Rockets liquid

R. E. Anderson, E. M. Vander Wall, and R. K. Schaplowsky, "Nitrogen Triduoride," USjW Propellant Handbook AE RPT-T -ll-11 Contract E04611-76-C-0058, Aerojet Liquid Rocket Co., Sacramento, Calif., 1977. 

Materials Compatibility With Liquid Rocket Propellants , Rept No DZ-113073-1, Boeing Co, Seattle, Wash, ASD (1970) 30) N.C. Paul,... 

Altitude Testing of the Aerojet AJ-10-179 liquid Rocket Engine , AFRPL-TR-72-128... 

V. Yang and A. Anderson. Liquid rocket engine combustion instability, volume 169 of Progress in Astronautics and Aeronautics. AIAA, Washington DC, 1995. 

F.E.C. Culick and V. Yang. Overview of combustion instabilities in liquid-propellant rocket engines. Liquid Rocket Engine Combustion Instability. Progress in Astronautics and Aeronautics, Vol. 169, pp. 3-37, Chapter 1, AIAA, 1995. 

Catalyst in alkylation and polymerization reactions Additives to liquid rocket fuels Uranium refining Cyclosarin (GF) 9.01... 

Liquid resoles, chemical shifts of methylene carbons in, 18 775t Liquid rocket propellants, 10 726-727 Liquid rubber technology, 9 563-566 Liquid runaround systems, 10 144 Liquids. See also Nonideal liquid mixtures boiling points of, 24 2841 bulk handling of, 18 5 combustion of, 13 174 degree of fire hazardousness of, 24 284 density of, 24 282... 

Ammonium thiocyanate is used as an ingredient in antibiotic preparations, pesticides, liquid rocket fuels, adhesives, and matches. It is also used in photographic processes, to improve the strength of silks, and as a weed killer. 

It is the oxidizer for liquid rocket fuels, and as a gas, oxygen is used in a mixture with helium to support the breathing of astronauts and divers and to aid patients who have dif-flculty breathing. It is use to treat (oxidize) sewage and industrial organic wastes. 

Petersen P, Bredahl E, Lauritsen O, Laursen T Examination of the liver in personnel working with liquid rocket propellant. Br J /wdMrd 27 141-146, 1970... 

Volume 2. L. E. Bollinger et al, eds, "Liquid Rockets and Propellants" (I960) Volume 3. N.W. Snyder, ed, "Energy Conversion for Space Power" (1961) Volume 4. N.W. Snyder, ed, "Space Power Systems (1961)... 

D.W. Rice, CombstnFlame 8(1), 21-8 (1964) CA 60, 14325 (1964) (Effect of compositional variables upon oscillatory combustion of solid rocket propellants) N ) R.W. Hart F.T. McClure, "Theory of Acoustic Instability in Solid Propellant Rocket Combustion , lOthSympCombstn (1965), pp 1047-65 N2) E.W. Price, "Experimental Solid Rocket Combustion Instability , Ibid, pp 1067-82 Qi) R.S. Levine, "Experimental Status of High Frequency Liquid Rocket Combustion Instability , Ibid, pp 1083-99 O2) L. Crocco,... 

Detonation and Two-Phase Flow is discussed at ARS Propellants, Combustion and Liquid Rocket Conference in 1961. Published by Academic Press, NY (1962)... 

Note 1 Salbei was a code name for either 99.5% nitric acid or its mixt with 5-10% coned sulfuric acid, added to suppress corrosion (Ref 1, pp 216 231 Ref 2, p Ger 170-R) Note 2 Tonka was a liquid rocket fuel, such as a mixt of crude m-xylidine 57 and Triethyl-amine 43%(Ref 1, p 216 Ref 2, p Ger 199-R) Refs 1) TM 9-1985-2 (1953) 2) PATR 2510... 

Both gas and liquid are very sol in water. Can be prepd by distUlation from the product of reaction of Ca fluoride (fluorspar) and sulfuric acid. Used as fluorinating agent in organic and inorganic reactions production of fluorine and A1 fluoride prepn of hydrofluoric acid production of fluoroborates, fluorosilicates, etc as an additive in liquid rocket propellants and for refining of uranium (Ref 3, p 588-R)... 

Borani — Propellenti liquidi per razzi (Liquid Rocket Propellants) consist of liquid hydrogen with boron or other light element, such as beryllium (Ref 31, p 129)... 

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

Zhidokosnye Raketnye Dvigateli (Liquid Rocket Propellants), Mashinostroenie, Moscow (1968) CA 71, 126715 (1969) 28) J.N. 

Uses Medecine, organic synthesis, commercial expls and liquid rocket propints (Refs 2, 2a, 5a, 7 8)... 

Use of alcohol as an ingredient of liquid rocket fuels also was described by Krop (Ref 6) and by Warren (Ref 10)... 

It was used (accdg to Dr H. waiter) during WWII as one of the ingredients of German liquid rocket fuels... 

In organizing the symposium, we made the usual division into solid and liquid rocket propellants. Most readers no doubt already know the relative merits of solid vs. liquid systems—viz., the instant readiness of solids (compared with cryogenic liquids), their higher density (important in volume-limited systems), and the relative simplicity of rocket construction liquids offer easy variation in thrust level and the attainment of higher specific impulses, the latter because physical separation permits the use of fuels and oxidizers that would be incompatible if premixed. 

Injector design determines the physicochemical processes occurring in liquid propellant rocket engines. A complete quantitative description of the processes in liquid rockets is impossible because of our limited understanding of chemical reaction mechanisms and rates. The use of similarity principles simplifies the solution of theoretical combustion problems and is described for channel flow with chemical reactions and for diffusion flames over liquid droplets involving two coupled reaction steps. We find the new result that the observed burning rate of a liquid droplet is substantially independent of the relative rates of the coupled reactions. 

In summary, all features of the liquid rocket engine combustion processes are extensively affected by injector design, and any simplified combustion model, in which the essential three-dimensional nature of the flow processes is ignored, can only be of qualitative significance. Nevertheless, these simplified models are useful in giving us some insight into the nature of the physicochemical phenomena that determine engine performance. In this connection, steady-state combustion rates and overall combustion efficiencies in propellant utilization are far less important practical problems than are control or elimination of instabilities, excessive heat transfer, and hard starts. 

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