The development of a transformable space nuclear power system

Аuthors

Volchkov G. V.^1*, Vystavkin A. G.^1*, Maksimenko D. V.^2**

1. Company «Red Star», 1а, Elektrolitny proezd, Moscow, 115230, Russia
2. Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia

*e-mail: info@redstaratom.ru
**e-mail: DVMaksimenko@rosatom.ru

Abstract

The article is devoted to one of the stages of forming of a future space nuclear power system, in particular — the development of a transformable design of such a facility. Considering the need for development transformable system, the factors that lead to it are:

• the increased power of the reactor and increased resource of space nuclear power system (7 years and more) lead to increased flows of ionizing radiation on the instruments of the spacecraft;
• placing the required heat transfer surfaces cooler-radiator.

The first factor affects on the length of the disposal of the reactor from the instrumental compartment.
Reducing the influence of ionizing radiation fluxes is achieved by solving an optimization problem to minimize the total weight of the radiation protection system with Pushing system and communications.
The second factor is the result of the conversion of heat into electric power in the reactor-converte. Therefore, it is necessary to increase the area of the cooler-radiator.
It is proposed to increase reliability of the cooler-radiator by using of high-temperature thermal tube in the structure.
The basic complexities of creating a transformable system and the requirements for it are shown.
This brief analysis of possible ways for structure transformation leads to the selection of the optimal alternative.
The selected convertible system, which is called «rope», is represented, principle of its operation at the space nuclear power system is shown.
The option of creating a reliable hydraulic connection for the possibility of transfer of the coolant in the chosen system is offered.
The need for calculations for ground layout for the tests, which imposes additional conditions in the mathematical description of the process, is indicated.
Represented calculations include:

• structural analysis of the mechanism for the determination of the driving link;
• kinematic analysis to determine the speed of feature points;
• dynamic analysis to determine the reduced forces and torques including the action of the gravity forces.

The results of calculations and ground tests of the model actuator for driving link are shown.
The conclusions indicate the direction of further works on the creation of the transformable systems for the second generation space nuclear power plants.

Keywords:

space nuclear power systems, transformable system, system of deployment, heat pipes

References

1. Andreev P.V., Galkin A.Ya., Eremin A.G. Patent RU 2225809, 04.03.2002.
2. Eremin A.G., Shitts E.N., Maksimenko D.V. Patent RU 2474893, 10.02.2013.
3. Artobolevskii I.I. Teoriya mekhanizmov i mashin (Theory of Mechanisms and Machines), Moscow, Nauka, 1988, 630 p.
4. NTTs Privodnaya Tekhnika, katalog produktsii, http://www.privod.ru/products/index.htm