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Technology-Driven Design of a Scalable Small Satellite Platform

Dannemann, Frank and Jetzschmann, Michael (2016) Technology-Driven Design of a Scalable Small Satellite Platform. In: Proceedings of 4S Symposium 2016. 4S Symposium, 30. Mai - 3. Juni 2016, Malta.

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Official URL: http://www.congrexprojects.com/4S2016


This paper presents a new approach in satellite platform design. While traditionally the design of technology demonstration- or scientific missions is driven by the requirements of the payload, the focus of our approach lies on using avionics technologies developed by the German Aerospace Center (DLR) as the core components of the satellite bus. These components will then drive the design of the Small Satellite Technology Platform, in short S2TEP. This methodology change towards a technology-driven approach results from the long-term goals identified for future in-house space missions, as there are a cost effective platform design, a shorter development time, short-term design adaptions and the ability to carry out own research and development activities which lead to a deeper design understanding. The accomplishment of these goals also requires a change within the satellite's model philosophy, a new development process and a flexible and highly autonomous ground segment. The first instantiation of the S2TEP platform will be a satellite in the micro-satellite class. During this project the needed avionics technologies will be further developed up to a Technology Readiness Level (TRL) mature enough to be integrated in the flight model for the first mission. By separating mission- and bus-development it is ensured that the payload does not influence the bus design too much. Though, a reference mission will be designed to set an interface to and an envelope for possible payloads. The DLR avionics technologies to be used for the S2TEP core avionics consist of the Onboard Computer (OBC), the Power Condition and Distribution Unit (PCDU) and the Transceiver-unit. All of these components are designed taking scalability into account - concentrating not only on performance parameters but also on quality aspects, like the migration path for all used electronic parts towards space qualification. Taking the OBC as an example, the scalability up to the next higher class of satellites will be presented within this paper.

Item URL in elib:https://elib.dlr.de/104988/
Document Type:Conference or Workshop Item (Poster)
Title:Technology-Driven Design of a Scalable Small Satellite Platform
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Dannemann, FrankUNSPECIFIEDhttps://orcid.org/0000-0002-0636-5866138661056
Journal or Publication Title:Proceedings of 4S Symposium 2016
Refereed publication:No
Open Access:Yes
Gold Open Access:No
In ISI Web of Science:No
Series Name:4S Symposium
Keywords:satellite design, platform design, scalability, technology-driven
Event Title:4S Symposium
Event Location:Malta
Event Type:international Conference
Event Dates:30. Mai - 3. Juni 2016
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Space
HGF - Program Themes:Space System Technology
DLR - Research area:Raumfahrt
DLR - Program:R SY - Space System Technology
DLR - Research theme (Project):R - Small Sat Kleinsatelliten (old)
Location: Bremen
Institutes and Institutions:Institute of Space Systems > Avionics Systems
Deposited By: Dannemann, Dr. Frank
Deposited On:02 Aug 2016 11:52
Last Modified:14 Jul 2023 11:37

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