Accession Number:

AD0328952

Title:

DESIGN STUDY OF A LARGE UNCONVENTIONAL LIQUID PROPELLANT ROCKET ENGINE AND VEHICLE. VOLUME 5. ADVANCED ENGINE-VEHICLE INTEGRATION STUDY

Descriptive Note:

Final rept.

Corporate Author:

AEROJET-GENERAL CORP SACRAMENTO CA

Personal Author(s):

Report Date:

1962-04-18

Pagination or Media Count:

135.0

Abstract:

Identifiers F-D engines, Thrust vector control, Weight, Bell nozzles.Advanced engine design concepts were studied on the cost performance parameter dollars per pound of payload of a total airborne vehicle and ground support system. Emphasis was placed on use of a 2 million pounds sea level force deflection F-D engine. This engine was used in two basic vehicle configurations a two stage vehicle with a thrust to weight ratio TW of 1.1 and using the F-D engine in both stages operating at Pc of 1000 psi and a single-stage-to-orbit vehicle with a TW of 1.4 and using one F-D engine operating at Pc of 3000 psi. Emphasis was placed on the engine installation, the engine influence on connecting subsystems, and the engine mounting structure.

Descriptors:

• *ROCKET ENGINES
• *BOOSTER ROCKET ENGINES
• *HYDROGEN
• RELIABILITY
• CONFIGURATIONS
• ATTACHMENT
• ROCKET ENGINE CASES
• THRUST
• THRUST VECTOR CONTROL SYSTEMS
• LIQUID ROCKET PROPELLANTS
• KEROSENE
• GAS GENERATING SYSTEMS
• ROCKET NOZZLES
• FUEL INJECTION
• PROPELLANT TANKS
• BELL NOZZLES
• OXYGEN
• MONOCOQUES
• CONTROL SYSTEMS
• SPACECRAFT

Subject Categories:

• Rocket Engines
• Unmanned Spacecraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE