Rapid Method for Spacecraft Sizing

Abstract

In this paper, a rapid method for spacecraft sizing is presented. This method is useful in both the conceptual and preliminary design phases of scientific and communication satellites. The aim of this method is to provide a sizing procedure similar to the ones used in the design of aircraft; actually by determining the mass of all the spacecraft subsystems. In the Introduction, the importance of an accurate initial mass budget in the design of satellites is emphasized. Literature about this topic is not very extensive and most of the existing methods have been recapitulated. The methodology followed in the proposed procedure for spacecraft mass sizing is based on these methods. Data from 26 existing satellites have been considered to obtain correlations between each subsystem mass and the mass of the whole spacecraft.

Keywords

spacecraft mass budget subsystem mass preliminary design

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References

Larson

J. W.

Wertz

J. R.

Space mission analysis and design, 2nd edition, 1992 (Kluwer Academic Publishers, Dordrecht, The Netherlands).

Agrawal

B. N.

Design of geosynchronous spacecraft, 1986 (Prentice-Hall, Englewood Cliffs, New Jersey).

Pritchard

W. L.

Sciulli

J. A.

Satellite communication. Systems engineering, 1986 (Prentice-Hall, Englewood Cliffs, New Jersey).

Satellite subsystems. Department of Aerospace Engineering and Engineering Mechanics, University of Texas at Austin, 1992.

ESA PSS-03–108. Spacecraft thermal control design data, Vol. 5, 1989, S: Existing satellites (ESA Publications Division, ESTEC, Noordwijk, The Netherlands).