Space flight is one the most bright exploratory ideas of the mankind. Such outstanding events of the 20th century as launch of the first man-made Earth satellite made on October 4, 1957 and the first manned space flight of Yuriy Gagarin made on April 12, 1961 significantly influenced activities of Yuzhnoye State Design Office.

First spacecraft launches opened new capabilities for space exploration bringing information about physical and chemical parameters of the upper atmosphere, parameters of the magnetic field of the Earth, ways of interaction between charged particles and magnetic field of the Earth, physics of the space rays and other information, including information required for manned flights preparation. However, a significant number of priority experiments could not be implemented using first spacecraft; major part of the obtained information needed updating, comparison and checkout.

This factor determined the need in regular spacecraft launches for both regular study of the space environment and statistical data collection and establishment of special systems operated on a permanent long-term basis (Sun-observation, radiation safety, ionosphere sounding systems, systems for detection of high-altitude nuclear explosion, etc.). Creation of new efficient launch systems and development of spacecraft corresponding to the class of such launch systems and covering the wide scope of scientific and application tasks within limited timing was required to implement the intended.

In these circumstances Yuzhnoye came with initiative of creation of a light launch vehicle 6301 based on P-12 strategic ballistic missile. Development of DS-1 (Dniepropetrovsk satellite - 1) spacecraft was initiated to support in-flight testing of 6301 system.

Implementation of this initiative brought Yuzhnoye, being the second launch system designer in the country, to the priority positions in the space activities.

The first space-specialized divisions were organized in Yuzhnoye in early 1961.

Spacecraft manufacture was established at Yuzhny Machine-building Plant.

The team of OKB-1 rendered significant practical assistance in spacecraft development to Yuzhnoye specialists.

Development of launch vehicle 6301 and DS-1 spacecraft turned to its flight-test phase in September 1961.

The first launch of DS-1 spacecraft took place on October 27, 1961 ending in a failure due to launch vehicle malfunction.

The launch of DS-1 spacecraft #2 took place on December 21, 1961. The spacecraft made a ballistic cruise due to early cutoff of 2nd stage engine of the launch vehicle.

A decision was made after two unsuccessful launches to create a simplified DS-2 spacecraft based on the equipment and structural elements of DS-1 spacecraft. DS-2 spacecraft #1 was launched onboard launch vehicle 6301 #6 ЛК and delivered to the orbit artificial Earth satellite on March 16, 1962. The first Yuzhnoye-designed spacecraft being the firstling of the Soviet Cosmos space exploration program started its operation. Official identification Cosmos-1 was assigned to the spacecraft.

Since then, every year on March 16 Yuzhnoye celebrates the birthday of its Space Division. The Design Office became a priority spacecraft and system developer for such areas of space activity as fundamental scientific researches in near-Earth space, study of the Sun and Sun-Earth relations, oceanographic studies, Earth observation and special systems debugging for Defense Ministry of the USSR. Several spacecraft generations were created for each of these fields and were successfully used for solution of different tasks (some spacecraft are still being operated).

Over the past 40 years of spacecraft development, Yuzhnoye State Design Office, in cooperation with Subcontractors, designed more than 70 types of spacecraft, commissioned 15 world-class space systems, launched into the orbit about 400 spacecraft developed by Yuzhnoye.

Achievements of the Company include, in particular:
- world-pioneer development and implementation of the principle of universal spacecraft platforms as the base for specialized spacecraft created by equipping of the universal platform with special-purpose equipment;
- application on Yuzhnoye-designed spacecraft (among the first in the former USSR) of gravity-magnetic stabilization systems of different classes and estro-television systems for precision indication of the spacecraft attitude parameters;
- development and implementation of electrical power supply systems for spacecraft of different types using original solutions in the field of solar array sectioning;
- development and implementation of high-efficiency active and passive spacecraft thermostating systems, gas-jet and liquid-propellant propulsions for spacecraft attitude control systems;
- development and implementation of a wide range of efficient antenna systems for launch vehicles and spacecraft, resolution of the problem of permanent radio-link with combat missiles flying in the descending segment of the orbit.

The Company has a great experience in international cooperation for space researches. Joint projects were run with the countries of Eastern Europe, France, India and Sweden. 22 automated Earth satellites were manufactured at Yuzhny Machine-building Plant and delivered to the orbit under Intercosmos-1 program with priority results obtained in a series of research areas.

