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Page Title:
Rocket engine performance requirements |
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|  MIL-L-23822C(AS)
3.3.7 (Cont'd)
Booster shutoff valve
Multipurpose nitrogen valve
Nitrogen check valve - oxidizer system
Nitrogen check valve - fuel system
Oxidizer valve & shear fitting
Fuel valve & shear fitting
Miscellaneous fittings and tubing
3.3.8
Weight. The weight of the rocket engine, as defined in
3.1, shall be 22 pounds 1 pound.
3.4
Performance requirements.
3.4.1
Rocket engine performance requirements. The rocket
engine shall conform to the requirements specified in Table I when
supplied with the quantity and type of fuel and oxidizer specified in
3.4.2.
3.4.1.1
Rocket engine thrust control. Thrust controls shall
be provided so that engine thrust may be set as shown in Tables H
and III.
3.4.2
Propellant.
3.4.2.1
Oxidizer. The oxidizer shall be inhibited red fuming
nitric acid (IRFNA) conforming to MIL-P-7254, Type IIIB. 211.3
pounds pounds shall be used to meet the requirements of Table I.
3.4.2.2
Fuel. The fuel (MAF-4, Hydyne) shall be a blend of
6 0% 1% unsymmetrical dimethylhydrazine by weight conforming to
MIL-D-25604, and the remainder by difference of diethylenetriamine
conforming to D-D-1271. 70.8 pounds 1 pound shall be used to
meet the requirements of Table I.
3.4.2.2.1
Specific Gravity.
The specific gravity of the fuel at
60 degrees ()/60 Fahrenheit (F) shall be 0.859 0.003.
3.4.3
Propellant pressurizing agent. The propellant pres-
surizing
agent shall be nitrogen conforming to MIL-P-27401.
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