MOLYBDENUM STRUCTURAL COMPONENT PROGRAM

MOLYBDENUM STRUCTURAL COMPONENT PROGRAM

Active / Technical Report | Accession Number: AD0404211 | Open PDF

Abstract:

The design and analysis of the final component control surface was completed. The control sur face will be located at the wing trailing edge. This component of TZM molybdenum is composed of a combination truss-crimped web substructure covered with corrugated panels on the mold line surfaces. Attachment of the panels to the sub structure is made at the corners by threaded at tachments in oversize holes to allow for thermal expansion. The panels carry only air loads while the substructure provides capabilities for carry ing shear, bending and torque loads. The hinge line is located along the forward rib so that a 20 degree movement contained either up or down, similar to conditions expected on a re entry vehicle.

Author(s):

No Author(s) Identified

Author Organization(s):

MCDONNELL AIRCRAFT CORP ST LOUIS MO

Descriptive Note:

Progress rept., 1 Feb - May 1963

Supplementary Note:

DOI: 10.21236/AD0404211

Pagination:

0008

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:

Approved For Public Release

Distribution Statement:

Approved For Public Release; Distribution Is Unlimited.

RECORD

Collection: TR

Identifying Numbers

Contract/Grant Number(s):

NOW-61-0653

Monitor Series:

NAVWEPS

Subject Terms

Communities of Interest:

Air Platforms

Descriptor(s):

*WINGS, *MOLYBDENUM ALLOYS, *TRAILING EDGES, STRUCTURAL PROPERTIES, THERMAL EXPANSION, CONTROL SURFACES, AERODYNAMIC LOADING

Field(s)/Group(s):

Properties of Metals and Alloys, Aircraft

Keyword(s):

MOLYBDENUM ALLOY TZM

Report Date:

1963 Mar 01