| 1 | 12.2.2025 Algorithm for filling databases of the automated control system utilized at space rocketry enterprises, considering the differentiation of working and archived information. | 19 | 634 | 0 | 0 | 0 | 35849 |
| 2 | 11.2.2025 Reviewing the benefits of utilizing AL–Mg–Sc alloys in Ukraine’s space rocket industry. Analysis of market factors | 26 | 533 | 0 | 0 | 0 | 35846 |
| 3 | 10.2.2025 Digitalization of design documentation development processes within the enterprise | 24 | 363 | 0 | 0 | 0 | 35843 |
| 4 | 9.2.2025 Product quality analysis using methods of statistical study of repair results | 22 | 288 | 0 | 0 | 0 | 35840 |
| 5 | 8.2.2025 Specificity of spaceport construction at a lunar base | 24 | 301 | 0 | 0 | 0 | 35837 |
| 6 | 7.2.2025 Autonomous deployable landing interface: a detailed technical framework for Mitigating terminal descent risks on planetary surfaces | 20 | 271 | 0 | 0 | 0 | 35834 |
| 7 | 6.2.2025 Floating launch platform of a sea-based space launch site | 21 | 380 | 0 | 0 | 0 | 35831 |
| 8 | 5.2.2025 Analysis and minimization of resistive forces occurring during rocket stage separation. Possibility of using a single pneumatic pusher for stage separation | 25 | 357 | 0 | 0 | 0 | 35828 |
| 9 | 4.2.2025 Thermal decomposition of hydrogen peroxide in the combustion zone of a gas generator. Simulation of the process | 23 | 534 | 0 | 0 | 0 | 35825 |
| 10 | 3.2.2025 Electric thrusters utilizing metal plasma | 26 | 448 | 0 | 0 | 0 | 35821 |
| 11 | 2.2.2025 Performance analysis and validation of a monopropellant air-detonation ramjet engine | 23 | 512 | 0 | 0 | 0 | 35818 |
| 12 | 1.2.2025 Methods for structural strength investigations of rocketry. | 26 | 620 | 0 | 0 | 0 | 35812 |
| 13 | 7.1.2025 Features of the implementation of smart technologies in accounting processes in enterprises in the rocket and space industry | 48 | 371 | 0 | 0 | 0 | 35491 |
| 14 | 6.1.2025 Studying the landing of the reusable first stage of the Cyclone-5 space launch vehicle on a maritime landing platform-duplicate-1 | 57 | 643 | 0 | 0 | 0 | 35488 |
| 15 | 5.1.2025 Studying the landing of the reusable first stage of the Cyclone-5 space launch vehicle on a maritime landing platform | 51 | 937 | 0 | 0 | 0 | 35485 |
| 16 | 4.1.2025 Experimental development of a pyrolysis technology for unwinding carbon composites for filler reuse | 53 | 790 | 0 | 0 | 0 | 35483 |
| 17 | 3.1.2025 Experimental research on separation diaphragm performance in propellant storage and feed systems of liquid propellant tanks | 54 | 987 | 0 | 0 | 0 | 35481 |
| 18 | 2.1.2025 Justification of the parameters of a vertical screw conveyor for transporting lunar regolith | 55 | 848 | 0 | 0 | 0 | 35479 |
| 19 | 1.1.2025 Promomoon initiative for moon village generation in honor of dr. Alexander degtyarev | 50 | 929 | 0 | 0 | 0 | 35475 |
| 20 | 16.1.2024 EDUCATIONAL TENDENCIES AS AN ELEMENT OF INNOVATIVE PROGRESS IN THE PERSONNEL TRAINING SYSTEM FOR THE STATE-OF-THE-ART ENTERPRISES | 143 | 1698 | 0 | 0 | 0 | 34966 |
| 21 | 15.1.2024 Enhancing operability of the fuel system units in the hot climate conditions | 134 | 3815 | 0 | 0 | 0 | 34974 |
| 22 | 14.1.2024 EXPERIMENTAL STUDIES OF THE PERFORMANCE OF PYROTECHNIC DEVICES INSTALLED ON THE LAUNCH VEHICLE SEPARATION SYSTEMS | 122 | 2827 | 1 | 0 | 0 | 35004 |
| 23 | 13.1.2024 MODEL OF QUALITY MANAGEMENT OF TECHNICAL PREPARATION FOR THE METAL+COMPOSITE JOINTS PRODUCTION | 138 | 2095 | 0 | 0 | 0 | 35010 |
| 24 | 12.1.2024 Hardening of steels modifying their surfaces with ion-plasma nitriding in glow discharge | 145 | 4640 | 0 | 0 | 0 | 35070 |
| 25 | 11.1.2024 PARAMETERS CALCULATION OF THE LUNAR REGOLITH TRANSPORT SYSTEM | 150 | 2149 | 1 | 0 | 0 | 35014 |
| 26 | 10.1.2024 METHOD OF AUTONOMOUS DETERMINATION OF THE ROCKET’S REFERENCE ATTITUDE DURING PRE-LAUNCH PROCESSING | 156 | 2682 | 0 | 0 | 0 | 35018 |
| 27 | 9.1.2024 General-purpose thermostatting module – new approach in development of up-to-date thermostating systems for rocket and space complexes | 151 | 2951 | 0 | 0 | 0 | 35030 |