THE SPACECRAFT OF SEARCH PERIOD OF WORK. DESCRIPTION OF THE PERIOD

The most important task to be solved concurrently with the work on creation of 63C1 launcher and DC-1 spacecraft was determination (initial and theoretical) of potential fields of effective application of space hardware and formation of the plan of research and development and experimental work in field conditions directed to confirmation of calculated assumptions, working out of conclusions on the possibility of creating operational space systems and requirements to them.
In December 1959, the Interdepartmental Scientific Technical Board on space Research at the USSR Academy of Science was established with academician M.V.Keldysh at the head that was charged with the development of thematic plans of creating the spacecraft, issue of main technical tasks, scientific - technical coordination of the work on investigation of upper atmosphere and space, organization of international cooperation in space research.
M.K. Yangel was appointed a member of the Presidium of the Interdepartmental Scientific Technical Board on Space Research.
In the field of applied tasks, Research Institute NII-4 of Defense Ministry was charged with similar tasks.

By joint efforts of the Academy of Science and Defensw Ministry of the USSR, the program of the first series of launches of 63C1 launch vehicle was prepared and approved in August 1960. The program included the tasks for development and launch of DC-A1, DC-P1, DC-K8 spacecraft which besides research experiments carried military - applied experiments. The first series of 63C1 LV launches implied also putting into orbit 1MC, 2MC research spacecraft developed by OKB-1.
By December 1961, the design documentation for DC-A1, DC-P1, DC-K8 spacecraft was already issued. In June 1962, the first of the above spacecraft - DC-P1 was injected into orbit and in February 1963, the 63C1 LV launches of the first series were completed.
The program of the second series of 63C1 LV launches approved in July 1962, included, besides the known spacecraft DC-A1 and DC-P1, the newly developed research spacecraft DC-MT and DC-MG and Omega-1 SC developed by the specialists of All-Union Research Institute of Electrical Mechanics to try-out an electro-wheel orientation system. The second launch of DC-2 spacecraft was planned to try-out the lift-off from a new silo launcher of 63C1 LV.
The first 63C1 LV launch of the second series was in May 1963, the last - in July 1965 (DC-A1 spacecraft).
The search period of space investigation was completed with the launch of DC-MO small spacecraft with optical equipment in March 1967 which was the last launch in the program of the third series of 63C1 LV launches.
In all, 15 successful launches of the spacecraft of eight types were conducted.
The DC-1, DC-A1, DC-K8, DC-P1, DC-MG, DC-MT spacecraft were made with maximal possible use of common design scheme and equipment. The sealed casing of the spacecraft consists of two semi-spherical bottoms and a cylindrical distance piece of 800 mm diameter. Inside the casing filled with nitrogen, the trusses are accommodated on which the units of chemical batteries, radio technical equipment and electronic units of research equipment are located. The sensors of research equipment are installed on the cylindrical part of casing and on the upper bottom.
The SC onboard support equipment mass assembled as a rule, of series - produced space instruments and devices. The basic elements of spacecraft equipment were the BKRL-E command radio line equipment developed by NII-648, Tral-MCD radio telemetry system and Rubin-1D orbit radio control system developed by Experimental Design Bureau of Moscow Institute of Energy, the chemical power sources developed by All-Union Research Institute of Current Sources.
The Thermal control system is built on the basis of two ventilators, a control unit with temperature sensors and a radiation surface. The DC-MT and DC-MG spacecraft use an offset heat exchanger with radiation surface.
The antenna - feeder devices of the spacecraft contain 4 rod aerials, 5 ribbon aerials, and one slot aerial.
The length of cylindrical part of the casing is not constant and varies for different spacecraft depending on the composition and size of electronic units of research equipment. The casing of DC-2 spacecraft is assembled without the use of the cylindrical distance piece.
All the spacecraft of search type were developed without the use of attitude control system. The exception is DC-MO spacecraft known in literature as "space arrow" which used a spacecraft aero gyroscopic attitude control system for the first time in world's practice. The characteristic feature of the spacecraft's appearance is an extended skirt of aero stabilizer.
The DC-P1 spacecraft used a solar power plant for the first time in OKB-586 practice. A battery of photo converters is made in the form of dodecahedron rigidly connected with a sealed container.
The mass of the first spacecraft was within the range of 47 [DC-2] to 321 kg [DC-MO], the mass of research equipment was between 4.5 kg and 44 kg.
The active lifetime of a spacecraft in orbit (excluding DC-P1 SC) was determined by the capabilities of chemical power sources and was 10…15 days.
The control of spacecraft functioning and reception of scientific data were effected by means of the ground command-and-measurement complex of the USSR Defense Ministry.
The work performed in this period allowed to not only form the target-oriented directions of further development of space engineering at the enterprises and in the USSR as a whole but also to prepare new economical decisions in the field of design-and-technology base, to approach right up to the idea of a unified spacecraft.

