Sci Rep
Kingdon J.
europepmc   +1 more source

Comprehensive Analysis of Unsymmetrical Dimethylhydrazine: Adsorption Behavior, Environmental Fate, and Toxicity Across Contrasting Soil Matrices. [PDF]

Toxics
Du J, Ren X, Zeng Y, Zhang L, Shi J, Yang S.   +5 more
europepmc   +1 more source

Research on curing reaction kinetics and curing process of hydroxy-terminated polybutadiene (HTPB) propellants. [PDF]

Sci Rep
Guo Z, Wang Y, Chiumsenti M, Wu Y, Zhen S, Liu H, Rossi R, Fu X.   +7 more
europepmc   +1 more source

Polymethylhydrosiloxane-Coated Ammonium Dinitramide: A Simple Strategy to Moisture-Resistant and Insensitive Energetic Microspheres. [PDF]

ACS Omega
Bui AT, Pham QH, Pham VT, Vu MT, Cao HT.
europepmc   +1 more source

Fault Detection and Isolation Based on Structural Analysis: Application to a Multi-Engine Propulsion Cluster. [PDF]

Sensors (Basel)
Murata R, Marzat J, Piet-Lahanier H, Boujnah S, Belleoud P.   +4 more
europepmc   +1 more source

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Liquid Propellant Rocket Motors

The Journal of the Royal Aeronautical Society, 1953
It has been said that a rocket motor is the simplest “ prime mover.” This is correct in theory, since fundamentally a rocket consists of a chamber containing a gas under pressure, having a nozzle at one end through which the gas expands, forming a propulsive jet. Since the pressure ratio of the rocket is always greater than the critical pressure ratio,
B. R. Diplock, D. L. Lofts, R. A. Grimston   +2 more
openaire   +1 more source

Electric Feed Systems for Liquid-Propellant Rockets

Journal of Propulsion and Power, 2013
Liquid-propellant rocket feed systems based on electric pumps are compared with the more classical pressure–gas and turbopump systems. The design parameters entering in the definition of the system mass are highlighted, and a careful choice of the figures of merit is performed, in particular for the electric motors and batteries.
P. A. Pavlov Rachov, H. Tacca, LENTINI, Diego   +2 more
openaire   +2 more sources

Liquid-propellant rocket abort fire model.

Journal of Spacecraft and Rockets, 1971
During a rocket launch pad abort, a hazardous payload material can be subjected to a severe thermal environment from the resulting fireball. A model has been developed which specifies heat flux from the fireball as a function of time for any initial propellant quantity.
B. E. BADER, A. B. DONALDSON, H. C. HARDEE   +2 more
openaire   +1 more source