Liquid propellers

RocketPropella.nts, Liquid propellants have long been used to obtain maximum controUabiUty of rocket performance and, where required, maximum impulse. Three classes of rocket monopropellants exist that differ ia the chemical reactions that release energy (/) those consisting of, eg, hydrogen peroxide, ethylene oxide, C2H4O and nitroethane, CH2CH2NO2 that can undergo internal oxidation—reduction reactions (2) those... [Pg.40]

W. E. Morrison and co-workers, "The Interior BaUistics of Regenerative Liquid Propellant Guns," Proceedings of 8th International Symposium on Ballistics, Apr. 1983. [Pg.55]

Bader, B. E., A. B. Donaldson, and H. C. Hardee. 1971. Liquid-propellent rocket abort fire model. J. Spacecraft and Rockets 8 1216-1219. [Pg.243]

Bessey, R. L. 1974. Fragment velocities from exploding liquid propellant tanks. Shock Vibrat. Bull. 44. [Pg.243]

Robert H. Goddard standing to the left of the first flight of a liquid-propellant rocket, (Public Domain)... [Pg.1021]

A liquid propellant consists of two liquid chemicals, fuel and oxidizer, which arc delivered from separate tanks into the cninbtistinii chamher of a liquid propellant rocket engine (LPRE). [Pg.1021]

There arc two major types of liquid propellants a storable propellant (that does not boil under a normal temperature) and a ciyogenic propellant (a liquefied... [Pg.1070]

Space launchers usually consist of several stages, which are the individual rockets stacked together. This is another method to increase efficiency—the stages are ejected as soon as their propellant is spent, and a rocket docs not have to cari y empty tanks. The number of stages also depends on engines effectiveness. Liquid-propellant rockets usually consist of two to three stages, while solid ones have to have three to five stages. [Pg.1072]

Gelling agent Poly(vinyl chloride) Thixotrophic liquid propellant... [Pg.119]

The combustion process is carried out in a thrust chamber or a motor case, and the reaction products are momentarily contained therein. The newly formed species are heterogeneous in composition and involve a wide variety of low molecular weight products. The temperature of these products is generally high, and it ranges from about 2,000°F (1,100°C) in gas generators to well over 8,000°F in advanced liquid propellant engines. The combustion products leave the chamber and are directed and expanded in a nozzle to obtain velocities from about 5,000 to 14,000 ft/sec. [Pg.122]

A form of cooling, and the one of prime interest, concerns ablative cooling. It is essentially a heat and mass transfer process in which mass is expended to achieve thermal dissipation, absorption, and blocking. The process is passive in nature, serves to control the surface temperature, and greatly restricts the flow of heat into the material substrate. As a result of these desirable attributes, ablative cooling (includes use of plastic compositions) has been widely used for thermal protection of solid propellant motors and less extensively in liquid propellant motors. [Pg.123]

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... [Pg.280]

Blast Hazards of the Liquid Propellants LCO and LN20 , URS-7309-12, Contract No F04611-73-00053, AFRPL (1974) 17) ChemRub-... [Pg.312]

For additional information on Nitrogen tetroxide, see under Liquid Propellants in Vol... [Pg.315]

Jensen, Chemical Rocket Propellant Hazards. Volume III. Liquid Propellant Handling, Storage and Transportation , CPIA-Pub-194, Contract No NOW-62-0604 (1970) 29) J.A. Letos,... [Pg.315]

Liquid Propellants can be packaged in 12 gallon polyethylene drums inside of strong, tight metal drums (Refs 33 and 34)... [Pg.479]

Compatibility of Plastics with Liquid Propellants, Fueis and Oxidizers", PLASTEC Rept 25 (1966) 11) N.T. Baldanza, Fiber Rein-... [Pg.788]

Iridium Coating for Spacecraft Rocket Nozzles. The coating of rocket nozzles with iridium is a good example of the ability of CVD to provide a complete composite material, in this case a structural refractory shell substrate coated with a corrosion- and oxidation-resistant component. The device is a thruster rocket nozzle for a satellite. The rocket uses a liquid propellant which is a mixture of nitrogen tetroxide and monomethyl hydrazine. [Pg.445]

L. Crocco and S. Cheng. Theory of Combustion Instability in Liquid Propellant Rocket Motors. Butterworths, London, 1956. [Pg.79]

D.T. Harrje and F.H. Reardon. Liquid propellant rocket combustion instability. Technical Report SP-194, NASA, Washington, DC, 1972. [Pg.79]

L. Crocco. Aspects of combustion instability in liquid propellant rocket motors, part 1. /. Am. Rocket Soc., 21 163-178, 1951. [Pg.92]

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. [Pg.92]

Nike-Ajax Tandem separating boost. Internal liquid-propellant rocket sustainer. [Pg.192]

The Handling and Storage of Liquid Propellants. Office of the Director of Defense Research and Engineering, Washington D.C., 1963... [Pg.399]

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