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Power-generation and propulsion complexes for spacecraft, universal space platforms (US) which combine a power unit and high- and low-thrust propulsion unions, make it possible to efficiently solve problems involved in creating satellite communication systems, environmental monitoring systems, industrial technology platforms, interorbital shuttles, etc. Electrical power consumed by prospective spacecraft designed for communication or environmental monitoring may be as high as 20-30 kW. Manufacturing of semiconductors and biological materials in space may require electrical power of 30-l00 kW in the coming decades. The power required to transport loads between orbits using ion-plasma jet engines will amount to tens to hundreds of kilowatts. For all these missions, nuclear power units have important advantages over solar photoelectric power units in their mass, size, cost, and performance characteristics. There is a good reason to consider the use of thermoelectric Nuclear Power Generators (NPG) for USPs due to their small bulk, their capacity for generating greatly increased power in the high-power mode during 15-20% of the total length of the mission, and minimal disturbance of the motion of the spacecraft.

In the report the principles of nuclear power and propulsion complex (NPPC) construction are presented. NPPC considered can ensure the time of spacecraft transfer to geostationary orbit (GSO) within 1 year under electric power level no less than 40 kW at prolonged nominal mode on GSO for spacecraft loads feeding. The main power and mass and dimension performances of such NPPC are summarized. Analysis of relationship between spacedraft mass, its mission payload and transfer time also and a number of main NPPC parameters is performed. The conclusion is made about considerable promises of the NPPC for creating future satellite multi‐purpose systems by using PROTON‐ and TITAN‐class launch vehicles.

One of the important future space technologies is the space production of semiconductive substances, composite materials, medical preparations and so on. Required for this electric power will equal 20–50 kW in nearest ten‐year period with further increasing to one hundred and more kilowatt. For similar production spacecrafts the application of thermionic space nuclear power (SNPS) can be perspective because these systems have a number of important advantages as compared with solar systems for spacecrafts of this type. The possible application concepts of thermionic SNPS with electric power 25 to 30 kW production spacecrafts are considered including the next versions: automatic loading and unloading of raw materials and products; loading and unloading executed by cosmonauts when SNPS being as a part of spacecraft and its demating from spacecraft during the process fulfillment; remote power transmission for power supply of production spacecrafts. It is shown that all considered versions thermionic SNPS can provide power supply of production spacecrafts with satisfying necessary operation requirements.

Control algorithms for ‘‘Topaz’’ type thermionic space nuclear power systems (SNPS) of second generation with electrical power up to 100 kW are considered. These algorithms are based on results obtained under creation of ‘‘Topaz’’ SNPS in ground and flight conditions and develop directly control principles of that SNPS. The most general demands for SNPS under start‐up and nominal modes taking into account of limitations necessary for security of prolonged lifetime are given. These demands must include the security of nuclear and radiation safety under possible emergency situations with SNPS and spacecraft. Control algorithms answering to these demands to a high degree are formulated. Therefore these algorithms can be considered as the most expedient for thermionic SNPS. In particular it is shown that duration of start‐up mode for thermionic SNPS will be equal from 1.5 to 2 hours. The specific values of parameters for these algorithms must be optimized in each concrete case.

The region of expedient using of SNPS with in‐core thermal thermionic reactor (ITR) is limited by electric power level of about 100 kWe under SNPS lifetime from 3 to 5 years. At the same time the reactor power may be forced from two to three times during the period of about half a year. The mathematical model of SNPS mass dependence on a degree of forcing is given. The results of calculation of payload masses and transfer times for transfer from low orbit to geostationary orbit for two thermal reactors having emission area 1.6 m2 and 2.5 m2 are given for different types of electrojets.