Accession Number:

AD0600234

Title:

INVESTIGATION OF A METHOD FOR THE PREDICTION OF VIBRATORY RESPONSE AND STRESS IN TYPICAL FLIGHT VEHICLE STRUCTURE. SUPPLEMENT 1 - DYNAMIC MODELING OF COMPLEX STRUCTURES

Descriptive Note:

Rept. for Dec 1962-Aug 1963

Corporate Author:

NORTHROP CORP HAWTHORNE CA NORAIR DIV

Report Date:

1963-08-01

Pagination or Media Count:

336.0

Abstract:

The dynamically similar structural model of the preceding contract See AD-416 784 was redesigned and reworked to improve the simulation. The sandwich structure simulation, the backing board simulation, the intake ducting simulation were improved. Some previously discovered errors in simulation were corrected. The reworked model was then Vibroacoustically tested. The results of this testing were compared to the results of the actual fuselage portion testing of the previous contract. The model was modified to obtain a dynamically similar structural model of the complete XSM-62 Snark missile. The Acoustic noise Test Program that was performed on the XSM-62 Snark missile during the design and development of the Snark missile program was duplicated for the model. The model test data was compared to the results of the missile test program. This was done to show the feasibility of such a dynamic modeling method for design of future missile and space vehicle systems.

Subject Categories:

  • Aerodynamics
  • Guided Missile Dynamics, Configurations and Control Surfaces

Distribution Statement:

APPROVED FOR PUBLIC RELEASE