Accession Number : AD0686330

Title :   THE THERMAL RESPONSE OF HEAT-SINK REENTRY VEHICLES

Corporate Author : POLYTECHNIC INST OF BROOKLYN NY DEPT OF AEROSPACE ENGINEERING AND APPLIED MECHANICS

Personal Author(s) : Crisp, John D ; Feitis, Peter

PDF Url : AD0686330

Report Date : Jul 1960

Pagination or Media Count : 38

Abstract : In a performance comparison of reentry vehicles there are a number of important interrelated criteria determining the acceptability of the vehicle. These include the peak deceleration, the limits imposed by atmospheric heating, guidance control and accuracy, and time of descent. A general study has been undertaken which places emphasis on the first two considerations and is based on three vehicle configurations appropriate to both manned and unmanned entry into the earth's atmosphere from high supercircular speeds. The first vehicle type, designated 'sphere' is a high drag, nonlifting body. The second, referred to below as the 'body' type, is of moderate drag and possesses a trimming lift capability; while the third, the 'wing', simulates low-drag, high lift vehicles. For each configurational type heat transfer behavior is to be assessed on the basis of three techniques of heat dissipation, viz., by radiation alone, by ablation or internal cooling, and by the utilization of the vehicle as a heat sink. In this paper are presented the results of the heat sink studies in the form of thermal-time response and specifically in terms of temperature-time histories and peak temperatures as a function of vehicle mass, shape and aerodynamic parameters, entry orbit. The thermal response is correlated to peak deceleration.

Descriptors :   *ATMOSPHERE ENTRY, *REENTRY VEHICLES, ABLATION, AERODYNAMIC CONTROL SURFACES, AERODYNAMIC HEATING, HEAT SINKS, HEAT TRANSFER, LIFTING REENTRY VEHICLES, SPHERES, THERMAL ANALYSIS, WINGS

Subject Categories : Spacecraft Trajectories and Reentry

Distribution Statement : APPROVED FOR PUBLIC RELEASE