What is GISS?

4.1 Analysis of requirements and proposals for the creation and serial maintenance of the GISS orbital constellation

The preliminary estimate of the energy and mass parameters of the GISS spacecraft is given in Tables 4.1 and 4.2.

Table 4.1. L/X Onboard SC. Summary of mass, consumption and heat release

Equipment	Number of pieces			Weight, kg				Power Cons. W		Thermal. W
	Install.	Active		Single			Summ	Single	Summ	Single	Summ
L-band PRTD module	1	1		188,5			188,5	6505	6505	4301	4301
X-band RRv module	1	1		320			320	4800	4800	4800	4800
Feeder Lain module	1	1		148,3			148,3	1293	1293	973	973
Multi-functional on-Board Digital Platform (MBDP)	1	1		300			300	3000	3000	3000	3000
ISL module	4	4		25			100	40	160	40	160
Total modules							1056,8		15758		13234
Other (cables and waveguides) 10%							105,68
Total Onboard SC							1162,5		15758		13234
Table 4.2. X/L Onboard SC. Summary of mass, consumption and heat release
Equipment	Number of pieces				Weight, kg			Power Con. W		Thermal. W
	Install		Active		Single	Summ.		Single	Summ.	Single	Summ.
X-band PRTD module	1		1		238	238		6048	6048	4032	4032
L-band RRv module	1		1		247,5	247,5		675	675	675	675
Feeder Lain module	1		1		148,3	148,3		1293	1293	973	973
MBDP	1		1		300	300		3000	3000	3000	3000
ISL module	4		4		25	100		40	160	40	160
Total modules						1033,8			11176		8840
Other (cables and waveguides) 10%						103,38
Total Onboard SC						1137,2			11176		8840

Table 4.1 and 4.2, the assessment of the energy and mass characteristics of the onboard repeaters was carried out taking into account the use of APAP with large numbers of antenna elements having a directivity (Gi) of 3 dB. The possible use of APAA with increased values of Gi≈9 dB of each AE will provide a reduction in the mass and power consumption of onboard special complexes (repeaters) on spacecraft of both types up to 1 ton and 12 kW. However, the mass of each GISS spacecraft, taking into account the main contribution to this indicator of the onboard power supply system, will remain about 3 tons. A factor of 3 between the weight of the repeater and the weight of the communications satellite is a common factor. For the simultaneous launch of 12, 15, 18 or 24 spacecraft into the orbital plane, GISS requires a launch vehicle of the class developed under the “lunar programs” in the USA, Russia, China and India, capable of placing a payload into a near-earth orbit 60÷90 tons. On their basis, a modification of the launch vehicle with a fairing for the cluster launch of the corresponding number of GISS spacecraft should be created – no less than 12 and no more than 24. The design results Since we regard GISS as an international system, and the United States, Russia, China and India are interested in creating and ensuring the development of the space industry and the serial production of such launch vehicles, for these countries the task of manufacturing one launch vehicle per year is not excessive. Even in the worst case, when 12 spacecraft are launched with one launch vehicle, four orbital planes in the constellation will be created in the irst year, eight in the second year, and twelve in the third year, which will already provide almost continuous control of the near-Earth space, excluding the equatorial regions. In the next three years, the orbital constellation in the worst case will reach 288 spacecraft with 24 spacecraft in each of the planes. In fact, there are always three more options for its creation than there are participants in the dispute over its design. If we consider as a uaranteed period of active existence of each of the GISS spacecraft in an orbit with an altitude of about 800 km in six years, then the launch cycle is repeated with the release rate of one launch vehicle per year for each country. The rate of serial production of repeaters with processing on board and spacecraft of two modifications – 48 spacecraft GISS per year. If it is possible to launch 24 spacecraft (72 tons of payload), then one launch vehicle will be required in two years of production. A good science fiction task for the future generation of developers – after the launch of a new group of spacecraft into the orbital plane, on the next orbital coil to assemble all the old spacecraft on a harpoon and drown together with the launch vehicle in the Pacific Ocean in the Mariana Trench.