Detonation Tube Conditions for Simulating: RP-1/LOX and Various Amine/ N2O4 Rocket Engine Plumes

reportActive / Technical Report | Accession Number: AD0771067 | Open PDF

Abstract:

The report documents the running conditions necessary to simulate RP- 1LOX and various AmineN2O4 rocket engine plumes using the Grumman Detonation Tube Facility to reproduce the chemical and thermodynamic state properties of the rocket engine combustion chamber. Absolute measurements of shortwave infrared SWIR radiation from a variety of plumes are being obtained. The propellant combinations being investigated are UDMHN2O4, A-50N2O4, RP-1LOX, and H2O2.

Author(s):
Leng, J. ; Slack, M. W.
Author Organization(s):
GRUMMAN AEROSPACE CORP BETHPAGE NY RESEARCH DEPT
Descriptive Note:
Research memo.
Pagination:
0028

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release
Distribution Statement:
Approved For Public Release; Distribution Is Unlimited.

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
RM-581
Contract/Grant Number(s):
DAAH01-72-C-0728
Monitor Series:
DARPA
 Subject Terms
Joint Capability Areas:
JCA_3.2_Engagement; JCA_3_Force Application; JCA_3.2.1_Kinetic Means; JCA_6_Net Centric; JCA_6.2.1_Information Sharing; JCA_6.2.2_Computing Services; JCA_6.4.1_Secure Information Exchange
Communities of Interest:
Weapons Technologies
Descriptor(s):
*ROCKET EXHAUST, AMINES, CHEMICAL PROPERTIES, DETONATIONS, HYDRAZINES, LIQUID OXYGEN, NITROGEN COMPOUNDS, NITROGEN OXIDES, ROCKET FUELS, SHOCK TUBES, SIMULATION, TABLES(DATA), TETROXIDES, THERMOCHEMISTRY, THERMODYNAMICS
Field(s)/Group(s):
Rocket Engines
Keyword(s):
A 50 propellants, RP 1 fuels
Report Date:
1973 Nov 01