Propulsion rocket engines

Grishin, S.D., Leskov, L.V, Kozlov, N.P. (1975), Electric-Propulsion Rocket Engines, Machinery (Mashinostroe-nie), Moscow. 

Rocket propellant is a mixture of combustible substances that is burned inside the combustion chamber of a rocket engine. Burning is the chemical process of decomposition and oxidation of the propellant. The resulting highly heated and compressed gas (propulsive mass) is ejected from a combustion chamber and facilitates propulsion—movement of the aggregate attached to the rocket engine. In physi-... 

Propulsion generates kinetic energy to facilitate motion of spacecraft. Although propulsion is provided by various types of devices, the most common propulsion system of modern space technology is a rocket engine, a device that propels a rocket by a force... 

Another attractive idea is to use electric power for propulsion. Having many design variations, the electric rocket engines (ERE) could roughly be divided into three groups ... 

The first experiments with the thermal electric engine were conducted in Russia in 1929 by its inventor, Valentin P. Glushko, who later became a world-famous authority in rocket propulsion. For more than forty years, the United States and Russia have devoted many resources to research and development of various kinds of EREs. First tested in space by the Russians in 1964, these engines have found some limited applications in modern space technology. For more than two decades Russian weather and communication satellites have regularly used electric rocket engines for orbital stabilization. The first spacecraft to employ ERE for main propulsion was the American asteroid exploration probe Deep Space 1, launched in 1998. The performance of... 

Summerfield, M., The Liquid Propellant Rocket Engine, )et Propulsion Engines, Princeton University Press, New )ersey (1959), pp. 439-520. 

Rocket Engine. A non-airbreathing reaction propulsion device that consists essentially of an injector, thrust chambers) and exhaust nozzle(s), and utilizes liquid fuels and oxidizers at controlled rates from which hot gases are generated by combustion and expanded thru a nozzle(s) (Ref 40a, p 125)... 

It is usually understood that a rocket motor is that part of the propulsion system in which the propellants are transformed into the exhaust jet, while a rocket engine is the entire system, ie, the rocket motor, the proplnt containers, pumps, etc. In conventional solid proplnt rockets, the motor and the engine happen to be the same piece of apparatus, but this is not so in liq proplnt rockets... 

The physical and chemical characteristics of these candidate liquid propellants vary widely. However, all of the liquids which have found application as rocket propellants have one common characteristic—they are designed to fit the particular requirements of at least one particular rocket engine and vehicle system. Obviously, few liquids initially fulfill the requirements of a propulsion system designed to perform a particular mission. Thus, various compromises must be undertaken between the... 

Applications. To date, the liquid propellant systems used in chemical propulsion range from a small trajectory control thruster with only 0.2 lbf (0.89 N) thrust for orbital station-keeping to large booster rocket engines with over l. 0 million lbf (4.44 MN) thrust. Bipropellant propulsion systems are the most extensively used type today for... 

Near-equilibrium flow conditions generally yield the maximum thrust for rocket propulsion, because partial recombination of the dissociated atoms, as the temperature falls, releases additional kinetic energy. On the other hand, when the rocket engine is considered for high temperature chemical processing, it is invariably desirable to freeze the composition attained in the combustion chamber. From both theoretical and practical standpoints, it is not always possible to predetermine the flow conditions in the De Laval nozzle as the foregoing discussion indicates,... 

R. J. Fontaine, R. S. Levine, and L. P. Combs, Secondary Nondestructive Instability in Medium Size Liquid Fuel Rocket Engines, in Advances in Tactical Propulsion, S. S. Penner, ed., AGARD Conference Proceedings no. 1, Maidenhead, England Technivision Services, 1968, 383-419. 

S. Lambiris, L. P. Combs, and R. S. Levine, Stable Combustion Processes in Liquid Propellant Rocket Engines, Fifth AGARD Combustion and Propulsion Colloquium, Braunschweig, April 1962. 

Solid-propellant rocket engines are attractive because of their simple propulsion principle, which avoids alimentation systems needed to produce combustion. Both oxidizer and fuel elements are present in a chemically stable material (the propellant), which is shaped to fit the motor itself. This feature, in particular, represents an obvious advantage for military applications such as nuclear ballistic missiles, which require a long-term storage capability and high service safety (3). 

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