| 28 | 8.1.2024 Theoretic-experimental evaluation of the solid-propellant grain erosive burning | 144 | 1516 | 0 | 0 | 0 | 35027 |
| 29 | 7.1.2024 Selection of the functional units for the Cyclone-4M ILV separation system | 157 | 3927 | 0 | 0 | 0 | 34957 |
| 30 | 6.1.2024 New methods of load-carrying capacity prediction for the ultimately compressed frame structures | 144 | 2531 | 0 | 0 | 0 | 34992 |
| 31 | 5.1.2024 Assessment of risk of toxic damage to people in case of a launch vehicle accident at flight | 166 | 2752 | 0 | 0 | 0 | 34981 |
| 32 | 4.1.2024 The dynamics of servo drives | 127 | 2161 | 0 | 0 | 0 | 34978 |
| 33 | 3.1.2024 Future projects of lunar exploration implemented by Yuzhnoye SDO | 142 | 1686 | 0 | 0 | 0 | 34965 |
| 34 | 2.1.2024 New and advanced liquid rocket engines of the Yuzhnoye SDO | 170 | 3102 | 0 | 0 | 0 | 34964 |
| 35 | 1.1.2024 ANTARES: Yuzhnoye’s project of XXI century | 104 | 534 | 0 | 0 | 0 | 35034 |
| 36 | 9.1.2023 Methodology for selecting design parameters of solid-propellant sustainer engines. Mathematical support and software | 87 | 2632 | 0 | 0 | 0 | 26993 |
| 37 | 8.1.2023 Specificity of developing pyrobolts with low impact and vibration impulse responses | 90 | 1793 | 0 | 0 | 0 | 26992 |
| 38 | 7.1.2023 Specificity of using rubbers as structural materials for making connector assemblies of temperature conditioning systems | 104 | 1552 | 0 | 0 | 0 | 26991 |
| 39 | 6.1.2023 Numerical modeling of translational and rotational vibrations of a solid-propellant rocket motor on a test stand during firing tests | 86 | 1607 | 0 | 0 | 0 | 26990 |
| 40 | 5.1.2023 Fueling-neutralization stations. New developments and applications | 88 | 1798 | 0 | 0 | 0 | 26989 |
| 41 | 4.1.2023 On control of spacecraft orientation to the ground data acquisition station | 83 | 964 | 0 | 0 | 0 | 26988 |
| 42 | 3.1.2023 Analysis of a modernized 9K51 Hrad Multiple Rocket Launcher System to determine the performance specifications of the 122-mm unguided rocket projectile in development | 102 | 2640 | 0 | 0 | 0 | 26987 |
| 43 | 2.1.2023 How Yuzhnoye develops models for flight safety index evaluation for the case of a rocket failure during the flight | 92 | 1952 | 0 | 0 | 0 | 26986 |
| 44 | 1.1.2023 On the development of a methodology for building air and missile defense systems. Explanation of the investigation mechanism | 84 | 2876 | 0 | 0 | 0 | 26682 |
| 45 | 21.1.2020 Contemporary approaches to the improvement of methods of space launch system operation for commercial launches of ILV | 125 | 1896 | 0 | 0 | 0 | 31081 |
| 46 | 20.1.2020 Studying the possibility of alternating delivery of rocket propellant wastes to a common thermal neutralization facility | 119 | 2056 | 0 | 0 | 0 | 31078 |
| 47 | 19.1.2020 Pyrobolts: types, design, development. Shear type pyrobolt developed at Yuzhnoye SDO | 183 | 3409 | 0 | 0 | 0 | 31074 |
| 48 | 18.1.2020 Development of autonomous power engineering systems with hydrogen energy storage | 133 | 3236 | 1 | 0 | 0 | 31056 |
| 49 | 17.1.2020 Acoustic problems of rocket launch | 127 | 2701 | 0 | 0 | 0 | 31054 |
| 50 | 16.1.2020 Parameters of the supersonic jet of a block propulsion system, flowing into a gas duct, considering chemical kinetics of gas-cycle transformations | 137 | 3416 | 0 | 0 | 0 | 31052 |
| 51 | 15.1.2020 Simulation of thermomechanical processes in functionally-gradient materials of inhomogeneous structure in the manufacturing and operation of rocket structural elements | 142 | 3266 | 0 | 0 | 0 | 31050 |
| 52 | 14.1.2020 On the problem of optimum control | 137 | 2153 | 0 | 0 | 0 | 31048 |
| 53 | 13.1.2020 Mathematical models of hydraulic servomechanisms of space technology | 127 | 1757 | 0 | 0 | 0 | 31045 |
| 54 | 12.1.2020 Modification of technology as the main course in the military transport aircraft development | 135 | 2033 | 2 | 0 | 0 | 31043 |
