دورية أكاديمية

THEORETICAL EFFECTS OF REENTRY AERODYNAMIC HEATING ON THE EXTERNAL SKIN STRUCTURE OF AMRAD EXPERIMENT NUMBER ONE

التفاصيل البيبلوغرافية
العنوان: THEORETICAL EFFECTS OF REENTRY AERODYNAMIC HEATING ON THE EXTERNAL SKIN STRUCTURE OF AMRAD EXPERIMENT NUMBER ONE
المؤلفون: Burleson, W G, Reynolds, R A
المساهمون: ARMY MISSILE COMMAND REDSTONE ARSENAL AL SYSTEMS RESEARCH DIRECTORATE
المصدر: DTIC AND NTIS
سنة النشر: 1965
المجموعة: Defense Technical Information Center: DTIC Technical Reports database
مصطلحات موضوعية: Fluid Mechanics, AERODYNAMIC HEATING, REENTRY VEHICLES, ABLATION, AIRFRAMES, ALUMINUM, ANTIMISSILE DEFENSE SYSTEMS, ATMOSPHERE ENTRY, BASE FLOW, BLUNT BODIES, CONICAL BODIES, DRAG, EQUATIONS, GLASS, GRAPHICS, GUIDED MISSILE TRAJECTORIES, HEAT SHIELDS, HEAT TRANSFER, MATHEMATICAL ANALYSIS, NOSE CONES, PHENOLIC PLASTICS, RADAR, RECOVERY, SEPARATION, SURFACE TEMPERATURE, TABLES(DATA), THEORY, THERMAL INSULATION, THICKNESS, VOLUME
الوصف: Calculated reentry aerodynamic heating effects on the external skin of an ICBM reentry test vehicle having a relatively low weight-to-drag ratio are presented in this report. The vehicle is a blunt cone with the aft portion designed to fail just after maximum heating and the forward portion designed to survive to impact. The tape-wound, reinforced plastic heat shield is subjected to maximum reentry heating rates between 1,250,000 and 6,500,00 kcal/sq m hr. Resulting external and internal surface temperature histories are given. Effects of extreme trajectory, vehicle characteristics, and atmosphere variations on the aluminum substructure temperature histories are discussed.
نوع الوثيقة: text
وصف الملف: text/html
اللغة: English
العلاقة: http://www.dtic.mil/docs/citations/AD0465896Test
الإتاحة: http://www.dtic.mil/docs/citations/AD0465896Test
http://oai.dtic.mil/oai/oai?&verb=getRecord&metadataPrefix=html&identifier=AD0465896Test
حقوق: Approved for public release; distribution is unlimited.
رقم الانضمام: edsbas.B70F608C
قاعدة البيانات: BASE