ABSTRACT
Large space structures can be classified the most completely stemming from their deployment principles. Nowadays, the mechanically deployed structures are widely introduced. Their chief advantage is a specified configuration accuracy achieved through stiffening the structure. A drawback of the mechanically deployed structures is a relatively low deployment coefficient (a ratio between the structure dimensions in stowed and deployed configurations) which limits their use in designing large objects. Materials used to fabricate antenna reflecting surfaces have to meet specific requirements dictated by structural features of foldable antennas and by a necessity of operation in space environment. The inflatable satellites-balloons have been also designed among the first, large, structureless systems deployed in space. A structure, similar to the last one, has been used in the US and French projects of solar sailing vehicles designed for missions to Mars. Thus, in 1990 a prototype solar sailing vehicle has been designed and subjected to ground tests in the USA.
