ASTM D2506-80(1989)

Standard Terminology Relating to Solid Rocket Propulsion (Withdrawn 1998)

General Information

• Status: Withdrawn
• Withdrawal Date: 09-Feb-1998
• ICS: 75.160.10 - Solid fuels
• Technical Committee: F07 - Aerospace and Aircraft
• Drafting Committee: F07.90 - Executive

Standards Content (Sample)

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ASTM D2506 80 II 0759510 0025810 6 II
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~m~ Designation: D 2506 - 80 (Reapproved 1989) An American National Standard
Standard Terminology Relating to
1
Solid Rocket Propulsion
This standard is issued under the fixed designation D 2506; the nlimber immediately following the designation indicates the year of
original adoption or, in the case of revision, the year of last revision. A number in parentheses indicates the year of last reapproval. A
superscript epsilon (E) indicates an editorial change since the last revision or reapproval.
1. Scope
2). All numerical values must be accompanied by specifica-
tion of the following assumptions: '
1.1 These symbols and definitions provide nomenclature
4.3.1 Chamber pressure (Pc),
for those parameters of common usage associated with solid
4.3.2 Ambient pressure (P ),
amb
rocket propulsion. In the interest of common understanding
4.3.3 Nozzle area expansion ratio (E) and whether or not
and standardization, consistent word usage is encouraged to
this is optimum, and
help eliminate the major barrier to effective technical com­
4.3.4 Nozzle divergence haIf-angle (a).
munication, particularly in the case of words having eco­
nomic importance.
NOTE I-Use the same time interval and propellant mass assump­
tions as for lopd; therefore, do not report a numerical value oflop without
2. Significance and Use
also reporting the corresponding value of lopd'
NOTE 2-With the only exception of ["SpS' all reported values of
2.1 Significant terms are grouped into major categories
propellant specific impulse must be accompanied by a statement of the
which have generally accepted meanings. Within each major
assumptions made in calculating a theoretical value, or a statement of
category, significant terms are given definite meanings,
the existing motor conditions and assumptions in obtaining a measured
symbols, and definitions. The following' criteria determine
or corrected value. A degree sign (") indicates a theoretical value, not a
acceptability of a term for inclusion:
value that has been obtained from ol"derived from the results ofa motor
2.1.1 The term is of interest to solid propulsion workers.
firing. In .stating the assumptions or motor conditions, or both, a
2.1.2 The term has a specific application or has been shQrthand notation may be used if no confusion will result. For
example, a measured propellant specific impulse of241.6 Ibf· s/lbm over
subject to misunderstanding or misuse.
the 25 psia action time from a motor operating at 1230 psia, exhausting
2.1.3 The term is not adequately defined for general use in
to 11.6 psia with an expansion ratio of9.8, a nozzle divergence angle of
any standard dictionary.
17.5 deg, and an expended mass of 3563 Ibm may be abbreviated as
2.1.4 Terms are used in current systems.
follows:
DEFINfI10N OR DESCRIPTION OF TERMS
IOpd(l230/11.6,9.8, 17's", aO.2Sp.mm - mba = 3563)
3. Geometry-Linear dimensions shall be expressed in = 241.6 Ibf· s/lbm
feet or inche&, including any decimal parts, and abbreviated
4.4 Theoretical Propellant Specific Impulse (r ), calcu­
sp
as ft or in. Angular dimensions shall be expressed in degrees
lated from propellant therm
...