Accession Number:

AD0885564

Title:

Altitude Ignition Studies

Descriptive Note:

Final rept. Jul 1968-Dec 1970

Corporate Author:

AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CA

Personal Author(s):

• Mastromonico, Charles R.

Report Date:

1971-07-01

Pagination or Media Count:

28.0

Abstract:

A facility for analyzing the effects of engine hardware parameters on the pulse characteristics of bipropellant attitude control thrusters in a space environments was constructed at the Air Force Rocket Propulsion Laboratory AFRPL. In a series of tests involving 32 engine configurations, 17 engine parameters were varied. The propellants considered were N2H4-UDMH 5050 and MMH fuels and NTO as the oxidizer. The experimental phase of the program was based on a statistical test matrix designed to minimize the number of firings and the hardware requirements. This report includes a detailed description of the altitude ignition facility and presents an analysis of the system and the data obtained. Author

Descriptors:

• *THRUST VECTOR CONTROL SYSTEMS
• *HYPERGOLIC ROCKET PROPELLANTS
• MATHEMATICAL MODELS
• ATTITUDE CONTROL SYSTEMS
• HYDRAZINES
• ALTITUDE CHAMBERS
• COLD FLOW
• HYPERGOLIC IGNITION
• VERNIER ROCKET ENGINES
• IGNITION LAG
• HIGH ALTITUDE
• COMBUSTION CHAMBERS
• NITROGEN OXIDES

Subject Categories:

• Combustion and Ignition
• Liquid Rocket Propellants

Distribution Statement:

APPROVED FOR PUBLIC RELEASE