Accession Number : AD0912052

Title :   Design of Blunt, Frontal Enclosure under Pressure for Air-Launched Missiles. I. Thermal Mechanical Properties.

Descriptive Note : Technical publication,

Corporate Author : NAVAL WEAPONS CENTER CHINA LAKE CA

Personal Author(s) : San Miguel, Anthony

Report Date : JUN 1973

Pagination or Media Count : 46

Abstract : Equations were developed to predict the thermal and mechanical properties required for a pressurized, polymeric frontal enclosure envelope (FEE) on a missile or aircraft as a function of mission requirements. It appears that a state-of-the-art, composite polymer insulator can be used as a pressurized FEE with a thickness less than 0.1 in. to satisfy a mission of Mach 3 at 5,000 ft altitude for some 3 minutes. The thermal and mechanical properties needed for a thickness of 0.05 in. and longer (ten minutes) or shorter times are given as examples of the practical use of the proposed design analysis. The analytical approach presented is intended primarily for specifying thermal and mechanical property requirements for polymeric materials. (Author, modified-PL)

Descriptors :   *HEAT RESISTANT PLASTICS), (*RADOMES, AIR TO AIR MISSILES), (*BLUNT BODIES, AIR TO AIR MISSILES), (*BOUNDARY LAYER, BLUNT BODIES), (*MEMBRANES, MATHEMATICAL PREDICTION, EQUATIONS, THICKNESS, THERMAL CONDUCTIVITY, THERMAL PROPERTIES, HEAT TRANSFER, PRESSURE, MECHANICAL PROPERTIES, VISCOELASTICITY, FAILURE(MECHANICS), SUPERSONIC FLIGHT, STAGNATION POINT, POLYMERS, MACH NUMBER, FRACTURE(MECHANICS), THERMODYNAMICS, AERODYNAMICS, PLASTICS.

Subject Categories : Air- and Space-launched Guided Missiles
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE