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

reportActive / Technical Report | Accession Number: AD0328952 | Open PDF

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.

Author(s):
No Author(s) Identified
Author Organization(s):
AEROJET-GENERAL CORP SACRAMENTO CA
Descriptive Note:
Final rept.
Pagination:
0135

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):
LRP-257-VOL-5
Contract/Grant Number(s):
NAS5-1025
Monitor Series:
NASA
 Subject Terms
Joint Capability Areas:
JCA_4.7.2_Installation Services; JCA_4.7_Base and Installations Support; JCA_5_Command and Control; JCA_4.6.1_General Engineering; JCA_4.6_Engineering; JCA_5.3_Planning; JCA_1_Force Support; JCA_1.2_Force Preparation; JCA_5.3.3_Develop Strategy; JCA_5.3.4_Develop Courses of Action; JCA_5.3.5_Analyze Courses of Action; JCA_1.2.6_Concepts; JCA_5.6.3_Assess Achievement of Objectives; JCA_5.6_Monitor; JCA_3.2_Engagement; JCA_3_Force Application; JCA_3.2.1_Kinetic Means; JCA_6.4.1_Secure Information Exchange; JCA_6_Net Centric; JCA_1.4.2_Health Service Delivery; JCA_1.4_Force Support
Communities of Interest:
Weapons Technologies
Descriptor(s):
*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
Field(s)/Group(s):
Rocket Engines, Unmanned Spacecraft
Keyword(s):
THRUST VECTOR CONTROL SYSTEMS, ULTRAHIGH THRUST
Report Date:
1962 Apr 18