Unified Small Spacecraft
Creation Concept

Positive results obtained from the first activities that confirmed viability of the remote methods for solution of scientific and application tasks inspired different organizations for placing a great number of applications for creation of new spacecraft and their equipping with equipment of different special application thus resulting in the need to expand the field of research and design activities.

Establishment of a special complex of theoretical departments was the next organizational step in expansion of the field of activity in ОКБ-586 taken as a result of such need. At the same time, analysis of the received applications showed that many proposals might lead to future trend for their development into separate sectors of spacecraft development that a single company could not run.

A decision was made to transfer some projects together with design documentation developed by OKБ-586 to other companies: State Scientific and Research Institute of Electromechanics (April 1962), OKБ-10 (August 1962) and Branch #3 of the Central Design Office for power machinery (June 1967). These companies are working successfully on further development of the projects initiated in OKБ-586. However, the remaining scope of work was so extensive that its accomplishment could be possible only provided that drastic steps on decrease of time and cost of spacecraft development and manufacture are taken. Decision-making on creation of the first in the world series of unified spacecraft under the Statement of Work from the Academy of Sciences of the USSR was an important milestone on this way. Independence of support systems, spacecraft structure and on-board equipment control algorithm from specific scientific task was selected, based on the summarized experience in spacecraft development, manufacture and operation, as the main unification principle that gave rise to serial production of spacecraft and their components, thus expanding the scope of scientific researches in near-Earth space.

It was obvious that creation of one unified type of spacecraft that could solve any scientific was impossible due to variety of research tasks and differences in requirements to the experiments. Indeed, use of spacecraft with chemical power sources for some studies that did not require long-term experiments in space proved to be right. On the contrary, power supply system based on photovoltaic converters was more applicable for the studies that required long spacecraft lifetime. Some scientific and research tasks required Sun-oriented spacecraft.

Finally, a decision was made to create three modifications of the unified satellite platform: non-oriented with chemical power sources - DS-U1, non-oriented with solar arrays - DS-U2 and Sun-oriented - DS-U3. Preliminary Design for the unified spacecraft was developed in 1963.

Extensive scope of the space-related activities pre-determined the Decree of the Minister of General Engineering of October 30, 1965 on creation of a space-specialized design office in OKБ-586. 49 unified spacecraft were manufactured and delivered to the orbit in 1963-1976. In order to improve performance capabilities, many of these spacecraft were equipped with additional devices and systems for spacecraft stabilization, spacecraft twist around its longitudinal axis or orientation based on the magnetic field vector of the Earth.

30 inventions witness high scientific and technical level of unified small spacecraft.

Unified small spacecraft platforms became instrumental base for establishment of international cooperation in the field of space exploration under Intercosmos program.

The results of scientific researches on some problems of space physics conducted using unified small satellites obtained high estimate and worldwide recognition. Those results were reported on 27 international symposia and congresses, published in 95 scientific articles in national and foreign publications and demonstrated on ten international and four national exhibitions.

Automated Universal Orbital Stations
Creation Concept

Unified small spacecraft of DS-U type played an outstanding role in pioneer studies of physical peculiarities and determination of characteristics of the near-Earth space.

By early 70s' study of mechanism of inter-relation between physical phenomena in near-Earth space and Sun-Earth relations became the issue of the day. Spacecraft of DS-U type could not be used for accomplishment of such a complex task due to their limited lifetime and functional capabilities.

The results of the analysis made by Yuzhnoye Design Office in 1971 showed that major part of the tasks (regardless of their departmental affiliation) might be divided into several groups. Similarity of the requirements imposed by the tasks of one group defined technical and economic expediency of creation, modernization and development of specialized spacecraft as modifications of the same spacecraft base named 'multi-purpose spacecraft' (KAM). In particular, the analysis showed that major part of scientific and application tasks that require data collection, memorization and transmission via radio links might be accomplished using multi-purpose spacecraft of three types only: KAM-1, KAM-11 and KAM-111.

A conclusion was made based on the results of engineering studies that the needs of fundamental studies of near-Earth space might be satisfied almost in full using two modifications of automated universal orbital station of KAM-1 class: Earth-oriented (AUOS-3) and Sun-oriented (AUOS-SM). These stations became the base platforms used for creation of task-oriented research spacecraft by their equipping with relevant scientific on-board equipment.

Automated Universal Orbital Station AUOS-3 was aimed at comprehensive study of the space, physical nature of solar activity, geophysical phenomena and their relation with solar activity conducted under the international cooperation programs; it was also aimed at the experiments to the benefit of national economy. It needs minimum changes in the structure and configuration of the on-board equipment when switching from application to another one.

The base spacecraft AUOS-SM was aimed at comprehensive study of the Sun to the benefit of science and national economy conducted under Koronas-I, Koronas-F and Photon Projects.

AUOS-SM-KF

The scientific satellite to investigate solar activity. The AUOS-SM-KF satellite was injected into orbit on July 31, 2001 by Cyclone launch vehicle from Plesetsk cosmodrome. It was built on the basis of AUOS-SM unified space platform developed by Yuzhnoye SDO.
At present, the satellite is operated in standard mode. The scientific information is received by IZMIRAN ground means in Troytsk (Russia) and Neustralitz (Germany).

The satellite is intended to perform comprehensive scientific experiments to investigate solar activity (Koronas-F Project):
- investigation of the dynamics of solar flares of different types;
- determination of the parameters of current layer, assessment of the role of thermal and non-thermal processes, accelerated electrons and protons;
- investigation of the evolution of active area of the Sun in pre-flare and post-flare phases;
- continuous observation of large-scale structure of quiet solar corona and evolution of coronal holes;
- investigation of internal structure and dynamics of state of the Sun including rotation of its internal layers based on the observation of solar oscillations.
The project is of world importance by the composition of tasks to be solved.
The comprehensive observations of solar activity from Koronas-F satellite allowed to acquire new knowledge of the internal structure of the Sun, its activity close to the maximum of solar cycle, to better understand the solar-terrestrial links and mechanisms of solar activity effect on the near-Earth space and Earth's atmosphere.

Participants of the experiment:
The Institute of Terrestrial Magnetism Ionosphere and Radio Wave Propagation (IZMIRAN) of the Russian Academy of Science, P.N. Lebedev Physical Institute of the Russian Academy of Science, Main Astronomical Observatory of the National Academy of Science of Ukraine, Kiev State University, and scientific institutions of Germany, Poland.
The composition of scientific equipment:

The satellite operation allows to continue further participation in the joint Russian-Ukrainian scientific investigation of the Sun. Already by late December 2001, more than 400000 pictures of the Sun had been received in different lines of X-ray range based on which the 3D images and dynamics of solar corona were reconstructed, for the first time the dynamic plasma structures with the temperatures almost ten times as high as the temperature of solar corona were revealed. During a day, through the onboard system of scientific data collection, in the order of 100 MByte of primary information was transmitted to the ground which was then distributed between the scientists - experiments organizers Interesting results may be received from the DIFOS solar photometer that monitors global oscillations of solar radiation intensity in the range from ultra-violet to infrared. The SRT-K solar X-ray telescope and RES-K X-ray spectrometer have a very short time of image construction which allows to trace in detail the course of solar processes in 11 spectral ranges well comparing with the data received from the instruments of American-European observatory SOHO by spatial resolution. The accumulated data received at the present time from the satellite will allow to better understand the inner state of the Sun and the physical processes taking place in its depths.

Study of physical processes that take place at energy liberation or transfer in different areas of active Sun and development of diagnostic system for permanent (regular) solar activity forecasting based on the results of such studies were the main scientific goals of the above projects.

Conceptual basis for modification of AUOS-3 and AUOS-SM stations remained, in principle, the same as previously outlined for the spacecraft of DS-U type. At the same time, functional capabilities of the spacecraft, namely payload mass (up to 400-600 kg), daily average power consumption (no less than 50 W), attitude control accuracy, number of commands, informational properties of the radio link were improved. Unification also affected configuration of the on-board scientific equipment: system providing technical service of scientific instruments and equipment for radio link of international frequency band to downlink data directly to the foreign originators of the experiments under Intercosmos program were incorporated as uniform parts.

All these steps gave a chance to increase the number of scientific instrument installed onboard the spacecraft from several instruments up to two dozen and more thus enabling experiments of comprehensive nature.

Development of task-oriented configurations for AUOS-3 stations started in 1973. All experiments conducted at the station may be considered as unique.

Eleven spacecraft based on AUOS-3 platform were developed, manufactured and launched in 1973-1991. Nine of these spacecraft were launched under international cooperation program. Application of unification ideas enabled task accomplishment in minimum time at minimum costs.

AUOS-SM station and its task-oriented configurations have been under development since 1987. The first configuration of the station - AUOS-SM-KI - is in the orbit. Koronas-I experiment on study of Sun radiation in the wide spectrum range is the task of this station.

All configurations of AUOS-3 and AUOS-SM stations were launched from Plesetsk Launch Site using launch vehicles 11K65M (in the early phases) and 11K68.

Spacecraft for Natural Resources Application
Tasks and History of the Sector

The issue of development of a separate sector aimed at application of space systems for solution of tasks related to natural resources was originally raised at the governmental level in the Decree of Central Committee of Communist Party of the Soviet Union and Council of Ministers of the USSR of May 5, 1977. The Decree stipulated development and establishment of state space system for exploration of natural resources of the Earth. The Decree entrusted Yuzhnoye Design Office with development of Ocean subsystem for comprehensive study of the ocean in order to elaborate a long-term weather and climate forecasting theory and implement it in national economy, to lay theoretical foundation for rational use of biologic and mineral resources of the ocean, to provide thorough economic activity at the shelf and in some individual water areas and to provide optimum and safe navigation and ocean pollution control.

Creation of Ocean subsystem started in 1979-1982 with scientific and methodological experiments using Ocean-E (Cosmos-1076 and 1151) and AUOS-3-R-P-IK (Intercosmos-20 and 21) spacecraft. Cosmos-1076 and 1151 spacecraft based on modified structure and hardware of Yuzhnoye-designed Celina-D spacecraft were equipped with radar, optical-electronic and radio-transmitting equipment as well as with the system for data acquisition from buoy platforms. Debugging of the methodology for synchronous remote measurement of oceanic and atmospheric parameters, development of methods for calibration of the remote sensing data using data from sub-satellite measurements, development of methodology, algorithms and programs for processing of the data from satellite measurements, etc. were the main tasks of the experiments. In general, the tasks were accomplished.

Methods for measurement of hydro-physical parameters in microwave, infrared and visible range of the spectrum of electromagnetic radiation emitted by the oceanic surface were debugged in course the experiment. The obtained material confirmed feasibility to map the large-scale distributions of the ocean temperature, wind speed, pack ice borders and density, water storage of the clouds, etc. Experiments with data acquisition and transmission system also brought positive results.

Large-scale flight operations with experimental satellites Ocean-OE (Cosmos-1500 and 1602) were conducted in 1983-1986 with participation of customer organizations from affected departments - State Hydrometeorology Committee, Ministry of Fish Industry, Marine Ministry and Academy of Sciences of the USSR. The above spacecraft were national and world pioneers in implementation of the complex surveillance principle that ensures simultaneous reception of radar, thermal and optical images through a combined swath as well as real-time data downlink from the spacecraft to data reception centers and directly to the customers' autonomous data reception stations. Data provided by these spacecraft was used for solution of important issues of the national economy, including regular mid-term and long-term forecasting of ice conditions in the Arctic region to support naval operation, ice and hydrometeorology conditions analysis for sea navigation in extremely difficult areas (nearby Vrangel Island in 1983, in Okhotsk Sea and Tatar Strait in 1985), in the Antarctic (in 1985) and in the operation areas of scientific and research ships and ships carrying scientific expeditions (support to liberation of 'Mikhail Somov' from ice captivity, in particular), etc. Surveying the land, the spacecraft provided valuable information concerning geological and soil structures, soil moisture rate, dynamics of pack ice evolution in the land-locked seas, lakes and rivers, monitoring of flood process dynamics.

20 thousand of inter-negatives and 30 thousand of printed images were delivered to 74 customer organizations over the time of Cosmos-1500 and 1602 spacecraft operation in 1983-1985. The results of spacecraft operation contributed to decision-making on stabilization of on-board research equipment configuration for further modifications and to creation of Ocean-01 subsystem.

Six Ocean-01 spacecraft were manufactured and launched to the orbit. The same spacecraft served as a base for creation of the first Ukrainian Sich-1 spacecraft.

The experience that was gained gave a chance to approach, with much understanding, development of the requirements to the operational system of the second phase based on use of Ocean-0 spacecraft. Development of this unique spacecraft that accommodated radar, radiometric and optical-electronic (of visible and infrared range) research equipment, wide-band radio link and data acquisition and transmission equipment was performed in 1980-1990.

Further development of natural resources sector took place under the National Space Program of Ukraine (Sich-1 space system).

Sich-1M

A multi-functional Earth remote sensing satellite. Created under the National Space Program.

The satellite was launched on 24.12.04.

The satellite was intended to obtain data concurrently in optical, infrared and microwave bands. A complex of research equipment installed on Sich-1M satellite allowed accomplishing a series of practical and scientific tasks of investigation of atmosphere and World Ocean , monitoring of hydrological and ice conditions, vegetable and soil land cover et al. The national scientific-applied program of using the Sich-1M satellite data was developed. The satellite carried the equipment of Variant international project for ionospheric investigation. This is the first international scientific project headed by Ukrainian specialists.

The Sich-1M satellite was built on the basic of Sich-1 satellite bus structure and Ocean-01 satellite family but by its instrumentation complex this was a satellite of essentially higher level:

- The updated imager ensured the resolution higher by an order (spatial resolution 24 m).

- The side-looking radar parameters were improved – the side – looking radar swath was widened from 450 to 700 km.

- The MTVZA-OK optical–microwave scanner for concurrent measurements in visible, IR and UHF – bands ensured global environment monitoring in the interests of meteorology, oceanology, fishing, climatology.

- The satellite carried the NAVSTAR satellite navigation system equipment and BIS-S digital radio line in international bands 8.2 GHz and 1.7 GHz with a disk data storage device, which brings the satellite to high technical level.

- Qualitatively new was the Earth observation data reception, processing and distribution complex.

In the tactico-technical parameters of research equipment the satellite stands with the SPOT, TRS-1, Resurs satellites.

The Sich-1M satellite had sufficiently high information capabilities by the composition and characteristics of research equipment and (which is most important) by the possibility of wide and expeditious user access to information. The satellite launch allowed demonstrating the capabilities and advantages of integrated investigations at the interaction of NOAA+Meteor+Sich-1M systems, which opened up the prospects of creating a highly effective system consisting of several satellites for continuous meteorological and oceanological investigations.

A wide set of onboard radio lines in the bands 137 MHz, 1.7 GHz and 8.2 GHz allowed receiving satellite signal by practically the whole existing inventory of reception stations on all continents (more than 1000 stations of the channel 137 MHz, more than 200-1.7 GHz, and more than 30-8.2 GHz) and directly at autonomous user terminals.

One of the tasks of Sich-1M satellite launch was support of Variant experiment – investigation of earthquake precursors. The Sich-1M satellite was launched at the same time as a French satellite DEMETR whose main scientific task was monitoring of seismically active phenomena in ionosphere. The concurrent observations at two spatial points created principally new favorable opportunities for setting new tasks and increasing the experiment results authenticity. In the frameworks of DEMETR and Sich-1M satellites scientific programs, the coordinated ground experiments and remote sensing experiments were carried out, which were timed with TIMED satellite and ground service facilities operation schedule. A retrospective analysis of the data was made using the data obtained as a result of previous satellite launches (including WINDII experiment on UARS, ALOUETTE-1, ISS-b and Intercosmos satellites). The synchronous experiment at different altitudes in seismically active areas allowed creating a database to confirm the developed theoretical hypotheses.

The first generation of the spacecraft includes DS-P1-Yu, DS-P1-I and Tulpan spacecraft based on DS-P1 spacecraft and aimed at solution of military tasks related to debugging, adjustment, calibration and certification of ground and space-based special-purpose systems belonging to the Defense Ministry of the USSR.

Spacecraft Radio-electronic Surveillance
Objectives and history of the sector

The works on development of space-based radio-electronic surveillance systems started in August 1960 when the task was set to develop for the Defense Ministry of the USSR the first experimental DS-K8 spacecraft aimed at experimental testing of means and methods for definition of the parameters of radar signals emitted by military radar-location stations.

Studies conducted using the equipment installed on-board Ds-K8 spacecraft showed the need for and expediency of development of improved payload and specialized spacecraft to accommodate such equipment. A decision was made to conduct developmental activities aimed at creation of the space-based radio-electronic systems for surveillance over radar-location systems. The first phase provided for development, based on the experience gained from creation of unified DS-U1 and DS-U2 spacecraft, and launch of two experimental DS-K40 spacecraft accommodating payload with improved sensing properties, mass and dimensions. Both launches of DS-K40 spacecraft that took place in 1965-1966 were unsuccessful due to launch vehicle failure.

Development of this sector turned to its second phase at development of means for radio-electronic surveillance as parts of Celina system based on considerably lighter micro-element-based equipment.

Development of Celina system started in 1964.

The system consisted of Celina-0 and Celina-D spacecraft.

Celina-0 spacecraft was aimed at sweep radio-electronic surveillance. The spacecraft was non-oriented; it had unique structure that used some components of the spacecraft that had been developed earlier and solar power sources.

Celina-D spacecraft was aimed at detailed radio-electronic surveillance conducted by the on-board equipment through radar signal acquisition, analysis and accurate orienting reference. This spacecraft was oriented in the orbital reference system; it differed from the earlier spacecraft with a more complex system of special and support equipment.

Experience gained from operation of Celina-0 and Celina-D spacecraft as parts of Celina system showed high efficiency of target task accomplishment due to implemented technical solutions also giving a chance to estimate feasibility for further improvement of radio-electronic surveillance systems. A number of determinant technical solutions implemented on the spacecraft on next generation Celina-2 development of which started in 1972 were outlined based on the results of analysis of Celina system operation and future trends of on-board special and support equipment development, namely:
- sweep and detailed surveillance functions implemented in single spacecraft;
- expanded frequency band;
- expanded swath for detailed surveillance;
- improved rate and responsiveness of surveillance (in particular, feasibility of special data downlink through re-translation spacecraft was provided);
- selected quasi-synchronous orbit that ensures improved efficiency of radio environment monitoring;
- selected configuration and tasks of the on-board control complex comprising automated spacecraft control system;
- increased spacecraft lifetime;
- improved spacecraft properties, namely payload mass, data storage, attitude control accuracy, capacity of electrical power supply system.

Celina-R spacecraft modification was created in 80s' based on Celina-D spacecraft and equipped with special equipment to monitor sources of radio emissions. Commissioning of Celina-R spacecraft solved the radio-electronic surveillance task in full.

Soviet Army used space systems based on Celina-0, Celina-D, Celina-R and Celina-2 spacecraft.

International Cooperation
Intercosmos program

Yuzhnoye Design Office made a significant contribution to evolution of international cooperation of socialist countries in the field of fundamental study of the near-Earth space with the help of space systems. Company's activities in this field were coordinated by 'Intercosmos' Council for International Cooperation of the Academy of Sciences of the USSR established in 1966 to coordinate activities of Ministries, Departments, Scientific organizations and industrial enterprises of the USSR.

Yuzhnoye Design Office came with an initiative to use Yuzhnoye-designed unified spacecraft of DS-U type (in 1965) and later automated universal orbital station for joint scientific experiments. The initiative was supported thus giving a chance to the Academy of Sciences of the USSR to run a wide-range complex program of space exploration (Intercosmos Program) in cooperation with Academies of Sciences of the socialist countries: Bulgaria, Hungary, German Democratic Republic, Cuba, Mongolia, Poland, Romania, Czechoslovakia, СРВ and with further participation of scientific organization from France, India, Sweden, Austria and other countries.

The first Intercosmos-1 spacecraft was launched onboard launch vehicle 11K63 on October 14, 1969 from Kapustin Yar Launch Site. 22 out of 25 automated spacecraft that the USSR launched to the orbit under Intercosmos Program were designed by Yuzhnoye Design Office and manufactured at Yuzhny Machine-building plant. Chapters 'Unified Small Spacecraft' and 'Automated Universal Orbital Stations' provide descriptions of Intercosmos spacecraft and the results of their operation.

