Pub Date : 2022-03-31DOI: 10.33950/spacetech-2308-7625-2022-1-56-69
Vitaliy A. Bershadskyi, B. Sokolov, Evgeny N. Tumanin
During development of propulsion systems for launch vehicles, in order to verify the design results, standalone developmental tests of propellant supply system components were run in specially designed test setups outfitted with the required instrumentation. As an example of such work, this paper describes the experience of standalone developmental testing of operational pressurization of propellant tanks. During tests in the constructed test setups, heat and mass exchange processes were tried out with simulation of design modes of operational pressurization of propellant tanks filled with oxygen and hydrogen. As a result of these tests, a rationale was provided for selection of working mediums as the pressurization gas, design and characteristics of gas injection into propellant tanks, a method for evaluating the efficiency of the pressurization process. Empirical dependences were obtained that were used as the boundary conditions in the models for practical calculations for refining the modes and evaluating the efficiency of the propellant supply subsystem of propulsion systems. The paper calls attention to the need to use for the purpose of development of the propellant supply systems that involves computer simulations the results of such earlier work when designing advanced rocket propulsion systems. Key words: propulsion system, propellant supply system, development of pressurization process, test setup, pressurization gas, propellant components, heat and mass transfer intensity, process efficiency, liquid surface sloshing, computer simulations.
{"title":"A method for verifying the model of tank operational pressurization process during development of propellant supply system in liquid rocket engines of launch vehicle propulsion systems","authors":"Vitaliy A. Bershadskyi, B. Sokolov, Evgeny N. Tumanin","doi":"10.33950/spacetech-2308-7625-2022-1-56-69","DOIUrl":"https://doi.org/10.33950/spacetech-2308-7625-2022-1-56-69","url":null,"abstract":"During development of propulsion systems for launch vehicles, in order to verify the design results, standalone developmental tests of propellant supply system components were run in specially designed test setups outfitted with the required instrumentation.\u0000As an example of such work, this paper describes the experience of standalone developmental testing of operational pressurization of propellant tanks. During tests in the constructed test setups, heat and mass exchange processes were tried out with simulation of design modes of operational pressurization of propellant tanks filled with oxygen and hydrogen.\u0000 As a result of these tests, a rationale was provided for selection of working mediums as the pressurization gas, design and characteristics of gas injection into propellant tanks, a method for evaluating the efficiency of the pressurization process. Empirical dependences were obtained that were used as the boundary conditions in the models for practical calculations for refining the modes and evaluating the efficiency of the propellant supply subsystem of propulsion systems.\u0000The paper calls attention to the need to use for the purpose of development of the propellant supply systems that involves computer simulations the results of such earlier work when designing advanced rocket propulsion systems.\u0000\u0000Key words: propulsion system, propellant supply system, development of pressurization process, test setup, pressurization gas, propellant components, heat and mass transfer intensity, process efficiency, liquid surface sloshing, computer simulations.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"16 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-03-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116646099","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2022-03-31DOI: 10.33950/spacetech-2308-7625-2022-1-96-108
Olga K. Zhigastova, Andrey V. Smolokovskiy, S. B. Usikov
Consideration is given to a method for calculating the duration of communication sessions of the command and tracking station with a spacecraft, which enables to make an efficient use of the session time when planning control operations in order to avoid their premature performance or contingency termination in the event of constraints in the ground site coverage. Thanks to the developed method, it was possible to identify communication coverage with limited radio visibility and exclude the times of constraints from the total session duration providing a zone of stable radio exchange with SC while performing control operations, thereby increasing reliability of their performance in the communication session. The method was successfully applied in control of the Resurs-P SC constellation, where it demonstrated its capabilities and efficiency. It can be used to control other advanced SC. Key words: spacecraft, ground control complex, flight planning, session control operations, spacecraft motion model, numerical integration method.
考虑了一种计算指挥和跟踪站与航天器通信会话持续时间的方法，该方法能够在规划控制操作时有效地利用会话时间，以避免控制操作过早执行或在地面站点覆盖受限的情况下意外终止。由于开发的方法，可以在有限的无线电可见性下识别通信覆盖范围，并从总会话持续时间中排除限制时间，从而在执行控制操作时与SC提供稳定的无线电交换区域，从而提高其在通信会话中的性能可靠性。该方法成功地应用于rres - p SC星座的控制，验证了其能力和效率。关键词:航天器，地面控制综合体，飞行规划，会话控制操作，航天器运动模型，数值积分法。
{"title":"Method for calculating the duration of communication sessions with a spacecraft under constraints of the communications coverage of the command and tracking station","authors":"Olga K. Zhigastova, Andrey V. Smolokovskiy, S. B. Usikov","doi":"10.33950/spacetech-2308-7625-2022-1-96-108","DOIUrl":"https://doi.org/10.33950/spacetech-2308-7625-2022-1-96-108","url":null,"abstract":"Consideration is given to a method for calculating the duration of communication sessions of the command and tracking station with a spacecraft, which enables to make an efficient use of the session time when planning control operations in order to avoid their premature performance or contingency termination in the event of constraints in the ground site coverage. Thanks to the developed method, it was possible to identify communication coverage with limited radio visibility and exclude the times of constraints from the total session duration providing a zone of stable radio exchange with SC while performing control operations, thereby increasing reliability of their performance in the communication session. The method was successfully applied in control of the Resurs-P SC constellation, where it demonstrated its capabilities and efficiency. It can be used to control other advanced SC.\u0000Key words: spacecraft, ground control complex, flight planning, session control operations, spacecraft motion model, numerical integration method.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-03-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130688581","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2022-03-31DOI: 10.33950/spacetech-2308-7625-2022-1-46-55
Ilya S. Komarov, Valery Feldshteyn
This article describes a methodology for the computational forecasting of dynamic characteristics and test modes, implemented by vibro-shock stands of explosive action. Vibro-shock stands are widely used in ground-based experimental testing of onboard equipment of spacecraft for non-stationary broadband impact arising from the operation of pyrotechnic separation means. The principle of operation of these stands is based on the excitation of an intense non-stationary broadband vibration mode using an explosive energy source in a system of elastic-inertial elements (resonator), affecting the test object. The presented analytical technique is used to predict the test modes implemented by the vibro-shock stand in the form of a shock spectrum and for pre-test calculations in order to adjust the characteristics of the stand, ensuring the implementation of the necessary test modes. The reliability of the calculation results performed according to this technique is confirmed by experimental data. Key words: dynamic stiffness, method of initial parameters, shock loading, pyrotechnic separation means, ground experimental development, vibro-shock strength, vibro-shock stands of explosive action.
{"title":"An analytical method for the dynamic response prediction and produced test modes generated by vibro-shock test benches","authors":"Ilya S. Komarov, Valery Feldshteyn","doi":"10.33950/spacetech-2308-7625-2022-1-46-55","DOIUrl":"https://doi.org/10.33950/spacetech-2308-7625-2022-1-46-55","url":null,"abstract":"This article describes a methodology for the computational forecasting of dynamic characteristics and test modes, implemented by vibro-shock stands of explosive action. Vibro-shock stands are widely used in ground-based experimental testing of onboard equipment of spacecraft for non-stationary broadband impact arising from the operation of pyrotechnic separation means. The principle of operation of these stands is based on the excitation of an intense non-stationary broadband vibration mode using an explosive energy source in a system of elastic-inertial elements (resonator), affecting the test object. The presented analytical technique is used to predict the test modes implemented by the vibro-shock stand in the form of a shock spectrum and for pre-test calculations in order to adjust the characteristics of the stand, ensuring the implementation of the necessary test modes. The reliability of the calculation results performed according to this technique is confirmed by experimental data. \u0000Key words: dynamic stiffness, method of initial parameters, shock loading, pyrotechnic separation means, ground experimental development, vibro-shock strength, vibro-shock stands of explosive action.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"20 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-03-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125557450","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2022-03-31DOI: 10.33950/spacetech-2308-7625-2022-1-80-95
Vladimir V. Коshlakov, Kirill V. Gotovtsev, L. Zakharenkov, A. V. Karevskiy, Evgeny N. Kiryushin, Aleksandr S. Lovtsov, Yu. A. Oshev, Aleksandr V. Semenkin, Aleksandr E. Solodukhin, Sergey Yu. Fedotov, S. Y. Fedyunin, Andrey G. Tsvetkov
Expanding space exploration in near-Earth space and deep space calls for an increase in power supply of space vehicles to a level of hundreds of kilowatts and higher. Pre-requisite for successful implementation of works on development of power propulsion systems of such power level, including those with nuclear energy sources, is availability of a full-scale experimental test bench equipment. A unique experimental test bench has been built and is successfully operating at JSC «Keldysh Research Center», which allows performing both research and developmental tests of key components of high-performance power and propulsion systems under conditions close to nominal operating conditions. The article describes the main components of JSC «Keldysh Research Center» test bench equipment, presents some results of the work fulfilled on it, outlines prospects for its furtherance and use in development of space high-performance power and propulsion systems. Key words: testing, ground developmental testing, power conversion system, test bench equipment, electric propulsion, power and propulsion system.
{"title":"TEST BENCH EQUIPMENT OF KELDYSH RESEARCH CENTRE \u0000FOR TESTING HIGH-PERFORMANCE POWER AND PROPULSION SYSTEMS","authors":"Vladimir V. Коshlakov, Kirill V. Gotovtsev, L. Zakharenkov, A. V. Karevskiy, Evgeny N. Kiryushin, Aleksandr S. Lovtsov, Yu. A. Oshev, Aleksandr V. Semenkin, Aleksandr E. Solodukhin, Sergey Yu. Fedotov, S. Y. Fedyunin, Andrey G. Tsvetkov","doi":"10.33950/spacetech-2308-7625-2022-1-80-95","DOIUrl":"https://doi.org/10.33950/spacetech-2308-7625-2022-1-80-95","url":null,"abstract":"Expanding space exploration in near-Earth space and deep space calls for an increase in power supply of space vehicles to a level of hundreds of kilowatts and higher. Pre-requisite for successful implementation of works on development of power propulsion systems of such power level, including those with nuclear energy sources, is availability of a full-scale experimental test bench equipment. A unique experimental test bench has been built and is successfully operating at JSC «Keldysh Research Center», which allows performing both research and developmental tests of key components of high-performance power and propulsion systems under conditions close to nominal operating conditions. The article describes the main components of JSC «Keldysh Research Center» test bench equipment, presents some results of the work fulfilled on it, outlines prospects for its furtherance and use in development of space high-performance power and propulsion systems.\u0000Key words: testing, ground developmental testing, power conversion system, test bench equipment, electric propulsion, power and propulsion system.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"139 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-03-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131702724","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2022-03-31DOI: 10.33950/spacetech-2308-7625-2022-1-109-124
V. Kovtun
The paper presents methods of providing power resources for the mission of the Yamal-100 spacecraft from the secondary onboard power supply sources — nickel-hydrogen storage batteries. For the first time in the world practice of using metal-hydrogen electrochemical batteries installed in a common gas manifold a ~10-years operational life in orbit has been achieved for batteries operated onboard a geostationary satellite. A decline in power capacity of storage batteries could result in early termination of the spacecraft mission. Therefore, the energy resource of the storage battery was maintained through proactive management consisting of prediction and active control. The methods that were developed for continuous observation in the form of monitoring and diagnostics of the storage batteries status including estimation of the current discharge energy capacity made it possible to predict further degradation loss under conditions of insufficient power for the storage batteries cooling equipment. The active control consisted in using methods aimed at providing optimal operating conditions, fending off a potential development of an anomalous thermal situation within the electrochemical reaction zone, and regenerating the energy capacity. The control furthermore used the synergy effect produced by secondary energy interrelationships between onboard systems. This made it possible to meet the batteries operational life requirements under exposure to an unfavorable external factor in the form of an increasing heat impact on the batteries temperature control equipment. The increase in thermal load was caused by re-reflection of a portion of the luminous flux from structural elements of the spacecraft and an increase in solar absorption factor (aging) of thermal control coatings. Key words: spacecraft, control process, nickel-hydrogen battery, provision of resources, energy capacity, proactive control, synergy.
{"title":"Procedures for cognitive and synergetic observation and proactive control of power capacity of nickel-hydrogen storage batteries onboard a geostationary spacecraft","authors":"V. Kovtun","doi":"10.33950/spacetech-2308-7625-2022-1-109-124","DOIUrl":"https://doi.org/10.33950/spacetech-2308-7625-2022-1-109-124","url":null,"abstract":"The paper presents methods of providing power resources for the mission of the Yamal-100 spacecraft from the secondary onboard power supply sources — nickel-hydrogen storage batteries. For the first time in the world practice of using metal-hydrogen electrochemical batteries installed in a common gas manifold a ~10-years operational life in orbit has been achieved for batteries operated onboard a geostationary satellite. A decline in power capacity of storage batteries could result in early termination of the spacecraft mission. Therefore, the energy resource of the storage battery was maintained through proactive management consisting of prediction and active control. The methods that were developed for continuous observation in the form of monitoring and diagnostics of the storage batteries status including estimation of the current discharge energy capacity made it possible to predict further degradation loss under conditions of insufficient power for the storage batteries cooling equipment. The active control consisted in using methods aimed at providing optimal operating conditions, fending off a potential development of an anomalous thermal situation within the electrochemical reaction zone, and regenerating the energy capacity. The control furthermore used the synergy effect produced by secondary energy interrelationships between onboard systems. This made it possible to meet the batteries operational life requirements under exposure to an unfavorable external factor in the form of an increasing heat impact on the batteries temperature control equipment. The increase in thermal load was caused by re-reflection of a portion of the luminous flux from structural elements of the spacecraft and an increase in solar absorption factor (aging) of thermal control coatings.\u0000Key words: spacecraft, control process, nickel-hydrogen battery, provision of resources, energy capacity, proactive control, synergy.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"430 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-03-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132135807","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2022-03-31DOI: 10.33950/spacetech-2308-7625-2022-1-125-143
Vadim V. Mironov, M. A. Tolkach
The problems of assessing a risk of damaging a spacecraft by meteoroids and space debris are fairly important. The probability of not damaging a SC depends on the properties of its structural elements, particle flux density and velocity of hypervelocity meteoroids and/or space debris. This article offers an analytical review of papers (primarily foreign ones) assessing velocity of meteoroids based on the experimental evidence. Stated are general requirements for experimental data acceptable for acquiring reliable meteoroid velocity data. Compared are meteoroid velocity values obtained from different models, including the data presented in the current national domestic standards. Based on the analysis of experimental data accumulated so far, the most probable values of meteoroid and space debris velocities to be used in ballistic limit equations have been proposed. Key words: meteoroid, space debris, spacecraft shielding against meteoroids, meteoroid environment, meteoroid flux density and velocity.
{"title":"Velocity and distribution velocity of meteoroids and space debris in near-earth space","authors":"Vadim V. Mironov, M. A. Tolkach","doi":"10.33950/spacetech-2308-7625-2022-1-125-143","DOIUrl":"https://doi.org/10.33950/spacetech-2308-7625-2022-1-125-143","url":null,"abstract":"The problems of assessing a risk of damaging a spacecraft by meteoroids and space debris are fairly important. The probability of not damaging a SC depends on the properties of its structural elements, particle flux density and velocity of hypervelocity meteoroids and/or space debris.\u0000This article offers an analytical review of papers (primarily foreign ones) assessing velocity of meteoroids based on the experimental evidence.\u0000Stated are general requirements for experimental data acceptable for acquiring reliable meteoroid velocity data. Compared are meteoroid velocity values obtained from different models, including the data presented in the current national domestic standards. Based on the analysis of experimental data accumulated so far, the most probable values of meteoroid and space debris velocities to be used in ballistic limit equations have been proposed.\u0000Key words: meteoroid, space debris, spacecraft shielding against meteoroids, meteoroid environment, meteoroid flux density and velocity.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"PAMI-6 6","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-03-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114129893","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2022-03-31DOI: 10.33950/spacetech-2308-7625-2022-1-70-79
Vladimir I. Marinin, Sergey M. Zhurikhin, D. Kireev, Dmitry Andreev, N. Andreeva, N. I. Kopyl, Aleksandr N. Senkovskiy, Sergey F. Ilyushenkov, S. N. Churkin
This article discusses capabilities of a new special-purpose software-measuring system for monitoring flatness of solar array (SA) wings. The performance data and specifics of work are presented. The specifics of measurement of SA wings flatness are described. The allowable deviations from flatness of SA wings of the science power module (SPM) as part of the International Space station are given. The composition of the measuring complex is developed. The visual approach of making plans for testing methods and measurement techniques based on visual components is considered in detail. The elements from which the measurement plans are built are considered. Sample plans for verification procedures, methods of measuring flatness of the front and back wing surfaces are provided. Basic requirements for processing of measurement results which are stored for compatibility with the old manual approach of measurements are specified. Basic measurement processing algorithms for calculation of general and local wing out-of-flatness are provided. Key words: SA wing, solar array wing, meter, component model, overview, general out-of-flatness, local out-of-flatness.
{"title":"Automated monitoring of flatness of solar array wings","authors":"Vladimir I. Marinin, Sergey M. Zhurikhin, D. Kireev, Dmitry Andreev, N. Andreeva, N. I. Kopyl, Aleksandr N. Senkovskiy, Sergey F. Ilyushenkov, S. N. Churkin","doi":"10.33950/spacetech-2308-7625-2022-1-70-79","DOIUrl":"https://doi.org/10.33950/spacetech-2308-7625-2022-1-70-79","url":null,"abstract":"This article discusses capabilities of a new special-purpose software-measuring system for monitoring flatness of solar array (SA) wings. The performance data and specifics of work are presented.\u0000The specifics of measurement of SA wings flatness are described. The allowable deviations from flatness of SA wings of the science power module (SPM) as part of the International Space station are given.\u0000The composition of the measuring complex is developed. The visual approach of making plans for testing methods and measurement techniques based on visual components is considered in detail. The elements from which the measurement plans are built are considered. Sample plans for verification procedures, methods of measuring flatness of the front and back wing surfaces are provided.\u0000Basic requirements for processing of measurement results which are stored for compatibility with the old manual approach of measurements are specified.\u0000Basic measurement processing algorithms for calculation of general and local wing out-of-flatness are provided.\u0000Key words: SA wing, solar array wing, meter, component model, overview, general out-of-flatness, local out-of-flatness.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"17 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-03-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128778246","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2022-03-31DOI: 10.33950/spacetech-2308-7625-2022-1-36-45
M. A. Gorodetskiy, K. V. Mikhailovskiy, S. Reznik
The paper discusses the feasibility of replacing conventional sandwich panel with carbon fiber skins and aluminum honeycomb core in the structure of an Earth remote sensing satellite bus. Thermal loading conditions for sun-synchronous orbit were considered and math simulations were run for stress-strain behavior of a satellite bus element built of the proposed versions of sandwich composite panels. Simulations results might be of interest for design of ultra-lightweight structures of the satellite bus, solar arrays and antenna reflector. Key words: Earth remote sensing spacecraft, Sun-synchronous orbit, math simulations, polymer composite materials.
{"title":"Determining parameters of sandwich composite panels for earth remote sensing satellite bus","authors":"M. A. Gorodetskiy, K. V. Mikhailovskiy, S. Reznik","doi":"10.33950/spacetech-2308-7625-2022-1-36-45","DOIUrl":"https://doi.org/10.33950/spacetech-2308-7625-2022-1-36-45","url":null,"abstract":"The paper discusses the feasibility of replacing conventional sandwich panel with carbon fiber skins and aluminum honeycomb core in the structure of an Earth remote sensing satellite bus. Thermal loading conditions for sun-synchronous orbit were considered and math simulations were run for stress-strain behavior of a satellite bus element built of the proposed versions of sandwich composite panels. Simulations results might be of interest for design of ultra-lightweight structures of the satellite bus, solar arrays and antenna reflector.\u0000Key words: Earth remote sensing spacecraft, Sun-synchronous orbit, math simulations, polymer composite materials.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"134 5-6","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-03-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"120909603","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2022-03-15DOI: 10.33950/spacetech-2308-7625-2022-1-5-20
B. Katorgin, V. Lopota, P. Levochkin, V. Chvanov, R. Samitov, B. Sokolov, I. M. Filippov, R. Murtazin, Igor A. Kryukov, N. Tupitsyn, Yury P. Ulybyshev, Dmitry S. Firstaev, A. V. Kiselev
The paper presents the results of an independent design study into the feasibility of developing for the Super-Heavy Space Rocket (SHSR) with 140–170 ton payload capacity a modular Launch Vehicle (LV) in the form of a tri-pack cluster of three two-stage medium LVs Soyuz-5 and three side-mounted bi-pack clusters based on coupling together the first stages of LV Soyuz-5 based on NPO Energomash oxygen-kerosene main engines RD171MV, RD180, RD191M and a four-chamber version of the RD120 engine. In addition to this, the paper discusses the feasibility of using the tri-pack cluster from the SHSR as a standalone Heavy LV with an increased payload capacity (50–60tons) to assure its more frequent use, and thus upkeep the operational reliability of the more powerful SHSR. The paper demonstrates the feasibility of designing the second-phase reusable versions of the first-stage clusters for SHSR and Heavy LV, as well as the feasibility of manned lunar missions using not two, but only one SHSR. Key words: integrated launch vehicle, launch vehicle, main engine, tri-pack cluster, bi-pack cluster, crew transportation spacecraft, lunar take-off and landing vehicle.
{"title":"POSSIBLE ENGINEERING DESIGN SOLUTIONS FOR DEVELOPENT OF HEAVY AND SUPER-HEAVY OXYGEN-KEROSENE SPACE ROCKET","authors":"B. Katorgin, V. Lopota, P. Levochkin, V. Chvanov, R. Samitov, B. Sokolov, I. M. Filippov, R. Murtazin, Igor A. Kryukov, N. Tupitsyn, Yury P. Ulybyshev, Dmitry S. Firstaev, A. V. Kiselev","doi":"10.33950/spacetech-2308-7625-2022-1-5-20","DOIUrl":"https://doi.org/10.33950/spacetech-2308-7625-2022-1-5-20","url":null,"abstract":"The paper presents the results of an independent design study into the feasibility of developing for the Super-Heavy Space Rocket (SHSR) with 140–170 ton payload capacity a modular Launch Vehicle (LV) in the form of a tri-pack cluster of three two-stage medium LVs Soyuz-5 and three side-mounted bi-pack clusters based on coupling together the first stages of LV Soyuz-5 based on NPO Energomash oxygen-kerosene main engines RD171MV, RD180, RD191M and a four-chamber version of the RD120 engine. In addition to this, the paper discusses the feasibility of using the tri-pack cluster from the SHSR as a standalone Heavy LV with an increased payload capacity (50–60tons) to assure its more frequent use, and thus upkeep the operational reliability of the more powerful SHSR. The paper demonstrates the feasibility of designing the second-phase reusable versions of the first-stage clusters for SHSR and Heavy LV, as well as the feasibility of manned lunar missions using not two, but only one SHSR.\u0000Key words: integrated launch vehicle, launch vehicle, main engine, tri-pack cluster, bi-pack cluster, crew transportation spacecraft, lunar take-off and landing vehicle.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"53 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-03-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133699107","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2022-03-15DOI: 10.33950/spacetech-2308-7625-2022-1-21-35
Mikhail Yu. Belyaev, Sergey I. Kudryavtsev, Dmitry Rulev, A. Krylov, Y. Batyrev, Sergey N. Alyamovskiy
The paper discusses methodological support for space experiment Vektor-T slated to be conducted in the Russian Segment of the International Space Station (ISS RS). The objective of the space experiment is to obtain additional information needed to improve the ISS motion control techniques based on the data from tracking the drift of calibrated solid body inside the ISS pressurized cabin. The paper provides the results of estimation of possible drift trajectories depending on the condition of the Earth atmosphere, positions of the steerable structural elements of the ISS and the location of the launch point with respect to the ISS center of mass. It reviews methodological issues involved in planning the space experiment sessions, their conduct and processing of the results. Key words: space experiment, micro-accelerations, pressurized cabin, calibrated body, drift.
{"title":"A study of possible drift trajectories of a calibrated solid body inside the ISS pressurized cabin during the conduct of experiment Vector-T","authors":"Mikhail Yu. Belyaev, Sergey I. Kudryavtsev, Dmitry Rulev, A. Krylov, Y. Batyrev, Sergey N. Alyamovskiy","doi":"10.33950/spacetech-2308-7625-2022-1-21-35","DOIUrl":"https://doi.org/10.33950/spacetech-2308-7625-2022-1-21-35","url":null,"abstract":"The paper discusses methodological support for space experiment Vektor-T slated to be conducted in the Russian Segment of the International Space Station (ISS RS). The objective of the space experiment is to obtain additional information needed to improve the ISS motion control techniques based on the data from tracking the drift of calibrated solid body inside the ISS pressurized cabin. The paper provides the results of estimation of possible drift trajectories depending on the condition of the Earth atmosphere, positions of the steerable structural elements of the ISS and the location of the launch point with respect to the ISS center of mass. It reviews methodological issues involved in planning the space experiment sessions, their conduct and processing of the results.\u0000Key words: space experiment, micro-accelerations, pressurized cabin, calibrated body, drift.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"14 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-03-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132325421","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
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