| 55 | 11.1.2020 Some results of strength calculations relying on analytical and FEM approaches. Trends of using contemporary machine learning strategies | 142 | 2635 | 0 | 0 | 0 | 31040 |
| 56 | 10.1.2020 Calculation and selection of parameters for a propellant consumption diagram of dual-thrust main SRM | 128 | 2977 | 0 | 0 | 0 | 31037 |
| 57 | 9.1.2020 Experimental investigation of a liner-free propellant tank made from polymer composite materials | 142 | 3459 | 1 | 0 | 0 | 31035 |
| 58 | 8.1.2020 Determining the main parameters of transport aircraft modifications considering the fuel efficiency | 119 | 1106 | 0 | 0 | 0 | 31033 |
| 59 | 7.1.2020 Studying the motion of a launch vehicle and observed space debris objects during launch preparation | 124 | 1987 | 0 | 0 | 0 | 31031 |
| 60 | 6.1.2020 Mechanics of a satellite cluster. Methods for estimating the probability of their maximal approach in flight | 132 | 1696 | 0 | 0 | 0 | 31028 |
| 61 | 5.1.2020 Strength and stability of inhomogeneous structures of space technology, consid-ering plasticity and creep | 141 | 4818 | 0 | 0 | 0 | 31026 |
| 62 | 4.1.2020 Terminal guidance of the aircraft being maneuvering while descending in the atmosphere under conditions of aerodynamic balancing | 127 | 1560 | 1 | 0 | 0 | 31024 |
| 63 | 3.1.2020 Analysis of the unsteady stress-strain behavior of the launch vehicle hold-down bay at liftoff | 152 | 3363 | 0 | 0 | 0 | 32230 |
| 64 | 2.1.2020 Analysis of development trends of design parameters and basic characteristics of missiles for the advanced multiple launch rocket systems | 144 | 6974 | 2 | 0 | 0 | 31001 |
| 65 | 1.1.2020 Solving a problem of optimum curves of descent using the enhanced Euler equation | 131 | 3114 | 0 | 0 | 0 | 27120 |
| 66 | 14.2.2019 Selection of the validation algorithm for the solid rocket motor trust measurement procedure | 139 | 1629 | 0 | 0 | 0 | 27216 |
| 67 | 13.2.2019 Study of the stress and strain state of the multilayer bellows | 125 | 1574 | 0 | 0 | 0 | 27215 |
| 68 | 12.2.2019 Procedure of acoustic loads measuring during the ILV launch | 133 | 1121 | 0 | 0 | 0 | 27214 |
| 69 | 11.2.2019 Winding the tubes of rectangular section using dowels | 124 | 1348 | 0 | 0 | 0 | 27213 |
| 70 | 10.2.2019 Dynamic performance of the gas drive with jet motor | 139 | 3829 | 0 | 0 | 0 | 32366 |
| 71 | 9.2.2019 Gas-dynamic simulation of the supersonic stream in the pulsed wind tunnel | 137 | 2159 | 0 | 0 | 0 | 27211 |
| 72 | 8.2.2019 Evaluation of the external acoustic loads, acting on the rocket when it passes the leg with maximum velocity head | 141 | 628 | 1 | 0 | 0 | 27210 |
| 73 | 7.2.2019 On critical stress of the longitudinal stability of the stiffened cylindrical shells. Dynamic problem | 120 | 887 | 0 | 0 | 0 | 27209 |
| 74 | 6.2.2019 Stabilization of gas reducers adjustment | 139 | 1418 | 0 | 0 | 0 | 27208 |
| 75 | 5.2.2019 Features of the development testing of the propellants deposition inside the tanks of launch vehicles | 132 | 1363 | 1 | 0 | 0 | 27207 |
| 76 | 4.2.2019 Numerical simulation of behavior of elastic structures with local stiffening elementse | 130 | 1140 | 1 | 0 | 0 | 27206 |
| 77 | 3.2.2019 Features of design and production of the technological aids for assembly of the spacecraft separation system of CLAMP BAND type | 116 | 1869 | 0 | 0 | 0 | 27205 |
| 78 | 2.2.2019 Mathematical models for assessment of safety in the impact area of cluster ammunition of the warhead during missile complex testing | 134 | 2560 | 0 | 0 | 0 | 27204 |
| 79 | 1.2.2019 Optimization of the trajectory of the antiaircraft guided missile | 142 | 3675 | 0 | 0 | 0 | 28723 |
| 80 | 27.1.2019 Phases of Cooperation of Yuzhnoye SDO and Dnipro National University Physical Engineering Department on the Issues of Mutual Human Resourcing: Past, Present. Future | 117 | 1535 | 0 | 0 | 0 | 27732 |
| 81 | 26.1.2019 New Technologies and Problems of Their Introducing in Ukraine | 123 | 1393 | 0 | 0 | 0 | 27731 |
