Auslegung und Inbetriebnahme der Sensorik, Aktorik und Avionik eines terrestrischen Landefahrzeugs

Abstract

For the simulation of landings on extraterrestrial orbs like the moon models of the landing vehicles, so called landing demonstrators, are built. This allows to test the sensor and actuator system before their implementation in the outer space at a minimum of costs. For using the sensor and the actuator system in the outer space special requirements have to be considered. For example actuators for the attitude control based on aerodynamical principles can not be used because of the non-existent atmosphere. Instead actuators on the basis of the recoil principle are used to ensure a fast reaction. This thesis describes the planning and implementing of the avionic of such a landing demonstrator. In a first step, based on the planning and selection of the components, the cold gas system which is used for the attitude control is investigated. Potential optimizations for its electrical activation are introduced, implemented and conclusively evaluated. Furthermore the development of an especially to the requirements of the landing demonstrator adapted hardware is described, which is used for the connection of the sensors to the bord computer and for the activation of the actuator system.