Rocket motors liquid-propellant

In a solid-propellant rocket motor, the propellant is contained within the wall of the combustion chamber, as shown in Fig. 1. This contrasts with liquid systems, where both the fuel and oxidizing components are stored in tanks external to the combustion chamber and are pumped or pressure-fed to the combustor. In hybrid systems, one component, usually the fuel, is contained in the combustion chamber, while the other component is fed to the chamber from a separate storage tank, as in liquid systems. The solid-propellant motor also has an ignition system located at one end to initiate operation of the rocket. The supersonic nozzle affects the conversion of... 

In this paper, an overview of the important phenomena is given. The supercritical combustion process employed is also known to occur in liquid propellant rocket motors (e.g. in LOX/GH2-motors), liquid propellant guns (LPG), advanced aviation gas turbines and, to a lesser extent, in internal combustion engines. Supercritical combustion is characterized by (1) injection of at least one liquid state fuel component into a chamber which is thermodynamically in the supercritical state, (2) density ratios of fuel to oxidizer near one, (3) supercritical phase transitions of fluid-particles due to combustion, (4) non-ideal properties of the fluids. Additionally a short description of pertinent design criteria is given. 

Hybrid rocket motors use propellants in two different states of matter, usually a solid fuel and a liquid or gaseous oxidizer. Like liquid rockets and unlike solid rockets a hybrid engine can be turned off easily but due to the fact that fuel and oxidizer (different states of matter) would not mix in the case of an accident, hybrid rockets fail more benignly than liquid or solid motors. 

Rocket Motors Articles consisting of a solid, liquid or hypergolic fuel contained in a cylinder fitted with one or more nozzles. They are designed to propel a rocket or a guided missile. The term includes Rocket Motors Rocket Motors With Hypergolic Liquids with or without expelling charge Rocket Motors, Liquid Fuelled. UN App. B, ICAO A2, lATA App. A... 

Other Uses of Nitric Acid. As mentioned earlier, fuming nitric acid (FNA) when mixed with ale, toluene or acet anhydr will cause an expln. However, there are many other uses for FNA in energetic materials technology. As either red fuming nitric acid (RFNA) or as nitrogen tetrox-ide, it is used extensively as the oxidizer in pro-pint systemsnfor ram-jets, jet motors, space rockets and other missiles (Refs 37, 38 39). See also under Liquid Propellants in Vol 7, L24-Rff... 

L. Crocco and S. Cheng. Theory of Combustion Instability in Liquid Propellant Rocket Motors. Butterworths, London, 1956. 

L. Crocco. Aspects of combustion instability in liquid propellant rocket motors, part 1. /. Am. Rocket Soc., 21 163-178, 1951. 

Ducted rockets are intermediate between solid rockets and liquid ramjets in their propulsion characteristics. The propulsive force of soHd rockets is generated by the combustion of propellants composed of oxidizer and fuel components. Thus, no additional fuels or oxidizers need to be introduced from the atmosphere into the rocket motor. The momentum change of the exhaust gas from the nozzle attached to the aft-end of the combustion chamber is converted into the thrust for propulsion. On the other hand, the propulsive force of Hquid ramjets is generated by the combustion of a liquid hydrocarbon fuel with air introduced from the atmo-sphere.Ii] jjjg incoming air is compressed by a shock wave formed at the air-intake attached to the front end of the combustor. The air taken in from the atmosphere serves only as the oxidizer for the ramjets. The thrust is created by the momentum difference between the exhaust gas from the combustor and the air taken in from the atmosphere. 

Investigation of Transverse Mode Combustion in Liquid Propellant Rocket Motors (PhD Thesis), Princeton Univ, June 1, 1961 E) L.A. Dickinson, "Command Initiation of Finite Wave Axial Combustion Instability in Solid Propellant Rocket Motors , ARS 32, 643(1962) F) S.Z. Burstein V.D. Agosta, "Combustion Instability Non-Linear Analysis of Wave Propagation in a Liquid Propellant Rocket Motor , Polytechnic Institute of Brooklyn, Dept of Mechanical Engineering,... 

Sirignano L. Crocco, "A Shock Wave Model of Unstable Rocket Combustors , AIAA 2, 1285(1964) I) B.T. Zinn, "A Theoretical Study of Nonlinear Transverse Combustion Instability in Liquid Propellant Rocket Motors (PhD Thesis)> Princeton Univ, May 1966 J) C.E. Mitchell, "Axial Mode Shock Wave Combustion Instability in Liquid Propellant Rocket Engines (PhD Thesis), Princeton Univ, NASA CR 72229(1967) K) E.L. 

Western States Sect Combust Inst, Paper, WSCI 65-23 (1965) 27) G.R. Mistier T.F. Seamans, Vacuum ignition characteristics of flox/diborane and oxygen difluoride/diborane, NASA Contract Report 1969, NASA-CR-100678. Avail CFSTI. From SciTechAerosp Rep 7 (12), 2196 (1969) 28) W.B. Powell et al, ClFj-Njli, liquid propellant evaluation and rocket motor development, TechRept 32-305, Jet Propulsion Lab, Calif Inst Tech, Pasadena, Ca, (May 1963) (NASA N63-21722) 29) H. Allen, Jr Pinna, Relative ignitability of typical solid propellants with C1F3, NASA TN-D-1533, NASA, Wash, DC, (Jan 1963) (NASA N63-11616) 30) R.F. Sawyer et al, AIAA J, 6, 11, 2111 (1968) CA 70, 13118 (1969) 31) M.C. Branch ... 

G.B.Siniarev M,B. Dobrovol skii "Liquid Propellant Rocket Motors, Oborongiz, Moscow(1957)... 

Barrel, Rocket-A vernacular term for the major component of a liquid-propellant rocket motor wherein combustion takes place the term thrust-chamber assembly is preferred Ref Rocket Encycl(1959),40... 

Crocco S.I.Cheng, "Theory of Combustion Instability in Liquid Propellant Rocket Motors , Butterworths, London(1956) 23)D.Altroan S.S. Penner, "Combustion of Liquid Propellants , in Vol 2 of B.Lewis et al, "High-Speed Aerodynamics and Jet Propulsion Combustion Processes ,... 

Refs l)Kirk St Othmer 11(1953), 764(Com-bustion products of rocket propints) 767 (Combustion chambers in rocket motors) 2)C.GRoss8c P.P.Datner, "Combustion Instability in Liquid-Propellant Rocket Motors , pp 352-402 in "Selected Combustion Problems , Combustion Colloquium, Cambridge Univ, England in 1953 published for AGARD,... 

New prepolymers based on 3,3-bis (azidomethyl) oxetane (BAMO) and 3-nitratomethyl- 3-methy-loxetane (NMMO) are used in advanced pintle-controllable solid rocket motor applications. These polymers yield favorable propellant energy with the combination of nitrato esters and ammonium nitrate, and allow solid propellant designs to compete with liquid propellants in arenas of energy management, approaching true start-stop-restart operation. 

Energetic materials which support rocket propulsion via chemical and thermodynamic changes in engines, as opposed to rocket motors, distinguish the liquid propellant mission versus applications of solid propellants. Liquid propellants encompass liquid-phase... 

The specific impulse of a propellant or a pair of reacting liquids in rocket motors is the most important characteristic of the performance. It is the - Thrustxtme (i.e., the impulse) per unit weight of propellant ... 

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