Liquid rocket motors

In addition to the numerous electronic and optoelectronic applications mentioned above, novel applications of CVD are also being used to generate macroscopic components (10 cm as opposed to 1 nm). One interesting example is the production of Ir/Re thrust chambers for liquid rocket motors (see Figure 6). For this structure... 

At one time this latter reaction was used in experimental rocket motors, the CIF3 oxidizer reacting spontaneously with the fuel (N2H4 or Me2N2H2). At low temperatures NH4F and NH4HF2 react with liquid CIF3 when allowed to warm from — 196 to —5° but the reaction is hazardous and may explode above —5° ... 

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... 

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. 

The use of liquid oxygen difluoride (40 or 90%) to stabilise liquid ozone as oxidant for gaseous hydrogen in a rocket motor was not entirely successful, explosions occurring at both concentrations. 

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 ... 

Yu.Kh. Shaulov M.O. Lerner, Goreniye v Zhidkostnykh Raketnykh Dvigateliakh (Combustion in Liquid Rocket Fuel Motors), GoslzdatOboronProm, Moscow (1961)... 

Beginning before and during WWII many liquid fuels started to be used for propulsion of jet and rocket motors and for spacecraft... 

Rocket motors with hypergolic liquids with or without an expelling charge 0322... 

O) R.C, Kopituk, A New Impact Detonability Tester for Evaluating Materials with Highly Reactive Oxidizers , Reaction Motor Div, Thiokol Chem Corp, Denville, NJ. Paper 1707-61 presented at the American Rocket Society Conference on Propellants, Combustion and Liquid Rockets, Palm Beach, Fla (26-28 April 196l)... 

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

Zucrow and Sellars (Z6), 1961 Experimental study of film cooling of rocket motors. Liquids of various 2Vpr used, with and without chemical reaction. 

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