Accession Number:

AD0257861

Title:

THE PROPULSIVE EFFICIENCY OF A LOW-THRUST PULSED EXHAUST ROCKET IN FIELD-FREE SPACE

Descriptive Note:

Corporate Author:

AEROCHEM RESEARCH LABS INC PRINCETON N J

Personal Author(s):

Report Date:

1961-04-01

Pagination or Media Count:

1.0

Abstract:

The propulsive efficiency of a low-thrust, pulsed exhaust velocity rocket in field-free space is compared with that of a constant exhaust velocity rocket. The efficiency investigated is the actual velocity at burnout normalized by the velocity a zero payload rocket would attain if all the kinetic energy of the exhaust, taken with respect to the rocket, was converted to vehicle velocity. The square-wave shaped pulse is shown to give the same efficiency as the constant exhaust velocity case, while in the asymptotic extreme of many pulses per mission the other pulse shapes considered give lower efficiencies. It is also shown that the characteristics of an optimized pulsed exhaust velocity rocket must be calculated in a manner slightly different from that of the constant exhaust velocity case. This is because the optimum exhaust velocity for a constant exhaust velocity rocket, in general, does not equal the optimum average exhaust velocity for an otherwise similar pulsed exhaust velocity rocket. Also the efficiency, delta VV sub c is usually less. Author

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Distribution Statement:

APPROVED FOR PUBLIC RELEASE