In 2015, 10 years since the launch of the first technological nanosatellite TNS-0 N1 developed by JSC Russian Space Systems (JSC RSS) was marked. Despite the relatively simple structure and small size of TNS-0 N1 (total weight was less than 5 kg), it was successfully used as a platform for testing a number of new technologies and systems modern at that time: new principles to be applied for the purpose of rocket and space equipment development, single-point control of a satellite via space system GLOBALSTAR, new samples of Sun and horizon sensors, as well as certification of COSPAS-SARSAT beacons, etc. The paper presents JSC RSS experience in nanosatellites development, as well as concepts of a number of technologies and nanosatellite systems suitable for pilot projects implementation. Several problems of development of perspective technologies of space instrument manufacturing are discussed, the possibility of carrying out scientific research and technological works compensating the difference in levels of technological readiness of elements of the service subsystems and the target hardware is considered. It is proposed to perform an analysis of domestic technology service and on-bard radio systems for small spacecraft with the objective of achieving a qualitatively new level of implementation of design works. The necessity to restore the concept of scientific-technological research works and their inclusion in the Federal Space Program, and in other Federal target programs is declared. Results of the works on creation of various useful loadings intended for placement on the nanosatellites of CubeSat format are presented.

Classification and methods of constructing of small satellites clusters are presented. The two basic classes of the small spacecraft clusters are considered: the clusters with uniform distribution of the objective function between the set of satellites of the same type constituting the cluster (distributed spacecraft), and the clusters with spatially dispersed functional modules of a single spacecraft (fragmented spacecraft). In the both cases, the cluster elements are supposed to be connected to each other via radio and operate in concert. Deployment of small spacecraft clusters is anticipated to stimulate the market of light and ultra-light launch vehicles, to give an impetus to the development and improvement of innovative technologies, including molecular and atomic nanotechnologies.

Development of micro and nanosatellites aimed at solar-terrestrial connection research is considered. Recommendations formulated at special scientific session of Space Council of the Russian Academy of sciences devoted to possibilities of solar-terrestrial research using micro-, nano- and picosatellites and discussion of expanded cooperation between small spacecraft designers and manufacturers are presented. The feasibility of competitive scientific priorities for small spacecraft is emphasized as an important complement to Russian Federal Space Program. A review of relevant foreign CubeSat projects is carried out. General requirements and approaches to problems of small satellites research and development are formulated and several examples are analyzed. Ways to improve CubeSat development in Russia are proposed.

A complex of works carried out at Space Research Institute of the Russian Academy of Sciences in the field of fundamental space research is reviewed. Suggested solutions ensure the creation of complex scientific instruments, including an onboard acquisition system and a transmitter of information, and experimental micro-satellite platforms into orbit in the infrastructure of the Russian segment of the International space station (ISS). A ballistic scheme of increasing the height of the orbit of the transport cargo ship "Progress" after fulfilling the main task – delivery of cargo to the ISSР – is implemented. A ground infrastructure which uses the common online channels is created for information acquisition, processing, and providing further access to the data; the infrastructure allows serving other projects too.

A device and a method for constructing local vertical for nanospacecraft based on the sight of the horizon of the Earth in the visible wavelength range are proposed. The use of such a system on the nanosatellite is reported to allow determination of the local vertical direction with accuracy comparable with the accuracy of infrared local vertical detectors, and also to provide significant gains in mass and power consumption. The disadvantages of the system include the inability to determine the orientation on the shady part of the orbit, as well as flashing of the image when struck by sunlight in the frame. Presented results of numerical experiments demonstrate that the proposed system works in a wide range of orientation angles. A semi-natural experiment to determine the pitch angle by processing video images received from camera is carried out. Results of the experiment confirm that the accuracy of the developed system for constructing local vertical of spacecraft based on video processing is comparable to the precision provided by infrared detectors of local vertical.

The problem of providing aerodynamic stabilization of the nanosatellite is considered in the probabilistic formulation with respect to the angular movement of the nanosatellite after separation from the launch vehicle, in contrast to the known works in which this problem is solved in a deterministic formulation. The formulas for selection of the design parameters (stock, static stability, length, longitudinal moment of inertia) of aerodynamically stabilized nanosatellite are derived. At the low circular orbits the selected values of the parameters provide deviation of the longitudinal axis of the nanosatellite from the center of mass velocity vector less than acceptable with a given probability at the desired height under the given angular velocity errors of the separation system. On the base of numerical calculations, nomograms are created providing a simple and convenient selection of main design parameters values for CubeSat standard nanosatellites.

A system of power supply for nanosatellite of the SamSat family is developed, the basic quantitative and qualitative criteria for the system components selection and its tactical and technical characteristics are presented. Statistics of power consumption of typical onboard systems of SamSat nanosatellites including an onboard computer with various operation modes, transceiver, navigation receiver with motion control system, and camera is analyzed. Results of model calculations of energy consumption by the nanosatellite with the account for the work of all providing the service onboard systems are demonstrated. Characteristic of available commercially manufactured power system elements such as battery, solar panel and the system controller are reviewed briefly. The internal scheme of interaction of elements of power supply system controller with each other is discussed, and interaction between elements of the power supply system as a whole is considered.

The possibility of using groups of nanosatellites of CubeSat standard is considered. This approach provides obtaining simultaneous measurements at a number of spaced points and therefore allows a better understanding of complex non-linear processes in the ionosphere is important for fundamental and practical problems. The use of nonlinear dynamics methods (the fractal approach, the percolation theory) is proposed to describe the state of plasma in the auroral region when applied to processing of the data obtained from CubeSat nanosatellites. A plasma density sensor is developed to provide a measurement of the background values of the plasma density and its non-stationary fluctuations.

The variety of nanosatellites design schematics makes it difficult to compare them on the basis of separate parameters. In the proposed approach, a typical nanosatellite is described as the apparatus having the minimum required hardware set. General concept, structure, and composition of onboard system of a nanosatellite intended to solve a number of typical tasks are considered. An approach to the analysis of possible failures is proposed; the analysis uses the fault tree constructed on the base of the sub-problems of the spacecraft objective function.

Perspective schematic of realization of proto-flight approach in ground testing of nanosatellites is presented. The approach presupposes performing qualification flight tests with the single manufactured sample. Advantages and disadvantages of the proposed approach are discussed. To reduce the impact of identified disadvantages, it is proposed to use computational models of reliability available in a range of organizations of the rocket and space industry. Extension of the software base is supposed to be advisable in the frames of the of the future program "Creation of scientific-educational space system of the Union state", including the establishment of specialized ground-based functional modules to predict residual life and reliability of onboard systems of nanosatellites on the base of comprehensive tests results.

A classification of small spacecraft according to mass criterion is suggested. Domestic and foreign prototypes and analogs of small spacecraft launching systems are considered, their characteristics are analyzed. Small spacecraft launching system based on research rocket complex MR-30 is proposed. The research rocket complex MR-30 includes newly-developed research meteorological rocket MN-300, the flight level of the rocket being about 300 km. Scientific, technical and economic justifications and offers on modernization of a research rocket complex for its use for problems of small spacecraft launching into low orbits are provided. Requirements to a universal platform of the staff payload of the research rocket in view of minimization of technical means of the onboard equipment of small spacecraft for realization of research and local problems from space locate are substantiated. A plan of modernization of the standard block of MN-300 rocket equipment to use it as a platform for small spacecraft launching at minimal cost is developed. The mass characteristics and dimensions of the rocket and the platform for small spacecraft arrangement are presented. The scheme of rocket experiment for small spacecraft launching to a low orbit by means of the research rocket complex is presented.

A compact microprocessor launching system for nanosatellites with defined separation parameters (initial velocity, zenithal and azimuthal angles) on a given trajectory is presented. The system includes magnetic induction ejector, the mechanisms for orientation of the discharge apparatus in the zenithal and azimuthal directions, and a microprocessor control module. The separation system may be mounted on any delivery vehicle or on the Russian segment of the ISS.

The possibility to use orbital stage of launch vehicle as a platform for the piggy back launch of either single or cluster of nanosatellites is considered. The program of the nanosatellites separation from an orbital stage is anticipated to provide a basis for the safe movement of nanosatellites after their group deployment. A special attention is given to the fact that after separation of the main payload, the orbital stage obtains the angular velocity, the value and direction of which is not known. Results of statistical analysis have allowed developing of a method of selecting the nanosatellites separation parameters (the velocity and time of separation). The separated values of the parameters ensure exclusion of the possibility of nanosatellites collision and reduce the satellites dispersion by a predetermined distance. Results of statistical modeling carried out for nanosatellites launching from carrier rocket Soyuz orbital stage are presented.

The features of uncontrolled motion of aerodynamically stabilized nanosatellite relative to the center of mass in low circular orbit are considered. An expression for the ballistic coefficient averaged over the period of oscillations of the angle of attack is derived. The distribution function of the probability density and numerical characteristics of statistical distribution of the average ballistic coefficient of nanosatellite of CubeSat standard are obtained by numerical simulation method. Solution to the problem of determination of the moment of the nanosatellite separation from the transport-launch container and of features of lowering from the orbit is solved.