Hypervelocity technology carbon/carbon testing
Abstract
The paper describes the procedures used at the Structures Test Laboratory of the Wright Laboratory's Flight Dynamics Directorate to test a carbon/carbon hot structure representing a typical hypersonic gliding body, and presents the results of tests. The forebody was heated to 1371 C over 13 test runs, using radiant quartz lamps; a vertical shear force of 5.34 kN was introduced to the nose at a stabilized temperature of 816 C. Test data were collected using prototype high-temperature strain gages, in-house-designed high-temperature extensometers, conventional strain gages, and thermocouples. Video footage was taken of all test runs. Test runs were successfully completed up to 1371 C with flight typical thermal gradients at heating rates up to 5.56 C/sec. Results showed that, overall, the termal test control systems performed as predicted and that test temperatures and thermal gradients were achieved to within about 5 percent in most cases.
- Publication:
-
IN: Structural testing technology at high temperature; Proceedings of the Conference
- Pub Date:
- 1991
- Bibcode:
- 1991stth.proc...38A
- Keywords:
-
- Carbon-Carbon Composites;
- Forebodies;
- Hypervelocity;
- Strain Gages;
- Thermocouples;
- Data Acquisition;
- High Temperature Tests;
- Quartz Lamps;
- Silicon Carbides;
- Temperature Gradients;
- Ground Support Systems and Facilities (Space)