Propelling system

There are other alternatives to the peristaltic pump for establishing the flow in continuous analysers, a detailed description of which is given in the authors book on FIA [2]. 

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D. R. Cmise, Theoretical Computation of Equilibrium Composition, Thermal Dynamic Properties, and Peformance Characteristics of Propellants Systems, NWC... 

The reaction with fluorine occurs spontaneously and explosively, even in the dark at low temperatures. This hydrogen—fluorine reaction is of interest in rocket propellant systems (99—102) (see Explosives and propellants, propellants). The reactions with chlorine and bromine are radical-chain reactions initiated by heat or radiation (103—105). The hydrogen-iodine reaction can be carried out thermally or catalyticaHy (106). 

Group 15 (VA) Perchlorates. Nitrogen perchlorates have been used as oxidizers in rocket propellants. Hydrazine perchlorate [13762-80-6] NH2NH2CIO4, and hydrazine diperchlorate, CIO4NH2NH2CIO4, have been investigated as oxidizers for propellant systems (60). Anhydrous salts can be... 

Nitrogen Oxides as Rocket Fuel Oxidants Including The Theoretical Performances of Propellant Systems Employing Nitrogen Tetroxide , JPL PR No 9-23, Cal Inst Tech, Proj No TU2-1,... 

Other refs which, although unclassified, are of limited distribution 1) Anon, Research on Ultra-High Impulse Propellant Systems , Imperial Chem Ind Ltd, Stevenson (Scotland), Contract N625584076, Prog Rept No 16, 1 Apr-30 June 64 (1964) 2) Ibid, Annual Prog... 

Parametric studies showed that mass diffusion in the gas phase could be neglected under most conditions. The calculations also show that the selection of the hypergolic combination (i.e., the gaseous oxidizer and the propellant system) fixes all of the parameters except the initial temperature and the oxidizer concentration. A general solution of the model shows that the ignition-delay time is approximately rated to the gaseous oxidizer concentration by the relation... 

Iron compounds are common catalysts for ammonium perchlorate propellant systems, and burning-rate augmentation is a strong function of catalyst surface area and shape. 

Most theoretical studies have concentrated on the analysis of the combustion zone of nonaluminized propellant systems. In actual practice, propellants containing aluminum are used in many applications. One study in which aluminum has been included has recently been published by Dunlop and Crowe (D2). In this study, the combustion zone is idealized to consist of four regions, as shown in Fig. 21. The results of these simplified one-dimensional analyses suggest that the combustion of aluminum particles in the gas... 

A cosolvent, typically ethanol, may be used to bring drug into solution. A small number of surfactants (sorbitan trioleate, oleic acid, and lecithin) may be dispersed in propellant systems and can aid in suspension stability and in valve lubrication. 

Rastogi, R. P. et al., Indian J. Chem., Sect. A, 1980, 19 A, 317-321 Reaction in this hybrid rocket propellant system is enhanced by presence of ammonium vanadate. 

Lester, D. H., Rept. NASA-CR-148711, Richmond (Va), USNTIS, 1976 Mixtures with liquid carbon monoxide, cyanogen (solidified), and methane are highly explosive [1]. Autoignition in liquid oxygen-hydrogen propellant systems has been reviewed [2],... 

Used industrially as a fluorinating agent and as an oxidizer in rocket propellant systems. This material is on the ITF-25 low threat list. 

This group of highly reactive compounds includes several which have found extensive use in preparative chemistry [1], Properties and reactions of several covalent tetrahydroborates have been reviewed [2], Preparation and properties of several new hydrides are given which are of interest as high-energy fuels in propellant systems [3,4], Individually indexed compounds are ... 

It is rather interesting that the maximum specific impulse of a rocket propellant system occurs when (T2iMW2)1/2 is maximized, even though the rocket combustion process is not one of detonation [17],... 

Fig. 2.21 (a) Scheme of a basic FIA system. C carrier (with or without a dissolved reagent) PS propelling system IV injection valve R reactor D detector W waste, (b) Slow recording—the commonest in this technique—corresponding to injection of triplicate standards and quintuplicate samples, (c) Fast recording, with its characteristic parameters. 

