Results 201 to 210 of about 2,274 (257)

Liquid Propellant Positioning and Control in Example Propellant Tank

2021
Two topics relating to low gravity fluid behavior in satellite propellant tanks are considered. In the first, static case, the problem of liquid trapping is examined. Satellite propellant tank end caps optimized for weight are generally shallower and more oblate than hemispherical end caps of the same radius.
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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
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Liquid-Propellant Rocket Power Plants

Journal of Fluids Engineering, 1947
Abstract This paper discusses some of the general features of liquid-propellant rocket power plants, and the propellant systems which have been developed. The object of the discussion is to call attention to problems requiring solution in order to improve the reliability and performance of liquid-propellant rocket power plants.
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Liquid propellant combustion waves

27th Joint Propulsion Conference, 1991
Design of efficient and stable combustors depends on accurate analysis of flowfields. In the present study, we examine combustion waves aIlSIng from hydrogen-air reactions In the scramjet flame holders with various ramp angles. TWo-iltep Taylor-Galerkin finite element methods are used to solve the Navier-Stokes system of equations.
W. YOON, T. CHUNG
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INVESTIGATION OF LIQUID ROCKET PROPELLANTS

1952
Abstract : N sub2 H sub4 derivatives: The f.p. of N sub2 H sub3 Me (I) wa s calculated as -56.08 deg. C; the eutectic for the system I-N sub2 H sub4 occured at 85 wt.-% I and -64 deg. C. Neutralizing I.H sub2 SO sub4 with KOH yielded 95. 6% I. The formation of trimethylazonium bromide in the reaction of N sub2 H sub4 and MeBr was not prevented by using
E. M. Wilson, R. H. Sanborn, K. H. Mueller, L. K. Moss, J. F. Harkee, A. F. GRAEFE, C. B. EATON   +6 more
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FUNDAMENTALS OF LIQUID PROPELLANT SENSITIVITY

1966
Abstract : Two experimental techniques are being used to study the sensitivity of liquid propellant systems: (1) pure environmental shock testing and (2) flash photolysis. Progress on the shock tube phase has been hindered by the inability to obtain reproducible results with nitroglycerine as the test system.
Ted A. Erikson, Allen J. Tulis
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Impact Ignition of Liquid Propellants

1992
Abstract : The report describes a preliminary study of the impact ignition of liquid propellants. In one experimental set up, two dimensional cavities were shocked and the cavity collapse studied by both high-speed framing and streak photography. Cavities in water and liquid propellant (LCP 1846) were studied.
S. M. Walley, N. K. Bourne, J. E. Field
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Solubilities of gases in liquid propellants

Journal of Chemical Education, 1977
A curious phenomenon observed in pressurizing liquid dinitrogen tetroxide with gaseous oxygen.
N. A. Gokcen, E. T. Chang
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Liquid Hydrogen as a Rocket Propellant

1992
For the final velocity u of a rocket related to the launching system with a launch mass m 0, mass m at the final velocity u and exhaust velocity v relative to the vehicle the following applies $$\frac{{{m}_{0}}}{m}={{e}^{u/v}}$$ (118) .
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Oxygen, Liquid, Propellant Grade

2017
This specification has been declared "CANCELLED" by the Aerospace Materials Division, SAE as of January 1990.
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