Pub Date : 2019-09-30DOI: 10.33950/SPACETECH-2308-7625-2019-3-109-120
Boris F. Zaretskiy, A. Guzenberg, Igor A. Shangin
Life support for first manned spaceflights was based on supplies of consumables. Crew life support systems based on supplies of water and oxygen, in spite of their simplicity, are extremely inefficient in orbital space missions and are unfeasible in deep space missions because of mass and volume constraints. Therefore, there are currently developed and are to be used on space stations the life support systems that are based on chemical and physical regeneration of water and oxygen extracted from human waste. In view of further advances in long-duration orbital stations, and the prospects of establishment of planetary outposts and deep space exploration, the problem of constructing an automated system for controlling a suite of regenerative LSS becomes urgent. The complexity of solving the problem of constructing an efficient control system in this case owes to the existence of a large number of effectiveness criteria. The paper proposes a system of consolidated global efficiency criteria, which allows to break up this problem into a series of sub-problems of optimization in order to solve this problem. The proposed criteria are longevity, cost, comfort. The paper presents a series of specific examples of using the proposed principles with necessary generalizations. Key words: space life support systems, atmosphere revitalization equipment, automated control system, global generalized efficiency criteria, longevity, cost, comfort.
{"title":"Жизнеобеспечение экипажа пилотируемого космического объекта, проблемы управления","authors":"Boris F. Zaretskiy, A. Guzenberg, Igor A. Shangin","doi":"10.33950/SPACETECH-2308-7625-2019-3-109-120","DOIUrl":"https://doi.org/10.33950/SPACETECH-2308-7625-2019-3-109-120","url":null,"abstract":"Life support for first manned spaceflights was based on supplies of consumables. Crew life support systems based on supplies of water and oxygen, in spite of their simplicity, are extremely inefficient in orbital space missions and are unfeasible in deep space missions because of mass and volume constraints. Therefore, there are currently developed and are to be used on space stations the life support systems that are based on chemical and physical regeneration of water and oxygen extracted from human waste. In view of further advances in long-duration orbital stations, and the prospects of establishment of planetary outposts and deep space exploration, the problem of constructing an automated system for controlling a suite of regenerative LSS becomes urgent. The complexity of solving the problem of constructing an efficient control system in this case owes to the existence of a large number of effectiveness criteria. \u0000 The paper proposes a system of consolidated global efficiency criteria, which allows to break up this problem into a series of sub-problems of optimization in order to solve this problem. The proposed criteria are longevity, cost, comfort. The paper presents a series of specific examples of using the proposed principles with necessary generalizations.\u0000 Key words: space life support systems, atmosphere revitalization equipment, automated control system, global generalized efficiency criteria, longevity, cost, comfort.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"28 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-09-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128170012","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 : 2019-09-30DOI: 10.33950/SPACETECH-2308-7625-2019-3-66-76
V. Platonov, A. Sumarokov
The paper discusses a math simulation of an Earth remote sensing spacecraft attitude control loop dynamics during imaging. The spacecraft is intended for imaging a swath along the flight path, stereo imaging, area and corridor imaging at an angle to the flight path. To provide the spacecraft with high maneuverability during imaging it is assumed that the control loop uses as its effectors one-axis powered gyros. Studies were conducted of the feasibility of using this spacecraft for performing a series of area and corridor surveys. Selected for the attitude control loop were the control parameters which allow meeting the specified performance. Simulation results have confirmed that the spacecraft is capable of performing these kinds of surveys and meeting the specified accuracy levels. Key words: Earth remote sensing spacecraft, control moment gyros, single-axis powered gyros, kinetic momentum, stabilization, angular rate, precession.
