Solar collectors support structure

Considering an outline design as suggested by Little (2011) (see Section 19.4.1), the collected electrical energy from solar collectors supported by satellite no. 1 at geostationary orbit would be beamed to Earth by laser onto satellite no. 2 positioned some 20 kilometres above the Earth. Satellite no. 2 would support the equipment to transform the laser to microwaves which would be beamed to a ground receiver. Ideally both satellites 1 and 2 would be fabricated from a polymer/libre composite skeletal space structure to support the collectors and equipment. Figure 19.9 illustrates the components that would be required for the SBSP system. 

The interfaces of importance in SECS are the solid/solid (S/S), solid/gas (S/G), and solid/ liquid (S/L) (4). The area-intensive nature of SECS components was established in the previous section. The major problem is collecting solar energy at a cost that is competitive with other energy forms. Thus, low initial cost is required for the materials, support structures, and production processes in the SECS of interest in Fig. 1 (6). This requires, for example, using thin films in mirrors, in photovoltaic systems, for antireflection coatings on windows, for passive collection, etc. in addition, these films must be made from inexpensive, durable, and easily processed materials (5). Inexpensive long-life materials in flat-plate collectors and durable, stable absorber coatings are also necessary. 

Balance of System - In a solar energy system, refers to all components other than the collector. In terms of costs, it includes design costs, land, site preparation, system installation, support structures, power conditioning, operation and maintenance costs, indirect storage, and related costs. 

It is advisable to refer to the first paragraph of the Appendix (Section 10.12) before reading the following sections. The following discussion refers only to Satellite 1 (Little, 2011) positioned at GEO as discussed in the Appendix. The support structures for the solar collectors and... 

The two types of support structures for the solar collectors and equipment that will be considered are the rigid deployable skeletal (RDS) structure and the rigidised inflatable flexible continuum (RIFC) structure both types of structure need to be lightweight and rigid and, in the case of the skeletal structure, high modulus composite materials would be used. In addition, the structures must be able to be folded to a minimum volume to be placed in the cargo bay of the Launch Vehicle, launched and deployed at LEO, and then taken to GEO by space tug,Wingo (2004). 

The space frame would be permanently placed at GEO at an altitude of 36 000 km Earth, but would remain in LEO for a short length of time whilst the support structure was deployed and the collectors and equipment were fixed to it by extra-vehicular activity (EVA). At GEO, the whole structure is exposed to a different loading regime from that of LEO. Although safe from AO attack at GEO, the structures would be exposed to the effects of solar... 

Rigid deployable skeleton support structure (RDSS) for solar collectors and equipment... 

Rigidised inflatable flexible continuum (RIFC) support structure for solar collectors and... 

The rigid deployable skeletal structure to support the solar collectors... 

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