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DLR-TUBSAT: a microsatellite for interactive Earth observation
Abstract
DLR-TUBSAT is a joint project of the Institute of Aerospace at the Technical University of Berlin (TUB) and the German Aerospace Center (DLR). The microsatellite was launched on 26 May 1999 with the Indian Polar Spacecraft Launch Vehicle (PSLV) together with KITSAT-3 and the primary payload IRS-P4. The test satellite was designed for interactive earth observation where the target is not clearly identified in advance, a search action is involved or a target has to be visually followed for a while. This paper will describe the mission objective, the final configuration of the satellite, the ground segment and the operations. Finally the achievements of the first year in orbit and the lessons learned will be presented.
... The microsatellite parameters from the TU Berlin heritage shown in Table 3 are from DLR-TUBSAT and MAROC-TUBSAT, and in Table 4 are from LAPAN-TUBSAT and two Indonesian built satellites, that is, LAPAN-ORARI and LAPAN-IPB. Additionally, the four satellite structure drawings are presented in Figures 4 and 5 [24][25][26][27][28][29] for the comparison of structural design. ...
Microsatellite has been considered as disruptive technologies in satellite engineering. Its development cost and time provide advantages for new kind of Earth observations, telecommunications, and science missions. The increasing trend of microsatellite launches and operations means that the approach was so successful that it could create funding sustainability. Major contributing factors of its success were due to the system design of the microsatellites. This chapter discusses two microsatellite system design approaches, namely Technical University of Berlin heritage and University of Surrey heritage. Both Universities provide approaches for system design and build of microsatellite systems. The design approaches are being compared along with lessons learned. The choices of microsatellites to be compared in this chapter will be those that are manufactured about the same time such that the technology compared is mostly the same and flown in-orbit. The chapter shows that the differences between the two system design approaches are on the choice of main computer and associated link configuration and in the attitude control modes. Another major different is in the satellites’ structure design. For some satellite’s components, incoming technologies have made the design choices from the two schools of thoughts converged.
... It can be considered as a microsatellite platform projects from 10 kg up to 100 kg according to the rule, but considering what expressed in Jie, Yanbin, Shihong and Lijun, (2013) we can take into account and include satellites up to 200 kg as micro-satellites. [3], [5], [8], [9], [10], [14], [12], [15], [16], [17] In Table I can be seen that different developed and developing countries are using micro-satellites, obtaining excellent results. This kind of platforms allows to install one or more different payloads with diverse purposes, giving to each one the conditions required. ...
The Bolivarian Republic of Venezuela has made developments in the space field during the past decade and on, placing to successfully in orbit two satellites on the last 7 years, one in the Geostationary Orbit (GEO) and another in the Sun-Synchronous Orbit (SSO) in order to the peaceful use of outer-space resources. Currently the Bolivarian Agency for Space Activities (ABAE, for its acronym in Spanish) is finalizing to build a research and development center for design, assembly and test of small satellites. It is conducted an investigation over the relevance, feasibility and scope of the development of a novel platform within a Micro-Satellite dimensions and weights standard. This research focuses on the country capabilities in terms of its technological development, the average cost of such kind of satellites and the Venezuelan potentially growth in this area, furthermore it explores results of space agencies around the world using such platforms and the scope of its missions proposed. As a result of this research is presented a conceptual and systematic proposal of a new Venezuelan micro-satellite platform. It suggests novel ways to develop this new platform and its possible applications that will allow to expand new potentials. The Development of a Bolivarian Republic of Venezuelan’s satellite platform, will allows the country to promote its own technological advances, and moreover to test new technologies and configurations.
Safety is a crucial requirement of On-Board Computer (OBC) design of a satellite, especially for the new type OBC--takes FPGA as central processor. Upon that this paper proposes a plan of FPGA OBC design and adds hierarchical fault tolerant concept to enhance the reliability of the OBC system. The fault tolerant architecture can be divided into three hierarchic ranks, containing single-CPU reconfiguration, component unit transfer and dual-CPU subrogation. One of the above fault manage mode will be chosen to deal with problems according to error situation in-orbit. In the worst cases, all three modes may be used. The last part of the paper gives the functional verification approach under development for the hierarchical fault tolerant OBC design.
The use of low cost micro-satellite platform for surveillance and remote sensing mission faces two main problems. Those are the narrow swath due to constraint in the use of swivel mirror for the scanning-type payload and the very limiting power generation due to the constraint of limited solar panel area due to the complexity of deployable system. The narrow swath constraint made the revisit time become very high especially in the equatorial region and the power generation limit create power deficit in for the mission. LAPAN-TUBSAT offers solutions for such problems by its ability of pointing the satellite, and therefore the payload, off-nadir, and by its momentum-biased hibernation mode, in which surplus power is generated. The paper discusses the mission development of the satellite as well as the detail of its subsystems.
There is an increasing need for Earth Observation (EO) missions to meet the information requirements in connection with Global Change Studies. Small and cost-effective missions are powerful tools to flexibly react to information requirements with space-borne solutions. Small satellite missions can be conducted relatively quickly and inexpensively by using commercial off-the-shelf-technologies, or they can be enhanced by using advanced technologies. A new class of advanced small satellites, including autonomously operating “intelligent” satellites may be created, opening new fields of application. The increasing number of small satellites and their applications drive developments in the fields of small launchers, small ground station networks, cost-effective data distribution methods, and cost-effective management and quality assurance procedures. There are many advantages of small satellite missions, like more frequent mission opportunities, a faster return of data, larger variety of missions, more rapid expansion of the technical and/or scientific knowledge base, greater involvement of small industry, feasibility by universities and others.This paper deals with general trends in the field of small satellite missions for Earth observation. Special attention is given to the potential of spatial, spectral, and temporal resolution of small satellite based systems. Examples show small satellites offer also the unique possibility to install affordable constellations to provide good daily coverage of the globe and/or allow us to observe dynamic phenomena.The facts and examples given in this paper lead to the conclusion: Small satellites are already powerful tools for monitoring global, regional and local phenomena. In the future, their application spectrum will even broaden based on the ongoing development in many areas of technology and observation techniques.
Earth Observation with TUBSAT-C
- Renner
- Udo
Renner, Udo. Earth Observation with TUBSAT-C. 4th International Symposium, 1998.
Thys; du Plessis, Francois. The SUNSAT Micro Satellite Program
- Mostert
- Sias
- Cronje
Mostert, Sias; Cronje, Thys; du Plessis, Francois. The SUNSAT Micro Satellite Program. 4th International Symposium, 1998.