Rocket technology

Mcrrit, G., ind G. Redinger. 1973. Measurements of heat and impulse transfer coefficient m turbulent stratified flow. Journal of Rocket Technology and Astronautics, no. I I. 

Reactions or compounds of exceptional hazard are those involving combinations of powerful oxidants and reducing agents, in the so-called redox reactions or redox compounds. Such systems are capable of very large energy release rates, the best known examples being the propellant pairs used in rocket technology. 

M. Shorr, A. J. Zaehringer Solid Rocket Technology. John Wiley and Sons, Inc., 1967. 

M. Schorr A.J. Zaehringer, eds, "Solid Rocket Technology , Wiley, NY... 

FASp. In Rocket Technology it stands for Final Average Sustained Pressure , and refers to die average pressure near the end of a test run before the pressure has begnn to foil off markedly... 

In rocket technology the term burning rate is usually employed in the more restricted sense of the rate of propagation of combustion at constant pressure in the rocket motor... 

Burning Area, Required In rocket technology, it is the area of solid-propellant material that is made available for combustion to satisfy the... 

Burnout, In rocket technology, this term has two meanings a)The termination of burning of a jet or rocket engine because of exhaustion of fuel. 

A demand for a specially high level of significance of at least 0.9999 is present in rocket technology and spacecraft industry. In order to reach the mentioned level of significance, there has to be an almost disappearing level of (3 so that there is no chance of mounting a defective part into the mentioned crafts. 

Perhaps one of the most important performance parameters in rocket technology from point of usage is the specific impulse. It is defined as the propulsive impulse. 

In rocket technology, the chamber in which the reaction of the propellants takes place. 

In rocket technology, a design of the propellant charge which results in the combustion process being restricted to the cross-section of the combustion chamber. This type of combustion is produced by coating all other surfaces with a non-flammable layer. In such rockets long, combustion times (10 minutes or more) at a nearly constant thrust can be achieved. 

Hybrids is the name given in rocket technology to systems in which a solid fuel in the form of a case-bonded charge with a central perforation is reacted with a liquid oxidant. Hybrids with solid oxidant and liquid fuel also exist. Hybrids can be thrust-controlled during combustion and can even be re-ignited if hypergolic components are incorporated in the formulation of the fuel charge. 

In rocket technology, the ratio between the initial mass of the rocket and its final mass, after the propellant has burnt out. The relation between the end-velocity of a rocket projectile (theoretical value, without considering friction by the atmosphere) and the mass ratio is described by the equation... 

In rocket technology the name for liquid and homogeneous propellants, which require no other reaction partner for the formation of gaseous reaction products. Gas formation can be due to catalytic decomposition (on concentrated H202 or anhydrous hydrazine) or to an intramolecular reaction, e.g., by decomposition of propylnitrate generating N2, CO, C02, NO, etc., -> Liquid Propellants. 

In rocket technology, the ratio between the burning surface of the propellant and the smallest cross-section of the nozzle. It determines the resultant pressure in the combustion chamber of the rocket (other relevant keywords -> Burning Rate, - Gas Jet Velocity - Rocket, Solid Propellant Rocket, Specific Impulse, - Thrust). 

In rocket technology, a collective term for all chemical propellants. 

In rocket technology, the recoil force produced by rearward gas discharge. It is expressed in tons, kiloponds, or newtons, and is one of the most important characteristic rocket parameters. The initial weight of a rocket must remain within a certain relation to the thrust. The launching thrust chosen is usually higher than the cruising thrust this can be achieved by the use of -> Boosters. 

In rocket technology, a design of the propellant charge which results in the combustion process being restricted to the cross-section of the... 

Hybrids is the name given in rocket technology to systems in which a solid fuel in the form of a case-bonded charge with a central perfora-... 

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