Session
Technical Session XI: Mission Lessons II
Abstract
The off-the-shelf availability of a large variety of Cubesat components from different manufacturers enables building-block-like configuration of Cubesat systems. Is it possible to utilize these components to build a nano satellite for scientific payloads? The German Aerospace Center (DLR) internal engineering group Clavis, with the goal of developing a flexible, modular nano satellite platform, was confronted with implementing their design into the AISat mission. The challenges, solutions and lessons learned is what this paper shall transport. From the early steps in designing a satellite bus for DLR internal small payloads to adapting this concept to a real payload and implementing a lot of experience was gained with respect to cost of modularity, interdependency of commercially available components from different manufacturers, verification, and integration. The initial Clavis concept was intended to be flexible with respect to the payload it may support, to be modular in order to provide for different mission scenarios, and to mainly consist of standardized components which enable a mission life time of up to one year (and possibly beyond). With the adoption of the AISat payload the conceptual design had to be adapted to the specific requirements of the payload since it was already defined.
Experiences in Combining Cubesat Hardware and Commercial Components from Different Manufacturers in Order to Build the Nano Satellite AISat/Clavis-1
The off-the-shelf availability of a large variety of Cubesat components from different manufacturers enables building-block-like configuration of Cubesat systems. Is it possible to utilize these components to build a nano satellite for scientific payloads? The German Aerospace Center (DLR) internal engineering group Clavis, with the goal of developing a flexible, modular nano satellite platform, was confronted with implementing their design into the AISat mission. The challenges, solutions and lessons learned is what this paper shall transport. From the early steps in designing a satellite bus for DLR internal small payloads to adapting this concept to a real payload and implementing a lot of experience was gained with respect to cost of modularity, interdependency of commercially available components from different manufacturers, verification, and integration. The initial Clavis concept was intended to be flexible with respect to the payload it may support, to be modular in order to provide for different mission scenarios, and to mainly consist of standardized components which enable a mission life time of up to one year (and possibly beyond). With the adoption of the AISat payload the conceptual design had to be adapted to the specific requirements of the payload since it was already defined.