Sawyer, R. F., The Homogeneous Gas-Phase Kinetics of Reactions in Hydrazine-Nitrogen Tetraoxide Propellant System, Ph.D. Thesis, Princeton University, 1965. 

Uses. Oxidizer in rocket propellant systems fluorinating agent... 

Uses. Oxidant in missile propellant systems Exposure. Inhalation... 

The specific impulse, under fixed pressure conditions, is invariant for any propellant system and is the basic chemical comparison parameter used in evaluation. 

J. Bedel, Considerations on rocket propulsion for an aerospace vehicle, Paper presented at Eurospace Conf, Brussels, Jan 23-24, 1964 (NASA N 65-24027) 11) G. Hennings G. Morrell, Preliminary investigation of a chemical starting technique for acid-gasoline rocket propellant system, Res Memo E52K21, Natl Advisory Committee for Aeronautics, Wash, DC (Jan 1953) 12) B. Lewis, USP 3177652 (1965)... 

P.I. Gold, Chemical species and chemical reactions of importance in nonequilibrium propellant performance calculations, NASA Accession No N66-33714, Rept No NASA-CR-65442, avail CFSTI, SciTechAerosp Rept 4 (19), 3722 (1966) CA 67, 4484 (1967) 47) S.S. Cherry L.J. van Nice, Pyrodynamics 6 (3-4), 275 (1969) CA 70, 98394 (1969) 48) R.E. Lo, Theoretical performance of the multicomponent rocket propellant system (oxygen, fluorine/ beryllium, lithium hydride)/hydrogen, Deutsche Versuchsanst Luft- und Raumfehri Rept11968, DLR-Mitt-68-21 (Ger), avail CFSTI, SciTech Aerosp Rept 7 (1), 161 (1969) CA 71,... 

For many purposes, rather than using the total impulse I, it is more convenient to use an impulse per unit area per unit explosive weight, ie Ii = I/ca, or I = pGI/ca = p0I., (where pG is the density of the unexploded HE) which we shall call the impulse constant. The term I, has the dimensions of velocity and is closely related to specific impulse which is commonly used as a measure of effectiveness of propellant systems. 

Zirkind reviews investigations of radiation emission of rocket exhausts since 1940 (Ref 11). Emission characteristics of the exhaust plume are strongly dependent on rocket engine parameters the propellant system. If these motor operating conditions are stipulated, machine computations can give exhaust composition sometimes temperatures... 

Propellant System, Engine System, Common Designation Thrust Level, lbs. Application Area... 

In the manufacture of PVC plastisol propellants, the usual care is taken to assure that all ingredients meet specifications for chemical composition, dryness, and particle size. Since PVC plastisol propellants do not involve chemical reaction in their curing process, however, the presence of certain impurities in the ingredients is far less critical than with those propellant systems that are solidified by polymerization reaction. Ammonium perchlorate, the most common oxidizer, can normally be procured from the supplier with the required low moisture content. If not, it is dried immediately before use. Tray dryers or other drying means may be used, depending upon the quantity of material. Normally, some or all of the oxidizer must be ground to achieve the desired mean particle size and particle-size distribuion. High speed hammer mills have proved... 

The reaction of epoxides with carboxylic acids in the presence of ammonium perchlorate can be very slow. The search for a catalyst to accelerate the cure rate for a particular formulation can be particularly rewarding. The slowness of the reaction can lead to a disadvantage of the system if not carefully investigated. If cure is stopped before all of the epoxide groups have been consumed, cure will continue at a rate which depends on storage temperature. The epoxide can continue to react with carboxyl groups rapidly at elevated temperatures, or very, very slowly at ambient temperature, to yield highly crosslinked propellant systems with low strain capability. 

Compatibility. Owing to the high reactivity of the isocyanate group, polyurethane propellants require a more sophisticated processing technique than the rather foolproof, carboxy-terminated polybutadiene aziri-dine and/or epoxy-cured propellant systems. Processing is even more complicated if bonding agents (see below) are present, which are used to bolster mechanical properties in practically any modern propellant. 

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