{"title":"Math simulation of attitude stabilization accuracy and performance for an earth remote sensing spacecraft","authors":"V. Platonov, A. Sumarokov","doi":"10.33950/SPACETECH-2308-7625-2019-3-66-76","DOIUrl":"https://doi.org/10.33950/SPACETECH-2308-7625-2019-3-66-76","url":null,"abstract":"The paper discusses a math simulation of an Earth remote sensing spacecraft attitude control loop dynamics during imaging. The spacecraft is intended for imaging a swath along the flight path, stereo imaging, area and corridor imaging at an angle to the flight path. To provide the spacecraft with high maneuverability during imaging it is assumed that the control loop uses as its effectors one-axis powered gyros. Studies were conducted of the feasibility of using this spacecraft for performing a series of area and corridor surveys. Selected for the attitude control loop were the control parameters which allow meeting the specified performance. Simulation results have confirmed that the spacecraft is capable of performing these kinds of surveys and meeting the specified accuracy levels. \u0000Key words: Earth remote sensing spacecraft, control moment gyros, single-axis powered gyros, kinetic momentum, stabilization, angular rate, precession.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"55 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-09-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126589723","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 : 2019-09-30DOI: 10.33950/SPACETECH-2308-7625-2019-3-89-97
S. Bronnikov, S. Kuzin, Irina A. Rozhkova
The article deals with the structure of the simulator for the training of the space station (SS) crew activity in an emergency situation. A brief history of the matter is given. The purpose of the simulator is to provide the crew with the possibility to carry out training (having the required correspondence of real) activities to parry emergency situations while ensuring the minimum of total cost of simulator ownership. The functions and tasks of the simulator that follow from the stated goal are given. The simulator is considered as a complex distributed information system including sets of data: • goals and tasks; • structure of the simulator; • conditions: requirements, external and internal factors affecting the creation and functioning of the simulator. The structure of the simulator is presented in the form of the following sets: • staf; • technical means of the simulator; • composition of the elements of the simulator. The staff of the simulator includes administrators, instructors, mission control centers (MCC) operators, crew. Technical means of the simulator are presented in the form of a set, which includes set of hardware, set of software tools and a database. To create the simulator, the borrowed means of the space complex (SC) are used: the communication system, the local networks of the SS and MCC, participating in flight management, and the global Internet. The structure and tasks of the simulator software are considered, including the software of the on-board server, ground servers, the on-board mobile terminal, the user's ground-based workstation. The simulator scheme includes on-board and ground subsystems interacting with each other using the standard ground-to-board communication system. The presented simulator can be used for working out of actions of the personnel for liquidation of emergency situations on complex objects, including a large number of personnel and technical means. Key words: simulator structure, training, emergency situation, crew, flight control center, simulator software.
{"title":"Onboard simulator for emergency situations training of the space station crew","authors":"S. Bronnikov, S. Kuzin, Irina A. Rozhkova","doi":"10.33950/SPACETECH-2308-7625-2019-3-89-97","DOIUrl":"https://doi.org/10.33950/SPACETECH-2308-7625-2019-3-89-97","url":null,"abstract":"The article deals with the structure of the simulator for the training of the space station (SS) crew activity in an emergency situation. A brief history of the matter is given. The purpose of the simulator is to provide the crew with the possibility to carry out training (having the required correspondence of real) activities to parry emergency situations while ensuring the minimum of total cost of simulator ownership. The functions and tasks of the simulator that follow from the stated goal are given.\u0000The simulator is considered as a complex distributed information system including sets of data:\u0000• goals and tasks;\u0000• structure of the simulator;\u0000• conditions: requirements, external and internal factors affecting the creation and functioning of the simulator.\u0000The structure of the simulator is presented in the form of the following sets:\u0000• staf;\u0000• technical means of the simulator;\u0000• composition of the elements of the simulator.