Accession Number : AD0486403

Title :   THERMAL ANALYSIS AND METEOROID PROTECTION OF SPACE RADIATORS,

Corporate Author : AEROSPACE CORP EL SEGUNDO CA EL SEGUNDO TECHNICAL OPERATIONS

Personal Author(s) : Wright, Clifford C.

Report Date : JUN 1966

Pagination or Media Count : 98

Abstract : This report presents a summary of the analysis used in the preliminary design of space radiators, based upon a one-dimensional, steady-state analysis of a plane rectangular, finned-tube configuration. The report covers the concepts of equivalent heat sink temperature (equilibrium temperature of a dry radiator), radiator thermal energy balance and area equations, fin effectiveness, finned-tube radiant energy interchange, armor-type meteoroid protection, fluid pressure drop, and radiator core weight. The analysis assumes that axial heat conduction may be neglected, the tube wall temperature is uniform in the radial and circumferential directions, the equivalent heat sink temperature is uniform over the surface of the radiator, the flow distribution to the tubes is uniform, and steady-state conditions prevail. Based upon this analysis, a digital computer program was developed. The program was designed primarily for the purpose of conducting preliminary design evaluations, obtaining design data, and conducting parametric analyses to determine the effects of the various radiator parameters such as finned-tube geometry, fluid temperatures, heat rejection rate, materials, exposure time on radiator core area, and weight. An outline of the computer program is presented in the report.

Descriptors :   *SPACECRAFT), (*RADIATORS(HEATING AND COOLING), THERMAL RADIATION, HEAT SINKS, HEAT TRANSFER COEFFICIENTS, FINS, THERMAL ANALYSIS, METEORS, PENETRATION, COMPUTER PROGRAMMING, PIPES, HEAT TRANSFER, PRESSURE, POLAR ORBIT TRAJECTORIES, WALLS, PARTIAL DIFFERENTIAL EQUATIONS.

Subject Categories : Thermodynamics
      Unmanned Spacecraft

Distribution Statement : APPROVED FOR PUBLIC RELEASE