FLIGHT DYNAMIC LOAD ANALYSIS OF THE ATLAS/CENTAUR BETA CONFIGURATION,

reportActive / Technical Report | Accession Number: AD0829057 | Need Help?

Abstract:

This report presents the results of an analytical investigation of the lengthened beta AtlasCentaur primary airframe structural integrity. The scope of the presentation includes 1 description of the analysis and control performance of the booster phase load relief autopilot, 2 description of the design criteria and resulting design loads, 3 a stress analysis demonstrating the ability of the lengthened Centaur and the Atlas airframe to support the design loads. Author

Author(s):
Kelly, C. P., Jr
Author Organization(s):
GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
Pagination:
0094

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release, Document Partially Illegible
Distribution Statement:
Availability: Document Partially Illegible.

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
GDA-AE61-1230
 Subject Terms
Communities of Interest:
No COI(s) Identified
Descriptor(s):
*LAUNCH VEHICLES, STRUCTURAL PROPERTIES, AIRFRAMES, AUTOMATIC PILOTS, STRESSES, AERODYNAMIC LOADING, ACCELERATION, PERFORMANCE(ENGINEERING), WIND, GUIDED MISSILE TRAJECTORIES, MODIFICATION KITS, STAGING, BOOSTER ROCKET ENGINES, FLIGHT TESTING
Field(s)/Group(s):
Mechanics, Ground Support Systems and Facilities for Space Vehicles
Keyword(s):
ATLAS CENTAUR LAUNCH VEHICLES, GRAPHS(CHARTS)
Report Date:
1961 Dec 08