Title

Prediction of Space Vehicle Thermal Characteristics

Date

1965

Index Abstract

Coming Soon

Photo Quality

Complete

Report Number

AFFDL TR 65-139

Creator

Bevans, J. T.

Ishimoto, T.

Loya, B. R.

Luedke, E. E.

Corporate Author

TRW Systems Group

Laboratory

Air Force Flight Dynamics Laboratory

Extent

188

NTRL Accession Number

AD472558

Identifier

AD0472558

Access Rights

Notice(s)

Distribution Classification

1

Contract

AF 33(615)-1725

DoD Project

6146

DoD Task

614617

DTIC Record Exists

Yes

Distribution Change Authority Correspondence

AFFDL LTR

Distribution Change Action Date

7/6/2005

Abstract

The first phase of a program to improve the prediction of spacecraft thermal performance is reported. The study has consisted of measuring actual joint thermal conductance, correlation of the measured joint conductance, programming an improved method of thermal radiation analysis, and performing an experimental comparison of predicted radiation exchange for a simple geometrical system. Three types of structural and three sizes of component mounting joints were tested and the conductances measured. A successful method of correlation was developed for the unfilled component mounting joints. A method of radiation analysis has been programmed which uses directional thermal radiation properties and accounts for the specularity and/or diffuseness of these properties. The results of this program can be readily incorporated into most existing thermal analysis programs. The user has the choice of the specular, the diffuse, or the specular-diffuse assumption. The prediction of radiation exchange using these assumptions for simple geometrical arrangements has been compared to experiment. Although the results were within the over-all experimental tolerances, further improvement in the predicted values is believed possible.

Report Availability

Full text available

Date Issued

1965-10

Provenance

Lockheed Martin Missiles & Fire Control

Type

report

Format

1 online resource