| 82 | 25.1.2019 Technological Peculiarities of Manufacturing Products of Irregular Profile by Method of Selective Laser Melting of 316L Powder Metal Material | 119 | 1835 | 0 | 0 | 0 | 27730 |
| 83 | 24.1.2019 Porous Cast Materials (Gasars). Options of Their Use in Space Rocket Hardware | 137 | 1885 | 0 | 0 | 0 | 27729 |
| 84 | 23.1.2019 Calculation of Thermal-Physical Properties of Gaseous Xenon | 116 | 1541 | 1 | 0 | 0 | 27728 |
| 85 | 22.1.2019 Calculation of Uncertainty of Represented Values of Linear Accelerations during Centrifugal Machines Certification | 115 | 1342 | 0 | 0 | 0 | 27727 |
| 86 | 21.1.2019 Optimization of Geometrical Shape of Isolation Valve Blading Position | 116 | 1058 | 0 | 0 | 0 | 27726 |
| 87 | 20.1.2019 Possibilities of Increasing Acting Loads on Hydraulic Actuator Middle Position Lock | 123 | 1141 | 0 | 0 | 0 | 27725 |
| 88 | 19.1.2019 Peculiarities of Radio Transparent Fairings Development | 162 | 1476 | 2 | 0 | 0 | 27724 |
| 89 | 18.1.2019 Designing of Servo Driver of Throttle Mechanisms and Fuel Flow Regulator of ILV Main Motor | 129 | 1385 | 0 | 0 | 0 | 27723 |
| 90 | 17.1.2019 Development of Prospective Small-Size Auxiliary SMR of New Type | 124 | 1943 | 0 | 0 | 0 | 27722 |
| 91 | 16.1.2019 Oscillation Processes in Rig at the Moment of SRM Transfer to Main Operation Mode | 122 | 1153 | 0 | 0 | 0 | 27721 |
| 92 | 15.1.2019 Simulation of SMR Oscillations in Rig that Arise during Firing Bench Test | 127 | 2071 | 0 | 0 | 0 | 27720 |
| 93 | 14.1.2019 Technique of Determination of SRM Operational Life Taking into Account Materials and Elements Strength Margins | 129 | 558 | 0 | 0 | 0 | 27719 |
| 94 | 13.1.2019 Prediction of Solid Propellant Burnout Time in Launch Vehicle Propulsion System in Flight | 129 | 1575 | 0 | 0 | 0 | 27718 |
| 95 | 12.1.2019 Monitoring of Launch Platform Drift Parameters during Zenit-3SL Integrated Launch Vehicle Prelauch Processing | 122 | 1613 | 1 | 0 | 0 | 27717 |
| 96 | 11.1.2019 Peculiarities of Development Testing of Space Rocket Thermostating System Mating Points Hoses | 129 | 892 | 0 | 0 | 0 | 27716 |
| 97 | 10.1.2019 Semi-Empirical Evaluation of External Acoustic Loads in Payload Area during Lift-off | 122 | 1717 | 1 | 0 | 0 | 27715 |
| 98 | 9.1.2019 Modeling of Cyclone-4M Rocket Jet Acoustic Emission by Volumetric Source | 138 | 1733 | 0 | 0 | 0 | 27714 |
| 99 | 8.1.2019 Virtual Tests of Cassette Reentry Vehicle Dash Elements Attachment System during Ground Operation | 131 | 2123 | 0 | 0 | 0 | 27713 |
| 100 | 7.1.2019 Experience of Development and Use of Generator Pressurization System for Tanks of Launch Vehicles on High-Temperature Propellants | 134 | 954 | 2 | 0 | 0 | 27712 |
| 101 | 6.1.2019 Investigation into Peculiarities of Delivery to Launch Base of Rocket Propellant with Specified Gasing | 126 | 1403 | 1 | 0 | 0 | 27711 |
| 102 | 5.1.2019 Methodology of Normative Principles of Justification of Launch Vehicle Launching Facility Structures Lifetime | 143 | 1695 | 0 | 0 | 0 | 27710 |
| 103 | 4.1.2019 Mathematic Modeling and Investigation into Stress-Strain State of Space Rocket Bays | 128 | 1804 | 4 | 0 | 0 | 27709 |
| 104 | 3.1.2019 Analysis of Spacecraft Control Issues In Early Design Phases | 145 | 1268 | 0 | 0 | 0 | 27708 |
| 105 | 2.1.2019 Flying Vehicle Maneuvering Dynamics in Atmosphere with Weight Asymmetry and Elements of Terminal Control in Turn Leg | 137 | 1157 | 1 | 0 | 0 | 27707 |
| 106 | 1.1.2019 On 65-th anniversary of the company | 118 | 536 | 0 | 0 | 0 | 27703 |
| 107 | 23.2.2018 On the Role of Space in Origination of Inertia Force Field, Earth Gravity Force Field and Zero Gravity of Material Body | 136 | 2384 | 0 | 0 | 0 | 30813 |
| 108 | 22.2.2018 Uncertainty Calculation Procedure during Measuring Instrumentation Calibration | 114 | 3408 | 0 | 0 | 0 | 30810 |
| 109 | 21.2.2018 Ensuring Aiming Accuracy of Ship’s Telemetry Reception Antenna Installation for Small Vessels | 107 | 1993 | 0 | 0 | 0 | 30807 |
| 110 | 20.2.2018 The Use of Special Devices during Launch Pad Development Testing | 117 | 1674 | 0 | 0 | 0 | 30805 |
