X-20 High Temperature Side Window Test Evaluation

Item

Title
X-20 High Temperature Side Window Test Evaluation
Date
1965
Index Abstract
Coming Soon
Photo Quality
Complete
Report Number
AFFDL TR 65-155
Creator
McGinnis, John C.
Corporate Author
The Boeing Company
Laboratory
Air Force Flight Dynamics Laboratory
Extent
222
NTRL Accession Number
AD477758
Identifier
AD0477758
Access Rights
Export Controls
Distribution Classification
1
Contract
AF 33(615)-2013
DoD Project
1368
DoD Task
136802
DTIC Record Exists
No
Distribution Change Authority Correspondence
AFFDL LTR
Abstract
The purpose of this program was to experimentally verify the X-20A side window assembly and provide experience for improved window design. The objective was to verify the structural integrity of an X-20A high temperature window design in the X-20A flight environment and provide test data to evaluate the design analysis and development procedures utilized. The window was subjected to a low-level boost vibration environment, outward acting (partial vacuum) limit boost pressure of 7.7 psia, and a simulated reentry heating time-temperature history. The window failed during the re-entry temperature cycle. The primary cause of failure was the high temperature gradient through the depth of the window frame of approximately 850 F which exceeded by a factor of 2 the ultimate design value. The extreme thermal gradient caused thermal curvature of the window frame which induced glass curvature in excess of allowable. Measured temperature and deflections are presented and compared with analytical values. A thermal analysis is presented and compared with test values. Deficiencies of the X-20 window design as determined from the test program are pointed out and suggested methods of improvement are given.
Report Availability
Full text available
Date Issued
1965-11
Provenance
Lockheed Martin Missiles & Fire Control
Type
report
Format
1 online resource
Media
AFFDLTR65-155.pdf