Orientation system of a spacecraft based on the inverse problems methodology

Аuthors

Chebakov E. V.¹, Nenarokomov A. V.²^*, A. , Reviznikov D. L.¹^**

1. Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia
2. ,

*e-mail: nenarokomovav@mai.ru
**e-mail: reviznikov@inbox.ru

Abstract

A reliable spacecraft orientation system is one of the main design tasks without which most missions cannot be performed. This circumstance imposes certain criteria on the development of the orientation system of vehicles in outer space. For a reliable control of the current orienta- tion a combined system of the orientation, sensor redundancy and backup systems are used. A combined system usually includes solar sensors and magnetometers for small satellites CubSat. The purpose of this paper is the analysis of the possibility to elaborate a backup or replacement orientation system for a spacecraft. This system uses radiation heat flux sensors based on the inverse problems methodology. It can be used for verification or correction of the angular orien- tation of the vehicle.

Unfortunately, in majority of practical situations the direct measurements of heat flux are problematic. These difficulties can be overcome with the use of some indirect thermal measu- rements combined with an inverse problem technique. The problem of retrieval of the angular orientation of a spacecraft demands to solve two inverse problems sequentially. The first one is the estimating of heat fluxes absorbed by spacecraft surface. The second one is the determining of angles of orientation based on the estimated values of radiative heat fluxes.

Keywords:

inverse problems, attitude control system, spacecraft, heat flux.

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