Accession Number:

AD0373614

Title:

ADVANCED CRYOGENIC ROCKET ENGINE PROGRAM AEROSPIKE NOZZLE CONCEPT

Descriptive Note:

Technical Report,01 Mar 1966,01 Jun 1966

Corporate Author:

ROCKETDYNE CANOGA PARK CA CANOGA PARK United States

Personal Author(s):

• Mahugh,Vernon L.

Report Date:

1966-06-30

Pagination or Media Count:

128.0

Abstract:

Analysis and preliminary design of an advanced rocket engine using an aerospike nozzle and analysis, test hardware design, and test evaluation of thrust chamber performance and thrust chamber durability are described.

Descriptors:

• LIQUID PROPELLANT ROCKET ENGINES
• RESEARCH MANAGEMENT
• ROCKET NOZZLES
• LIQUID PROPELLANT ROCKET ENGINES
• COMBUSTION CHAMBERS
• CAPTIVE TESTS
• PERFORMANCE(ENGINEERING)
• INJECTORS
• FUEL INJECTORS
• TURBOPUMPS
• THROTTLING
• MIXTURES
• CRYOGENIC PROPELLANTS
• HYDROGEN
• ANNULAR NOZZLES
• WATER
• LIQUID COOLED
• COMBUSTION
• SPIKES
• COPPER
• FILM COOLING
• PIPES
• NICKEL
• STAINLESS STEEl

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE