HYBRID MOTOR CONCEPTS (I)-COMPONENT DEVELOPMENT AND REPRODUCIBILITY FIRINGS

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Abstract:

Eighteen successful firings of a 7 x 30 test motor were made with a concentric configuration of solid propellant and hybrid fuel grains. There were no hardware failures, and commercial injector nozzles and valves were used. Conventional rocket nozzle and chamber designs were satisfactory for hybrid use and standard insulation and ablative materials provided good protection of exposed hardware. A piston expulsion device was developed and provided a reliable and reproducible method of pressurizinf the oxidizer. A solid propellant gas generator provided a compact pressure source for driving the piston expulsion system. The ratio of the booster phase thrust to the hybrid sustainer thrust exceeded 20. Combustion efficiency during hybrid operation was about 90 of theoretical. The reproducibility of total impulse was poor in the hybrid phase. Combustion and injection processes appear to be inherently less reproducible than solid propellants. Author

Author(s):
Stone, William C.
Author Organization(s):
ROHM AND HAAS CO HUNTSVILLE ALA REDSTONE ARSENAL RESEARCH DIV
Annotation:
Hybrid motor concepts. I. Component development and reproducibility firings.
Pagination:
0035

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
S-70
Contract/Grant Number(s):
DA01 021AMC11 040Z
 Subject Terms
Joint Capability Areas:
JCA_3.2_Engagement; JCA_3_Force Application; JCA_3.2.1_Kinetic Means; JCA_1_Force Support; JCA_1.2_Force Preparation; JCA_1.2.6_Concepts
Modernization Areas:
Space
Communities of Interest:
Weapons Technologies
Descriptor(s):
*HYBRID ROCKET ENGINES, *BOOSTER ROCKET ENGINES, *SUSTAINER ENGINES, HYBRID ROCKET ENGINES, HYBRID ROCKET ENGINES, ROCKET PROPELLANT GRAINS, HYBRID ROCKET PROPELLANTS, CONFIGURATIONS, LIQUID ROCKET OXIDIZERS, SOLID ROCKET PROPELLANT BINDERS, COMBUSTION CHAMBERS, ROCKET ENGINE CASES, ROCKET NOZZLES, INJECTORS, GAS GENERATING SYSTEMS, PISTONS, CAPTIVE TESTS, THRUST, SPECIFIC IMPULSE, INTERIOR BALLISTICS, BURNING RATE, AMMONIUM COMPOUNDS, PERCHLORATES, OXYGEN, TETROXIDES, NITROGEN COMPOUNDS, ALUMINUM, BUTYL RUBBER
Field(s)/Group(s):
Rocket Engines, Liquid Rocket Propellants, Solid Rocket Propellants
Keyword(s):
NITROGEN OXIDE(NO2), NITROGEN OXIDE(N2O4)
Report Date:
1965 Sep 01