Editorial Note

For the last years one of the point of view heading in the field of the space applications turns into the advancement and the production of little (by mass and sizes) fake satellites for various purposes (communcation, navigaion, scientific) and vehicles of a light class rather modest and fit to launch these little satellites into a required circle. Specifically, there is an inclination to grow the production of little satellites-microsatellites with the mass of up to 100 kg and minisatellites with the mass of 100-500 kg. As the training shows, such s/c end up being fairly monetary while acknowledging low-scale research missions, diverse monitomg programs, etc.

Lower expenses on improvement, tests and produce, and furthermore, on dispatching into space, the likelihood to discharge a few s/c into the circle simultaneously and also a high dependability of orbital frameworks of various purposes comprising of an extraordinary number of satellites alludes to the upsides of little satellites in examination with customary huge size and costly s/c. Also, the expense of the assembling and dispatch of minisatellites doesn't surpass (7-10 million dollar) and of microsatellites (2-2.5 million dollar) with rather high unwavering quality and fast season of advancement (12-year and a half).

Design peculiarities of the power supply system of small satellites

The restrictions on sizes and mass dictate the certain technology of the development of systems and parts of small satellites. As a rule, small satellites are being manufactured in the form of polyhedron, prism or cylinder with stationary solar arrays (SA) mounted on the body or, with opening and then fixing solar panels if there are restrictions on sizes during the launch. The limitations on sizes and mass direct the specific innovation of the improvement of frameworks and parts of little satellites. When in doubt, little satellites are being produced as polyhedron, crystal or chamber with fixed sun based clusters (SA) mounted on the body or, with opening and afterward fixing sun based boards in case there are limitations on sizes during the dispatch. Silicon photocells with the thickness from 20 up to 200 jam and nickel-cadmium fixed cradle batteries are utilized on board most of modem little satellites. The uncontrolled construction with an immediate exchange of energy to the heap (the alleged "cushion structure") in view of the equal switch of SA, BB and the heap is normal to the force supply arrangement of little satellites. The yield voltage of such PSS is characterized by the scope of the BB voltage change with its charge and release, which can be adequately high. The control of the charge current and the security against the BB re-energize are accomplished, because of exchanging off or shunting of the entire SA or its part, more sometimes-because of the utilization of unique constant or discrete controllers. Little satellites are dispatched into low close Earth roundabout circles, center and high elliptic circles with a huge flightiness. The creators don't have information on the utilizing of little satellites in geostationary circles. The most wide-spread circles of little satellites are low roundabout close Earth circles (300-600 km) and center elliptic circles with a huge flightiness (the perigee is 250-600 km, the apogee-4000-6000 km or up to 200000 km). The circle tendency relies upon the addressed errand. The pinnacle force of the heap for most of microsatellites is in the scope of 50-75 Wt, the heap type is variable part with a consistent part (natural utilization of emotionally supportive networks). The utilization force of emotionally supportive networks is, as a typical, 10-15% of a pinnacle one.