\u0000The staff of the simulator includes administrators, instructors, mission control centers (MCC) operators, crew. Technical means of the simulator are presented in the form of a set, which includes set of hardware, set of software tools and a database. To create the simulator, the borrowed means of the space complex (SC) are used: the communication system, the local networks of the SS and MCC, participating in flight management, and the global Internet.\u0000The structure and tasks of the simulator software are considered, including the software of the on-board server, ground servers, the on-board mobile terminal, the user's ground-based workstation. The simulator scheme includes on-board and ground subsystems interacting with each other using the standard ground-to-board communication system.\u0000The presented simulator can be used for working out of actions of the personnel for liquidation of emergency situations on complex objects, including a large number of personnel and technical means.\u0000Key words: simulator structure, training, emergency situation, crew, flight control center, simulator software.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"28 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-09-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131808682","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 : 2019-09-30DOI: 10.33950/SPACETECH-2308-7625-2019-3-98-108
Andrey Vladimirovich Yaskevich
The new peripheral docking mechanism is part of a docking unit designed in compli-ance with the International Docking System Standard (IDSS). The mechanism kinematics is based on the Gough-Stewart platform. Spring mechanisms are used for transformation of spacecraft approach kinetic energy. However, traditional damping is replaced by energy ac-cumulation. Therefore, the design includes new devices. The dynamic math model of the dock-ing mechanism described in this paper takes into account its main features – kinematics, inertia properties and generation of internal active forces by separate devices. Along with spacecraft motion equations and algorithms of docking unit contact interaction analysis, this model is part of a docking math model used for the analysis of kinematics and dynamics processes from the first contact to the end of retraction. Key words: spacecraft, docking mechanism, dynamics equations.
{"title":"Математическая модель динамики периферийного стыковочного механизма с накоплением кинетической энергии сближения космических аппаратов","authors":"Andrey Vladimirovich Yaskevich","doi":"10.33950/SPACETECH-2308-7625-2019-3-98-108","DOIUrl":"https://doi.org/10.33950/SPACETECH-2308-7625-2019-3-98-108","url":null,"abstract":"The new peripheral docking mechanism is part of a docking unit designed in compli-ance with the International Docking System Standard (IDSS). The mechanism kinematics is based on the Gough-Stewart platform. Spring mechanisms are used for transformation of spacecraft approach kinetic energy. However, traditional damping is replaced by energy ac-cumulation. Therefore, the design includes new devices. The dynamic math model of the dock-ing mechanism described in this paper takes into account its main features – kinematics, inertia properties and generation of internal active forces by separate devices. Along with spacecraft motion equations and algorithms of docking unit contact interaction analysis, this model is part of a docking math model used for the analysis of kinematics and dynamics processes from the first contact to the end of retraction.\u0000Key words: spacecraft, docking mechanism, dynamics equations.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"68 4 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-09-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129328449","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 : 2019-06-30DOI: 10.33950/SPACETECH-2308-7625-2019-2-55-66
A. Yaskevich, I. Chernyshev
Spacecraft docking is a controlled on-orbit mechanical assembly process realized using active and passive docking units. The docking mechanism of the active unit provides capture conditions, attenuation of active spacecraft approach energy, alignment and retraction of the docking units before their hard connection. A kinematical scheme of a new peripheral docking mechanism is considered in this paper. Instead of energy damping, it is based on energy accumulation using springs with controlled recoil blocking. The blocking is activated before docking and keeps the docking mechanism in its initial position. On the first contact signal, the blocking is switched off releasing the energy of compressed springs for quick forward moving of the docking ring and improving capture. The blocking is activated again after capture and approach energy is accumulated by the springs without returning to the mechanical system. Avoiding contacts of docking mechanism links between each other and with the docking unit body is important for peripheral mechanisms due to their design. A procedure for choosing parameters of an energy accumulator that allows attenuating a max permissible energy without link contacts and without exceeding the max permissible value of the axial interface load is considered here. Key words: spacecraft, docking, docking mechanism.
