Loading [a11y]/accessibility-menu.js
LED-based attitude reconstruction and back-up light communication: experimental applications for the LEDSAT CubeSat | IEEE Conference Publication | IEEE Xplore

LED-based attitude reconstruction and back-up light communication: experimental applications for the LEDSAT CubeSat


Abstract:

Optical observations are intensively applied to space debris monitoring for the achievement of orbit determination and for gathering information on their attitude motion,...Show More

Abstract:

Optical observations are intensively applied to space debris monitoring for the achievement of orbit determination and for gathering information on their attitude motion, even if constrained by light conditions. Light Emitting Diodes (LEDs) installed on the external surfaces of a satellite could increase the visibility interval to the whole eclipse time. LEDSAT (LED-based small SATellite) is a 1-Unit CubeSat aimed at demonstrating the effectiveness of LEDs for the improvement of space debris optical monitoring algorithms. The LEDSAT experimental mode includes flashing patterns that will allow the CubeSat attitude reconstruction and the testing of a back-up light-based communication method. This paper will describe the features of the LEDSAT experimental mode, by describing the needed measurements for achieving the satellite LED-based attitude reconstruction and the features of the back-up LED communication.
Date of Conference: 19-21 June 2019
Date Added to IEEE Xplore: 17 October 2019
ISBN Information:

ISSN Information:

Conference Location: Turin, Italy

I. Introduction

Space debris monitoring is usually performed by a variety of different techniques and instrumentation, such as radar and laser ranging and optical observations by means of groundbased telescopes. On this purpose, optical observation is usually exploited for improving the precision of satellite orbit determination. The observations can be scheduled for surveillance tasks, in order to identify and track new orbital debris, or for tracking known objects and improving their position estimation. The orbit and position estimation of a satellite or a debris is achieved by performing astrometric measurements on the images acquired by the telescopes [1]. The data analysis mainly relies on the determination of the observed object celestial coordinates. These are determined by recognizing the background stellar field in the images by comparison with stellar catalogues [2]. The integration of a larger multiplicity of data (e.g. acquired with a telescope network dislocated over a larger area, or by a single telescope over a longer observation campaign) allow to improve the orbit determination of the tracked orbital debris.

Contact IEEE to Subscribe

References

References is not available for this document.