Technology demonstration by the BIRD-mission

• Published in: Acta astronautica 2005, Vol.56 (1), p.57-63
• Main Authors: Brieß, K., Bärwald, W., Gill, E., Kayal, H., Montenbruck, O., Montenegro, S., Halle, W., Skrbek, W., Studemund, H., Terzibaschian, T., Venus, H.
• Format: Article
• Language: English
• ISSN: 0094-5765; 1879-2030
• DOI: 10.1016/j.actaastro.2004.09.041

Small satellites have to meet a big challenge: to answer high-performance requirements by means of small equipment and especially of small budgets. Out of all aspects the cost aspect is one of the most important driver for small satellite missions. To keep the costs within the low-budget frame (in comparison to big missions) the demonstration of new and not space-qualified technologies for the spacecraft is one key point in fulfilling high-performance mission requirements. Taking this into account the German DLR micro-satellite mission BIRD (Bi-spectral Infra-Red Detection) has to demonstrate a high-performance capability of spacecraft bus by using and testing new technologies basing on a mixed parts and components qualification level. The basic approach for accomplishing high-performance capability for scientific mission objectives under low-budget constraints is characterized by using • state-of-the-art technologies, • a mixed strategy in the definition of the quality level of the EEE parts and components, • a tailored quality management system according to ISO 9000 and ECSS, • a risk management system, • extensive redundancy strategies, • extensive tests especially on system level, • large designs margins (over-design), • robust design principles. The BIRD-mission is dedicated to the remote sensing of hot spot events like vegetation fires, coal seam fires or active volcanoes from space and to the space demonstration of new technologies. For these objectives a lot of new small satellite technologies and a new generation of cooled infrared array sensors suitable for small satellite missions are developed to fulfil the high scientific requirements of the mission. Some basic features of the BIRD spacecraft bus are • compact micro satellite structure with high mechanical stability and stiffness, • envelope qualification for several launchers, • cubic shape in launch configuration with dimensions of about 620 × 620 × 550 mm 3 and variable launcher interface, • mass ratio bus:payload = 62 kg:30 kg, • high peak power of 200 W at 10–20 min, and average power 60 W, • advanced thermal control system with radiators, heat pipes, MLI, temperature sensors and contingency heaters, • new developed high-performance spacecraft bus computer with integrated latch-up protection and error detection and correction system, • three-axis stabilization of the spacecraft by an attitude control system in state space representation, • integrating the payload platform with its structu