INTELSAT VI satellite test program

Author

Tadler, George A.

Author_Institution

Hughes Aircraft Co., Los Angeles, CA, USA

fYear

1991

fDate

24-26 Sep 1991

Firstpage

57

Lastpage

61

Abstract

The INTELSAT VI satellite test program was designed around repetitive ground testing and no onboard integrated diagnostics. The ultimate design goal was to maximize both communications capacity and operational lifetime by minimizing the satellite dry weight (i.e. satellite without propellants). On board integrated diagnostic increase cost, reduct operational lifetime, and decrease reliability because of the added complexity to the satellite design. System reliability was optimized by adding redundancy to the maximum possible extent. The repetitive test philosophy began with component-level testing and ended with the final test verification program at the launch base

Keywords

aerospace test facilities; aerospace testing; artificial satellites; environmental testing; redundancy; reliability; INTELSAT VI satellite test; aerospace testing; communications capacity; component-level testing; final test verification; operational lifetime; redundancy; reliability; repetitive ground testing; weight minimisation; Aircraft; Aluminum; Artificial satellites; Propellants; Propulsion; Rockets; Satellite ground stations; Telemetry; Testing; Titanium;

fLanguage

English

Publisher

ieee

Conference_Titel

AUTOTESTCON '91. IEEE Systems Readiness Technology Conference. Improving Systems Effectiveness in the Changing Environment of the '90s, Conference Record.

Conference_Location

Anaheim, CA

Print_ISBN

0-87942-576-8

Type

conf

DOI

10.1109/AUTEST.1991.197520

Filename

197520