{"title":"Choice of energy accumulator parameters for a new peripheral docking mechanism","authors":"A. Yaskevich, I. Chernyshev","doi":"10.33950/SPACETECH-2308-7625-2019-2-55-66","DOIUrl":"https://doi.org/10.33950/SPACETECH-2308-7625-2019-2-55-66","url":null,"abstract":"Spacecraft docking is a controlled on-orbit mechanical assembly process realized using active and passive docking units. The docking mechanism of the active unit provides capture conditions, attenuation of active spacecraft approach energy, alignment and retraction of the docking units before their hard connection. A kinematical scheme of a new peripheral docking mechanism is considered in this paper. Instead of energy damping, it is based on energy accumulation using springs with controlled recoil blocking. The blocking is activated before docking and keeps the docking mechanism in its initial position. On the first contact signal, the blocking is switched off releasing the energy of compressed springs for quick forward moving of the docking ring and improving capture. The blocking is activated again after capture and approach energy is accumulated by the springs without returning to the mechanical system. Avoiding contacts of docking mechanism links between each other and with the docking unit body is important for peripheral mechanisms due to their design. A procedure for choosing parameters of an energy accumulator that allows attenuating a max permissible energy without link contacts and without exceeding the max permissible value of the axial interface load is considered here.\u0000Key words: spacecraft, docking, docking mechanism.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"87 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-06-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124369959","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 : 2019-06-30DOI: 10.33950/SPACETECH-2308-7625-2019-2-81-90
B. Sokolov, Pavel A. Shcherbina, Ivan B. Sishko, Aleksandr V. Shipovskiy Aleksandr, A. Lyapin, A. Konovalova
The paper demonstrates the feasibility of using iodine as propellant for thrusters with closed electron drift and its economic viability. It describes a test setup for running experiments. It provides the results of experimental studies of the stationary plasma thruster using iodine as its propellant with xenon gas-passage hollow cathode, as well as of the operational mode of the thruster where a mixture of xenon and iodine is used. During tests gas dynamic and electrical properties of the thruster were analyzed. Thermal conditions in the iodine storage and supply system were studied. Conclusions were drawn on how the test object could be improved and upgraded. The paper describes the option to use a thermionic non-flow cathode as the compensator cathode for the operation of the iodine thruster. The paper provides the results of an experimental study of the prototype non-flow compensator cathode in diode mode. Based on the results of the studies an experimental facility was built for testing a thruster with non-flow compensator cathode. Key words: cathode, compensator cathode, thruster with closed electron drift, stationary plasma thruster, iodine.
{"title":"Experimental studies of iodine stationary plasma thruster","authors":"B. Sokolov, Pavel A. Shcherbina, Ivan B. Sishko, Aleksandr V. Shipovskiy Aleksandr, A. Lyapin, A. Konovalova","doi":"10.33950/SPACETECH-2308-7625-2019-2-81-90","DOIUrl":"https://doi.org/10.33950/SPACETECH-2308-7625-2019-2-81-90","url":null,"abstract":"The paper demonstrates the feasibility of using iodine as propellant for thrusters with closed electron drift and its economic viability. It describes a test setup for running experiments. It provides the results of experimental studies of the stationary plasma thruster using iodine as its propellant with xenon gas-passage hollow cathode, as well as of the operational mode of the thruster where a mixture of xenon and iodine is used. During tests gas dynamic and electrical properties of the thruster were analyzed. Thermal conditions in the iodine storage and supply system were studied. Conclusions were drawn on how the test object could be improved and upgraded. The paper describes the option to use a thermionic non-flow cathode as the compensator cathode for the operation of the iodine thruster. The paper provides the results of an experimental study of the prototype non-flow compensator cathode in diode mode. Based on the results of the studies an experimental facility was built for testing a thruster with non-flow compensator cathode. \u0000Key words: cathode, compensator cathode, thruster with closed electron drift, stationary plasma thruster, iodine.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"58 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-06-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121314460","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 : 2019-06-30DOI: 10.33950/SPACETECH-2308-7625-2019-2-5-13
Yury N. Makushenko, R. Murtazin, D. S. Zarubin
The success of the International Space Station project has inspired the partners to review possible steps in space exploration beyond Low Earth Orbit. The Moon, Mars, or asteroids - the priorities of partners’ national programs could be different. Understanding of the deep space exploration viability by the joint team led partners to consideration regarding Cis-Lunar Spaceport which will become a Spaceport and should facilitate the implementation of the national programs. At the present time a concept of the Spaceport located on high-elliptical lunar orbit is being widely discussed. The Spaceport is considered to be a transportation hub supporting deep space exploration programs: missions to the Moon, asteroids, Mars and other natural and artificial objects. Different schemes of crew delivery to the lunar surface using Lunar Lander based and serviced at the Spaceport are compared in the paper. The Spaceport utilization significantly reduces transportation operations time limits and provides conditions for reusable lunar spacecraft implementation. Key words: Cislunar spaceport, high-elliptical lunar orbit, ascent module, descant module, reusable lunar crew vehicle.
