METHOD OF NONDESTRUCTIVE THERMAL PROTECTION OF LEADING EDGE OF FLYING VEHICLE AGAINST INTENSIVE THERMAL FLUX AND LEADING EDGE OF FLYING VEHICLE WITH NONDESTRUCTIVE THERMAL PROTECTION

摘要

FIELD: aeronautical engineering and rocketry; thermal protection of leading edge of flying vehicles performing flights in atmosphere at supersonic and hypersonic speed. SUBSTANCE: leading edge of flying vehicle is made in form of envelope with minimum aerodynamic drag; envelope is made from material possessing high thermal conductivity and radiating power. Edge has spherical blunts and side surfaces taking-up reduced thermal loads. Translucent rod mounted in envelope adjoins its inner surface. During flight of flying vehicle, thermal flux from spherical blunt is conductively removed to zone at reduced thermal loads. Then this flux is re-radiated from outer surface of this zone. Radiation flux from inner surface of edge is transported via transported via translucent rod to medium at lower temperature. EFFECT: possibility of smooth temperature distribution inside edge; increased area of radiating surface at small overall dimensions; enhanced operational reliability through arresting momentary peaks of thermal load. 5 cl, 7 dwg