Introduction (problem) 1 Purpose, objectives and basic requirements for the spacecraft 1.1 Purpose and key objectives of spacecraft 1.2 Requirements for CA 1.2.1 Reliability requirements 1.2.2 Requirements for mechanical loads 1.2.3 Requirements for external factors 184.108.40.206 Thermal Model 220.127.116.11 Radiation conditions 18.104.22.168 Impact meteor-man-made bodies 22.214.171.124 Electromagnetic Compatibility 1.3 The flight program (research program) 2 The composition of the space complex 2.1 The composition of the spacecraft 2.1.1 The service platform 2.1.2 Payload 2.2 Launch vehicles 2.3 Controls (GCC) 2.4 means for receiving, processing and dissemination of targeted information (NKPOR) 3 Design and appearance of the main characteristics of satellites 3.1 Principles of spacecraft (SC) 3.2 Design-layout scheme SC 3.3 Preliminary Mass-inertial characteristics 3.3.1 Mass summary 3.3.2 Coordinate Systems 3.3.3 Mass-inertial characteristics 3.4 A preliminary calculation of the energy balance and SES 3.5 A preliminary calculation of the heat balance 3.6 Ballistic study 4 Key performance characteristics of systems platform 4.1 on-board control 4.1.1 Appointment 4.1.2 Composition 4.1.3 Software 4.2 onboard radio 4.2.1 Appointment 4.2.2 Analysis and justification of selecting the type of receiver-transmitter 4.2.3 Reception Transmitter 4.2.4 Antenna-feeder system 4.3 Power supply system 4.3.1 Appointment 4.3.2 The composition of the SES 4.3.3 Solar panels 4.3.4 Batteries 4.3.5 Conversion and Control System 4.4 Propulsion KA 4.4.1 Appointment 4.4.2 Analysis and justification of selecting the type of control 4.4.3 The composition of control 4.4.4 Description and characteristics of units and systems of control 4.5 Means of thermal control 4.5.1 Appointment 4.5.2 The composition of TCS 4.5.3 Method of calculation 4.5.4 The results of thermal calculation 4.6 onboard cable network 5 Task equipment 5.1 Rationale for the target hardware 5.2 Payload composition and its characteristics 5.2.1 Complex Remote Sensing 5.3 Provide information to reset the target spacecraft 5.3.1 Appointment 5.3.2 Analysis and rationale for the choice of the complex relief Chi 5.3.3 Structure of the complex relief Chi 5.3 Description of work payload together with the flight program 6 spacecraft design, durability 6.1 Housing design spacecraft 6.2 Solar panels 6.3 Design Control 6.4 Preliminary assessment of structural strength Layout 7 spacecraft as part of AU, and separation system for the possible launch vehicles 8 Ground Segment 8.1 ground control. Organization of flight control. 8.2 means for receiving chi. 8.3 Processing and distribution of qi, including promotion of the project. 9 feasibility study 9.1 A preliminary calculation of the cost of the project (project cost structure) 9.1.1 Input data for calculations 9.1.2 Estimation of the cost of R & D, including the development and production of the TOE 9.1.3 Estimation of costs to start and conclude the boost into orbit 9.1.4 Cost estimates for the trial operation of spacecraft 9.2 Conclusion on the economic viability of the project and possible sources of fund raising in stages 9.3 Evaluation of the possibility of commercialization of the project. Conclusion Applications 1. Schematic division QC. 2. Schedule Development CC. 3. Dimensional drawing spacecraft. 4. Provisional circuit board cable network.