| 111 | 19.2.2018 Control of Validity and Assessment of Accuracy of Telemetry Results during Full-Scale Test of Launch Vehicles | 123 | 2259 | 0 | 0 | 0 | 30801 |
| 112 | 18.2.2018 Angular Stabilization of an Object Rapidly Rotating around Longitudial Axis | 126 | 1909 | 0 | 0 | 0 | 30799 |
| 113 | 17.2.2018 Peculiarities of Dynamics of Recoverable Part of Stage of Aircraft-Type Configuration with Turbojet Engine | 133 | 1398 | 0 | 0 | 0 | 30796 |
| 114 | 16.2.2018 Design Solutions to Prevent Propellant Ingress into SRM Case Space behind Sealing Ring | 234 | 2310 | 0 | 0 | 0 | 30792 |
| 115 | 15.2.2018 Topical Issues of Creation of Space Rocket Thermostatic System Mating Points | 131 | 1258 | 1 | 0 | 0 | 30786 |
| 116 | 14.2.2018 A Concept of Modular Transport Vehicle for Lunar Program | 122 | 1441 | 0 | 0 | 0 | 30780 |
| 117 | 13.2.2018 On an Approach to Constructing the Extremes in the Tasks of Optimal Solutions Search | 115 | 994 | 0 | 0 | 0 | 30778 |
| 118 | 12.2.2018 Methodological Support for Initial Phase Optimization of Projecting Design, Trajectory Parameters and Rocket Object Motion Control Programs | 129 | 1724 | 6 | 0 | 0 | 30770 |
| 119 | 11.2.2018 Some Peculiarities of Ensuring LRE Guarantied Service Life in the Conditions of Replacement of Components of Interindustry Application | 113 | 1820 | 0 | 0 | 0 | 30768 |
| 120 | 10.2.2018 Calculation of Gas Flow in High-Altitude Engine Nozzle and Experience of Using Water-Cooled Nozzle Head during Tests | 124 | 2648 | 0 | 0 | 0 | 30766 |
| 121 | 9.2.2018 The Impact of Worm Design on Power and Anti-Cavitation Properties of Worm-Centrifugal Pumps | 128 | 2948 | 0 | 0 | 0 | 30763 |
| 122 | 8.2.2018 Development of Nozzle Blocks New Manufacturing Technology without Blazing | 125 | 2201 | 3 | 0 | 0 | 30757 |
| 123 | 7.2.2018 Theoretical Models of Sound Speed Increase Effects in Gas Duct with Corrugated Wall | 138 | 2640 | 0 | 0 | 0 | 30754 |
| 124 | 6.2.2018 Introduction of Additive Technologies for LRE Parts Manufacturing | 120 | 1914 | 0 | 0 | 0 | 30751 |
| 125 | 5.2.2018 Electromagnetic Valves Developed by Yuzhnoye SDO Liquid Rocket Engines Design Office | 135 | 2852 | 1 | 0 | 0 | 30749 |
| 126 | 4.2.2018 Turbopump Units of Rocket Engines Developed by DO-4 | 139 | 1052 | 1 | 0 | 0 | 30735 |
| 127 | 3.2.2018 Possible Ways of Modernization of VEGA Launch Vehicle AVUM Stage Main Engine Assembly | 132 | 2622 | 0 | 0 | 0 | 30733 |
| 128 | 2.2.2018 Yuzhnoye SDO-Developed Upper Stage Liquid Rocket Engines | 161 | 1061 | 0 | 0 | 0 | 30729 |
| 129 | 1.2.2018 Design Office of Liquid Rocket Engines is 60 | 131 | 670 | 0 | 0 | 0 | 30723 |
| 130 | 16.1.2018 Some Correlation Dependences in Families of Aton and Apollo and Rendezvous Frequency in Main Asteroid Belt | 120 | 994 | 0 | 0 | 0 | 30477 |
| 131 | 15.1.2018 The Results of Using Automated Methods to Solve Standardization Tasks in Yuzhnoye SDO Practice | 128 | 1876 | 0 | 0 | 0 | 30474 |
| 132 | 14.1.2018 A Rectangular Section Pipes Winding Programs Calculation Procedure | 125 | 1567 | 0 | 0 | 0 | 30472 |
| 133 | 13.1.2018 On Selection of Materials for Creation of Modern LV Thermostating System Mating Hoses | 130 | 1716 | 2 | 0 | 0 | 30469 |
| 134 | 12.1.2018 A Device for Soft Separation of Spacecraft from Launch Vehicle | 131 | 1805 | 0 | 0 | 0 | 30464 |
| 135 | 11.1.2018 Ensuring Long Lifetime of the Electrochemical Accumulators Included in Space Rocketry Electric Power Supply Systems | 132 | 1822 | 0 | 0 | 0 | 30466 |
| 136 | 10.1.2018 The Rocket Propellant Vapors and Water Solutions Neutralization Units. The Accumulated Experience and Prospects of Updating the Neutralization Units | 146 | 1286 | 0 | 0 | 0 | 30462 |
| 137 | 9.1.2018 On the Peculiarities of High-Temperature Rocket Propellants Drain from Delivery Means to Filling Tank for Closed Drain | 126 | 1740 | 0 | 0 | 0 | 30460 |
| 138 | 8.1.2018 The Solid–Propellant Motors with Regulated Thrust | 157 | 1988 | 1 | 0 | 0 | 30458 |
| 139 | 7.1.2018 Prospective Gas Purification Device for LRE Test Bench | 137 | 1095 | 0 | 0 | 0 | 30456 |
| 140 | 6.1.2018 On Building of Inertial Navigation System in the Condition of Presence of Considerable g-Load and Angular Velocity in Preferential Direction | 138 | 1573 | 0 | 0 | 0 | 30454 |
| 141 | 5.1.2018 Experimental Determination of Lateral Force Caused by SRM Thrust Vector Eccentricity and Skew | 131 | 2467 | 0 | 0 | 0 | 30421 |
| 142 | 4.1.2018 Determination of Angular Acceleration of Rotary Elements of Rocket Systems during Ground Tests | 122 | 1118 | 0 | 0 | 0 | 30411 |
| 143 | 3.1.2018 The Means of Functional Suppression of Radio Electronic Facilities of Small-Size Unmanned Aerial Vehicles with Electromagnetic Radiation Focusing | 129 | 1856 | 0 | 0 | 0 | 30408 |
| 144 | 2.1.2018 Dehydration of Hydrocarbon Fuels by Method of Over-Saturation Drop | 125 | 1610 | 0 | 0 | 0 | 30403 |
| 145 | 1.1.2018 Modernization and Automation of Temperature Calculation of Measurement Errors of Climatic Chambers for Accelerated Environmental Tests | 120 | 1830 | 0 | 0 | 0 | 30158 |
| 146 | 27.2.2017 Solution of “Unsolvable” Problems | 123 | 799 | 0 | 0 | 0 | 29966 |
| 147 | 26.2.2017 State of the Art and Prospects for Nuclear-Quadrupole Resonance Thermometry in Ukraine | 139 | 2482 | 0 | 0 | 0 | 29962 |
| 148 | 25.2.2017 Vacuum Conditions Simulation Criteria | 138 | 1078 | 0 | 0 | 0 | 29958 |
| 149 | 24.2.2017 Method of Supercooled Cryogenic Liquid Production | 142 | 711 | 0 | 0 | 0 | 29954 |
| 150 | 23.2.2017 Optimization Technique for Mass of Locally Loaded Rocket Bays with Wafer Structure | 128 | 2111 | 0 | 0 | 0 | 29948 |
| 151 | 22.2.2017 Advanced Aluminum Alloys for Launch Vehicle Pipeline Parts Manufacture | 122 | 1303 | 0 | 0 | 0 | 29944 |
| 152 | 21.2.2017 Mass Parameter Optimization of Thermal Protective Structure for Reusable Spacecraft | 125 | 1014 | 0 | 0 | 0 | 29940 |
| 153 | 20.2.2017 Research Support for Development of Launch Vehicle Payload Unit Composite Load-Bearing Compartments | 131 | 2513 | 0 | 0 | 0 | 29866 |
| 154 | 19.2.2017 Experience in Development of Pneumatic System for Aerodynamic Payload Fairing Separation | 134 | 729 | 0 | 0 | 0 | 29862 |
| 155 | 18.2.2017 Development Test of Payload Fairing Separation Dynamics under Ground Conditions | 134 | 848 | 0 | 0 | 0 | 29858 |
| 156 | 17.2.2017 Development Test of Spacecraft Separation Dynamics under Ground Conditions | 137 | 984 | 0 | 0 | 0 | 29854 |
| 157 | 16.2.2017 Determination of Spherical Flange Connections Gasket Clamping Site Width | 128 | 547 | 0 | 0 | 0 | 29850 |
| 158 | 15.2.2017 Oxidizer Feedline Structural Optimization Results | 133 | 1501 | 0 | 0 | 0 | 29846 |
| 159 | 14.2.2017 Development Test of Isolating Valve Operation under Cryogenic Conditions | 129 | 793 | 0 | 0 | 0 | 29842 |
| 160 | 13.2.2017 Experience in Development of Isolating Fuel Valve with Pneumatic Drive and Hydraulic Brake for Operation under Cryogenic Conditions | 125 | 1811 | 0 | 0 | 0 | 29836 |
| 161 | 12.2.2017 Determination Procedure for Pneudraulic System and Its Components No-Failure Operation Probability | 124 | 1027 | 0 | 0 | 0 | 29785 |
| 162 | 11.2.2017 Remote Monitoring Method of Pneudraulic System Structural Elements Integrity | 127 | 1417 | 0 | 0 | 0 | 29781 |
| 163 | 10.2.2017 Analysis Method of Hydraulic Parameters of Circular Intake Device in Limit Operating Modes | 128 | 2209 | 0 | 0 | 0 | 29771 |
| 164 | 9.2.2017 Peculiarities of Development of Cryogenic Propulsion System Circulating Cooling System | 130 | 1322 | 0 | 0 | 0 | 29767 |
| 165 | 8.2.2017 Analysis Method of Nitrogen Tetroxide Tanks Generating Pressurization Systems | 117 | 603 | 0 | 0 | 0 | 29763 |
| 166 | 7.2.2017 Features of Pneumatic Hydraulic Feeding System with the Use of Oxygen-Methane Cryogenic Propellants | 131 | 1276 | 0 | 0 | 0 | 29758 |
| 167 | 6.2.2017 Set of Actions on Enhancement of Launch Vehicle Payload Capability | 139 | 1160 | 0 | 0 | 0 | 29754 |
