Accession Number : ADA294055
Title : Leading Edge Material Thermal and Ablation Test Evaluations for Extended Range Reentry Missions.
Descriptive Note : Final rept. May 94-Jan 95,
Corporate Author : NICHOLS RESEARCH CORP ALBUQUERQUE NM
Personal Author(s) : Moody, Henry L. ; Graves, Craig M. ; Moody, Daniel S. ; Deleget, James L.
PDF Url : ADA294055
Report Date : JAN 1995
Pagination or Media Count : 131
Abstract : Arc-heater tests were conducted on candidate Air Force leading edge materials for extended range reentry applications. The objectives were to obtain thermal and ablation data on leading edge materials at a swept angle representative of the operational system. Model holders were designed and fabricated to allow the testing of leading edges at the desired 60 deg sweep angle and for comparison, 0 deg sweep. The NASA-Ames 60MW (IHF) facility was selected because of its unique ability to simulate both the pullout and glide phases of extended range in a single test. A total of 23 arc-heater runs were made, 11 calibration and 12 model runs. Calibration involved using a replica configuration of the 60 sweep model to acquire heating and pressure data on the nosetip and leading edges. In the 12 model runs, 20 material samples were tested. The test variables included material type (223 Pan C-C, FWPF C-C, 40DO C-C, SAID C-C with Ultramet coating, Cercarb, and an MSNW impregnated carbon sock over Poco), weave orientation relative to the sweep angle, angle of attack (0 deg and 10 deg), and trajectory sequence (i.e., glide only, pullout only, pullout and glide). The tests resulted in the generation of a data base for C-C leading edge material thermal and ablation responses during high altitude reentry flight. All pure C-C materials ablated in a well behaved laminar manner with no apparent mechanical ablation. The other materials appear to either have a thermostructural problem and/or underwent melt with resulting complex and irregular shaping . Weave orientation appeared to have little influence on ablation; the influence of angle of attack was as expected (the shape change was biased by the angle of attack). (MM)
Descriptors : *REENTRY VEHICLES, *GUIDED MISSILE TRAJECTORIES, *ATMOSPHERE ENTRY, *LEADING EDGES, *AEROTHERMODYNAMICS, TEST AND EVALUATION, THERMAL PROPERTIES, DATA BASES, ABLATION, MECHANICAL PROPERTIES, MODIFICATION, ANGLE OF ATTACK, COATINGS, CARBON CARBON COMPOSITES, ANTENNAS, SHAPED CHARGES, CALIBRATION, TRAJECTORIES, LAMINAR FLOW, NOSES, GUIDED MISSILE COMPONENTS, ANTENNA WINDOWS.
Subject Categories : Guided Missile Traj, Accuracy and Ballistics
Guided Missile Dynam, Config & Cntrl Surfaces
Guided Missile Reentry Vehicles
Distribution Statement : APPROVED FOR PUBLIC RELEASE