Conceptual design for a solar instrument on the proposed Spartan Lite spacecraft

Michael James Amato; Roger J. Thomas; Joseph M. Davila; Ronald S. Polidan

doi:10.1117/12.259704

25 November 1996 Conceptual design for a solar instrument on the proposed Spartan Lite spacecraft

Michael James Amato, Roger J. Thomas, Joseph M. Davila, Ronald S. Polidan

Proceedings Volume 2804, Missions to the Sun; (1996) https://doi.org/10.1117/12.259704
Event: SPIE's 1996 International Symposium on Optical Science, Engineering, and Instrumentation, 1996, Denver, CO, United States

Abstract

Spartan Lite is a proposed series of very low-cost spacecraft missions which offer potential flight opportunities for pointed solar experiments. Early versions will be launched as Space Shuttle attached payloads with the capability of being released for free flight. They would not be recovered, allowing useful lifetimes of six months to one year. An expendable launch vehicle option will be added later. The spacecraft is 3-axis stabilized with a cylindrical instrument cavity 100 cm long and 36 cm in diameter. If approved, the program would provide multiple launch opportunities during the upcoming solar maximum. A conceptual instrument design for a solar pointed mission on Spartan Lite is shown and discussed. The Extreme-Ultraviolet Normal Incidence Spectrograph will observe the solar spectrum between 290 and 466 A with high spatial and spectral resolutions. The large bandpass is due to the compact design, fitting two optical systems into the instrument cavity, each observing a different, but overlapping, wavelength range.

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Michael James Amato, Roger J. Thomas, Joseph M. Davila, and Ronald S. Polidan "Conceptual design for a solar instrument on the proposed Spartan Lite spacecraft", Proc. SPIE 2804, Missions to the Sun, (25 November 1996); https://doi.org/10.1117/12.259704

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KEYWORDS

Space operations

Electronics

Solar processes

Extreme ultraviolet

Satellites

Spectral resolution

Control systems

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