| 168 | 5.2.2017 Structural Perfection of Cyclone-4 Integrated Launch Vehicle | 124 | 771 | 0 | 0 | 0 | 29750 |
| 169 | 4.2.2017 Increase of LV Payload Capability through Enhancement of Propulsion System Pneudraulic System Characteristics | 131 | 570 | 0 | 0 | 0 | 29746 |
| 170 | 3.2.2017 Creation of Advanced Facilities for Spacecraft / Launch Vehicle Integration | 130 | 555 | 0 | 0 | 0 | 29739 |
| 171 | 2.2.2017 Creation of Universal System of Launch Vehicle Space Head Modules for Cluster Spacecraft Missions | 141 | 1164 | 0 | 0 | 0 | 29649 |
| 172 | 1.2.2017 DO-2 – Semicentenary | 115 | 537 | 0 | 0 | 0 | 30174 |
| 173 | 17.1.2017 Peculiarities of Design and Development Test of Dispenser Turning Actuator System for SHM with Iridium NEXT SC | 121 | 1571 | 0 | 0 | 0 | 29518 |
| 174 | 16.1.2017 Principal Directions for Creation of Integrated Launch Vehicle Autonomous Onboard Flight Safety System | 123 | 2045 | 0 | 0 | 0 | 29514 |
| 175 | 15.1.2017 Assessment of Liquid Equipment Neutralization Method Effectiveness | 120 | 963 | 0 | 0 | 0 | 29505 |
| 176 | 14.1.2017 Design Studies into Dynamic and Structural Characteristics of Two-Stage Direct-Action Solenoid-Operated Hydraulic Valve | 120 | 1011 | 0 | 0 | 0 | 29497 |
| 177 | 13.1.2017 Reliability Evaluation of ILV Thermostating System Mating Hoses | 128 | 1809 | 0 | 0 | 0 | 29483 |
| 178 | 12.1.2017 Static Performance Prediction of Hot-Gas Flapper-Nozzle Actuator | 117 | 1605 | 0 | 0 | 0 | 31702 |
| 179 | 11.1.2017 Environmental Safety of Bench Testing the Advanced Solid-Propellant Rocket Motors | 127 | 872 | 0 | 0 | 0 | 29442 |
| 180 | 10.1.2017 Features of Measurement System for Gas-Dynamic Model Tests of Rocket Complex Elements | 123 | 1142 | 0 | 0 | 0 | 29438 |
| 181 | 9.1.2017 Mathematical Simulation of Gas-Jet Control System Distributor for Launch Vehicles | 118 | 1399 | 0 | 0 | 0 | 29434 |
| 182 | 8.1.2017 Initial Imperfection Effect on Loss of Rod Stability under Axial Compression Conditions | 123 | 993 | 0 | 0 | 0 | 29430 |
| 183 | 7.1.2017 Static Approach Application in Analysis of Gas-Dynamic Parameters in Launch Vehicle Vented Bays | 114 | 860 | 0 | 0 | 0 | 29425 |
| 184 | 6.1.2017 Drought Post-Effects Satellite Monitoring | 121 | 2017 | 0 | 0 | 0 | 29420 |
| 185 | 5.1.2017 Development of Working Liquid Discontinuity Measurement Procedure and Its Certification | 114 | 1051 | 0 | 0 | 0 | 29374 |
| 186 | 4.1.2017 Basic Selection Criteria of Heat-Resistant and Thermal Protective Structures for High-Altitude Hypersonic Flying Vehicle | 121 | 1306 | 0 | 0 | 0 | 29370 |
| 187 | 3.1.2017 Development Strength Test of Modified Antares ILV | 122 | 985 | 0 | 0 | 0 | 29366 |
| 188 | 2.1.2017 Ultimate Stability Stresses in Smooth Cylindrical Skins. Dynamic Problem | 113 | 847 | 0 | 0 | 0 | 29361 |
| 189 | 1.1.2017 Methodology for Measurement Uncertainty Evaluation during Metrological Certification of Measuring Instruments | 120 | 852 | 0 | 0 | 0 | 29354 |
| 190 | 16.2.2016 Method of Coefficient for Optimization and Analysis of Operating State of Fine Filter Cases | 114 | 846 | 0 | 0 | 0 | 28333 |
| 191 | 15.2.2016 A New Method of Testing Oil-Filled Current Transformers for Explosion-Proofness | 121 | 1191 | 0 | 0 | 0 | 28331 |
| 192 | 14.2.2016 Investigation of Deformability of Carbon Plastic Panels in Moisture Absorption Process | 121 | 2304 | 0 | 0 | 0 | 28329 |
| 193 | 13.2.2016 Experience of Developing Thermometric Instruments Based on Nuclear Quadrupole Resonance | 130 | 692 | 0 | 0 | 0 | 28327 |
| 194 | 12.2.2016 The Use of Thermoelectric Technologies in Spacecraft Thermostatic Systems | 124 | 1144 | 0 | 0 | 0 | 28325 |
| 195 | 11.2.2016 Experimental Investigation into Power Characteristics of Fast-Flowrate Gas Jet Propulsion Systems | 120 | 655 | 0 | 0 | 0 | 28323 |
| 196 | 10.2.2016 Mathematical Model of High-Flowrate Electropneumatic Valve | 128 | 789 | 0 | 0 | 0 | 28321 |
| 197 | 9.2.2016 Metrological Support of Kinematic Model Testing on Zero-Gravity Test Stands | 143 | 943 | 0 | 0 | 0 | 28319 |
