Retroreflector, Optical Bench, Instrument AIT BUS: Primary Structure, Tertiary structure, Antenna Boom, MGSE
LRI: High precission optics and highly stable optomechanics (CFRP, Zerodur, titanium) for beam shaping, routing and detection
BUS: highly stable CFRP Structures and a deployment mechanism.
As the outer segments and the complete boom fold out separately, there are only two degrees of freedom during each fold-out procedure; only three degrees of freedom in the case of spin-stabilized satellites. The design principle of the Double Star boom can be adapted to a variety of spinstabilized satellites. A concept for an active, springdriven deployment, using redundant deployment springs at the hinges is available for non-spinning satellites. Both versions can be realized either with one or two boom segments. The length of the deployed boom can be extended to more than four meters, depending on the dimensions of the spacecraft and on the mass to be deployed.
Solar generators, Coldgas propulsion system, Satellite primary structure
High resolution remote sensing satellite, resolution 2.5 m(PAN),5 m(MS)
Solar generators with deployment mechanisms and pyrodrive modules
High resolution earth observation for GIS, 0.7 m GSD
The patented deployment mechanisms of the solar generators are optimized for high torque, low friction and low shock loads