Spacecraft transferred to other organization for further development
Meteor Spacecraft

Per the Decree of Central Committee of Communist Party of the Soviet Union and Council of Ministers of USSR of October 30, 1961 ОКБ-586 was entrusted with development of a spacecraft for national meteorological system 'Meteor'. Launch vehicle 65C3 being designed by ОКБ-586 at that time was planned to be used to launch the spacecraft. Preliminary Design development was conducted in 1961-1962. According to technical specifications and design the spacecraft accommodated the following main research equipment:
- television (developed by the National Scientific and Research Institute for Television);
- infrared (developed by Scientific and Research Institute #10);
- actinometric (developed by Geofizika Central Design Office).

Support equipment included electrical power supply system with oriented solar array, gravity attitude control system with gas-jet propulsion for primary spacecraft orientation to Earth, telemetry system and programmed control system. Spacecraft mass in the Preliminary Design phase complied with payload capacity of launch vehicle 65C3.

Main subcontractors were defined; good technical solutions were found for some systems (in particular unfolding umbrella-like antenna for television equipment) in course of development in ОКБ-586.

However, due to different reasons resulting, first of all, from the need to use all facilities of ОКБ-586 and Plant #586 for development of a new generation strategic missiles and R-56 heavy missile M. K. Yangel made a proposal to transfer development of Meteor spacecraft to State Scientific and Research Institute of Electromechanics and to transfer development of launch vehicle 65C3 and communication satellites to ОКБ-10.

The Committee for Military and Industrial Issues of the Presidium of Council of Ministers of the USSR supported this proposal retaining leading role in these systems for ОКБ-586. As a result of that further development of launch vehicle 65C3 was transferred to ОКБ-10 and further development of Meteor spacecraft was transferred to State Scientific and Research Institute of Electromechanics. In May 1962 Developed Design Documentation for Meteor spacecraft was transferred to State Scientific and Research Institute of Electromechanics; a team of the specialists was sent to render assistance in further development.

In 1962 the design underwent significant changes, namely: gravity attitude control system was substituted with active reaction-wheel-based system, system for solar arrays orientation was developed, changes in the structure of the spacecraft were made. ОКБ-586 retained development while Plant #586 retained manufacture and delivery of body elements, gas-jet system, antenna feeder devices and some other components.

As a result of such 'overweight' of the spacecraft and delay in works on development of launch vehicle 65C3 a decision was made to use launch vehicle 8A92M to launch Meteor spacecraft. The first five Meteor spacecraft were launched from Baikonur Launch Site with successive spacecraft, starting with spacecraft #6, launched from Plesetsk Launch Site using launch vehicles 8A92M and, later, 11K68. Meteor space meteorological system was commissioned in 1969.

Spacecraft development of which was terminated
Unified Spacecraft Platforms DS-U4 and DS-U5

Development of DS-U4 and DS-U5 spacecraft platforms was conducted per the initiative of ОКБ-586 as evolution of functional capabilities of DS-U-type spacecraft platforms.

DS-U4 platform was aimed at a wide range of scientific and application studies to be conducted during the space flight with further return of the scientific equipment and object of the study to the Earth. In contrast to previous modifications, DS-U4 platform included unified rescue capsule in one of two versions - biological and technical - to study the effect of the space environment on the living beings and hardware, correspondingly. The capsule was equipped with life-support, capsule-landing and beacon systems. This platform is a national pioneer small spacecraft (up to 550 kg) with round-trip capsule.

DS-U5 was the first designed in the USSR spacecraft with variable orbit. The platform was aimed at for scientific and application studies of the near-Earth space in high circular (up to 4000 km) and elliptical (up to 10000 km) orbits with a wide range of inclinations.

The structure of DS-U4 and DS-U5 platforms was a tore with removable upper lid. Such structure ensured convenient frame-free equipment installation and the best aerodynamic properties of the spacecraft. Attitude control system was based on the rotary stabilization principle. One of the two solar arrays also served as a shutter of thermal control system.

Preliminary Designs for the platforms (1965) and supplements to Preliminary Designs (1966) were issued; experimental works on testing and debugging of the structural elements were commenced; individual technical specification for ionosphere configuration of DS-U5 platform, DS-U5-I, was concurred; spacecraft integration with launch vehicle 11K65M was coordinated.

The works were terminated in 1967 due to overload of the Company with orders in the main sector.