| 198 | 8.2.2016 Development and Validation of Program Module for Construction of Virtual Models of Real Structures in ANSYS System | 106 | 604 | 0 | 0 | 0 | 28316 |
| 199 | 7.2.2016 Analysis of Operation Modes and Selection of Chemical Current Source Included in Autonomous Electric Power Supply Systems of Self-Propelled Launcher | 121 | 787 | 0 | 0 | 0 | 28314 |
| 200 | 6.2.2016 Experimental Investigations into Results of Testing Cyclone-4 ILV Thermostating System Mating Points | 122 | 524 | 0 | 0 | 0 | 28312 |
| 201 | 5.2.2016 Creation of Technological Tooling and Testing of Cocoon-Type Cases Manufacturing Technology | 124 | 1227 | 0 | 0 | 0 | 28310 |
| 202 | 4.2.2016 Experimental Investigations of Possibility of Creating Impulse SRM with Short Operation Period | 124 | 1630 | 0 | 0 | 0 | 28308 |
| 203 | 3.2.2016 Selection of Optimal Trajectories of Spacecraft Launch Vehicles | 122 | 994 | 0 | 0 | 0 | 28306 |
| 204 | 2.2.2016 Normalization of Technical System Reliability Using Information Approach | 113 | 459 | 0 | 0 | 0 | 28304 |
| 205 | 1.2.2016 On Minimal Aerodynamic Resistance of Rotation Body at Zero Angle of Attack in Hypersonic Non-Viscous Flow | 128 | 507 | 0 | 0 | 0 | 28016 |
| 206 | 21.1.2016 Selection of Optimal Parameters of Wind Desalting System with Hydrogen Energy Storage Unit | 112 | 765 | 0 | 0 | 0 | 27643 |
| 207 | 20.1.2016 Determination of External Characteristic of Autonomous WPP for Regulation by Rotor Withdrawal from under Wind | 122 | 754 | 0 | 0 | 0 | 27641 |
| 208 | 19.1.2016 Blade Geometry for Maximal Power Coefficient and Minimal Noise Level | 114 | 451 | 0 | 0 | 0 | 27639 |
| 209 | 18.1.2016 Method of Design Evaluation of SRM Lifetime and Ensuring its Long-Term Operation | 121 | 739 | 0 | 0 | 0 | 27637 |
| 210 | 17.1.2016 Modeling of Solid Rocket Motor Starting Process | 122 | 1779 | 0 | 0 | 0 | 27635 |
| 211 | 16.1.2016 Peculiarities of Development of SRM Thrust Vector Controls at DO-5 | 102 | 811 | 0 | 0 | 0 | 27633 |
| 212 | 15.1.2016 Calculation of Solid Propellant Grain Burning Surface Using Automated 3D-Modeling Systems | 121 | 1210 | 0 | 0 | 0 | 27631 |
| 213 | 14.1.2016 Development of Powder Pressure Accumulators for Rocket Cold Start – the Most Important Condition of its Successful Realization | 126 | 723 | 0 | 0 | 0 | 27629 |
| 214 | 13.1.2016 The Impact of Diaphragm’s Shape on Gas Dynamic Flow Characteristics in Small-Size SRM Combustion Chamber | 108 | 775 | 0 | 0 | 0 | 27627 |
| 215 | 12.1.2016 Increasing Effectiveness of Meteorological Rockets when Using Hybrid Motors | 121 | 590 | 0 | 0 | 0 | 27624 |
| 216 | 11.1.2016 Methodology of Design Evaluation of Main SRM Flowrate-Thrust Characteristics after Stage Separation | 120 | 749 | 0 | 0 | 0 | 27621 |
| 217 | 10.1.2016 Development of Winding Pattern during Calculation of Composite Case Winding Programs | 115 | 886 | 0 | 0 | 0 | 27619 |
| 218 | 9.1.2016 Evaluation of SRM Intraballistic Parameters Scatter by Monte-Carlo Method | 114 | 555 | 0 | 0 | 0 | 27617 |
| 219 | 8.1.2016 Assessment of Validity of Hypothesis of Constancy of Specific Vacuum Thrust Pulse during SRM Designing and Testing | 111 | 807 | 0 | 0 | 0 | 27614 |
| 220 | 7.1.2016 Updated Design of SRM Test Rig | 114 | 820 | 0 | 0 | 0 | 27612 |
| 221 | 6.1.2016 Ensuring Solid Rocket Motor Moisture Resistance by Design | 109 | 1539 | 0 | 0 | 0 | 27610 |
| 222 | 5.1.2016 Scientific-Technical Base for Creation of Detonation Solid Rocket Motors | 108 | 1051 | 0 | 0 | 0 | 27608 |
| 223 | 4.1.2016 The Company’s Experience in Designing and Operating Special Bench Equipment for SRM Ground Tests | 109 | 499 | 0 | 0 | 0 | 27605 |
| 224 | 3.1.2016 On Peculiarities of Life Testing and Safe Storage of Solid Rocket Motors | 112 | 1552 | 0 | 0 | 0 | 27602 |
| 225 | 2.1.2016 Experience of Testing SRM Thrust Vector Controls | 119 | 1156 | 0 | 0 | 0 | 27600 |
| 226 | 1.1.2016 Solid Rocket Motors Developed by DO-5 | 145 | 681 | 0 | 0 | 0 | 27589 |
