Rocket propellants basics

Hs 298 (Henschel 298) was a rocket-propelled, radio-controlled missile designed primarily as an air-to-air weapon to be carried on fighter aircraft as well as the bomber types. There were several versions but the basic type was called Hs 298 V-2. It used a solid propellant (Ref 1, pp 203-05 Ref 2, p Ger 91-L)... 

H.A. Aaronson, "Basic Research.on Rocket Propellants High Polymer Systems. 

The propellant is the most vital sub-system of a gun and rocket or missile system and accordingly, the performance of a gun, rocket or missile mainly depends on the propellant used. Some basic performance parameters are used to define the characteristics of these propellants and they are different for gun and rocket propellants. 

Oxides of lead, basic lead stearate, lead-2-ethyl hexoate, basic lead salicylate Render the bum rate of DB rocket propellants independent of pressure over a certain pressure range [236]. Such salts are effective only with cooler propellants i.e., cal. val. below -850calgT... 

In Example 2.12, the method of random balance, factors have been selected by the effects of their significance on dynamic viscosity of uncured composite rocket propellant. The screened-out factors are X3 mixing speed X5 time after addition of AP and Xg vacuum in vertical planetary mixer. Since insufficient vacuum in a mixer causes bubbles to appear in the cured propellant, the value of this factor is fixed at the most convenient one. For the other two factors a design of basic experiment has been done according to a FUFE matrix, as shown in Table 2.103, and aimed at obtaining the mathematical model of viscosity change. 

Castorioa, Ibid, "Explosive Plasticizers for Nitrocellulose", PATR 1755 (Dec 1949) 13) H.A. Aaronson, "Basic Research.on Rocket Propellants High Polymer Systems. The Kinetics of Solution of Cellulose Nitrates in Explosive Plasticizers", PATR 1786 (Oct 1950)... 

Use Blast furnaces copper smelting steel production (basic oxygen converter process) manufacture of synthesis gas for production of ammonia, methyl alcohol, acetylene, etc. oxidizer for liquid rocket propellants resuscitation, heart stimulant decompression chambers spacecraft chemical intermediate to replace air in oxidation of municipal and industrial organic wastes to counteract effect of eutrophication in lakes and reservoirs coal gasification. 

Altman and Fabbbb, Basic Research on Rocket Propellants, Armed Servicee Tech-nicdl Ir onmtion Agency Progreea Kept. 9-26. 

More detailed basic information can be obtained from the ample literature on rocketry and rocket propellants, examples of which are the books by Sutton, Wimpress, and Warren, while the Rocket Propellant Handbook by Kit and Evered is merely a convenient re-fer Ke for properties of some ingredients. 

The prediction of burning-rate characteristics, on the other hand, has not been possible. This has caused rocket designers to adopt a trial-and-error approach to the development of specific propellants to meet specific mission requirements. In an effort to reduce the large development effort required for each new propulsion system, considerable basic research effort has been directed toward the definition and quantitative characterization of propellant combustion mechanisms. The ultimate objective of this effort is to provide methods for predicting the burning-rate characteristics of particular propellant formulations. 

FI ox. Fluorine/Oxygen Mixture for Atlas Rockets. A research program of the Lewis Research Center of NASA using this new propellant indicates that the pay load capacity is increased by 90% for 160km high orbits and by 65% for tasks with escape velocity. About 30% fluorine 70% oxygen is taken as a basic mixt... 

The temperature and composition of propellant combustion products are of interest to those concerned with materials of construction and insulation for the combustion chamber and nozzle of the rocket motor. These values are readily computed from basic thermodynamic data for the specific propellant composition and operating pressure of interest with the aid of today s large-scale digital computers. By way of illustration, however, the products of combustion computed this way for the three typical plastisol propellants given in Table I are shown in Table III for a combustion pressure of 1000 p.s.i.a. Approximate propellant composition is also shown for convenient reference. 

Summary) 2)Aerojet Rept 410(1949), "Basic Development of the Aeroplex Propellants and Associated Rocket Design and Production" (Volumes 1,2 and 3) 3) Warren( 1958), 11. ... 

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