{"title":"The cislunar spaceport for the crew delivery to the lunar surface","authors":"Yury N. Makushenko, R. Murtazin, D. S. Zarubin","doi":"10.33950/SPACETECH-2308-7625-2019-2-5-13","DOIUrl":"https://doi.org/10.33950/SPACETECH-2308-7625-2019-2-5-13","url":null,"abstract":"The success of the International Space Station project has inspired the partners to review possible steps in space exploration beyond Low Earth Orbit. The Moon, Mars, or asteroids - the priorities of partners’ national programs could be different. Understanding of the deep space exploration viability by the joint team led partners to consideration regarding Cis-Lunar Spaceport which will become a Spaceport and should facilitate the implementation of the national programs. \u0000At the present time a concept of the Spaceport located on high-elliptical lunar orbit is being widely discussed. The Spaceport is considered to be a transportation hub supporting deep space exploration programs: missions to the Moon, asteroids, Mars and other natural and artificial objects. \u0000Different schemes of crew delivery to the lunar surface using Lunar Lander based and serviced at the Spaceport are compared in the paper. The Spaceport utilization significantly reduces transportation operations time limits and provides conditions for reusable lunar spacecraft implementation.\u0000 Key words: Cislunar spaceport, high-elliptical lunar orbit, ascent module, descant module, reusable lunar crew vehicle.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"19 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-06-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125260821","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 : 2019-06-30DOI: 10.33950/SPACETECH-2308-7625-2019-2-67-80
B. Sokolov, N. Tupitsyn
The paper presents results of engineering studies and research and development efforts at RSC Energia to analyze and prove the feasibility of using the mass-produced oxygen-hydrocarbon engine 11D58M with 8.5 ton-force thrust as a basis for development of a high-performance multifunctional rocket engine with oxygen cooling and 5 ton-force thrust, which is optimal for upper stages (US), embodying a system that does not include a gas generator. The multi-functionality of the engine implies including in it additional units supporting some functions that are important for US, such as feeding propellant from US tanks to the engine after flying in zero gravity, autonomous control of the engine automatic equipment to support its firing, shutdown, adjustments during burn and emergency protection in case of off-nominal operation, as well as generating torques for controlling the US attitude and stabilizing it during coasting, etc. Replacing conventional engine chamber cooling that uses high-boiling hydrocarbon fuel with the innovative oxygen cooling makes it possible to get rid of the internal film cooling circuits and eliminate their attendant losses of fuel, while the use of the oxygen gasified in the cooling circuit of the chamber to drive the turbo pump assembly permits to design an engine that does not have a gas generator. Key words: Multifunctional rocket engine, oxygen cooling, gas-generatorless design, upper stage.
{"title":"A study into the feasibility of using the oxygen-hydrocarbon engine 11D58M as a basis for development of a high-performance multifunctional gas-generatorless rocket engine with oxygen cooling","authors":"B. Sokolov, N. Tupitsyn","doi":"10.33950/SPACETECH-2308-7625-2019-2-67-80","DOIUrl":"https://doi.org/10.33950/SPACETECH-2308-7625-2019-2-67-80","url":null,"abstract":"The paper presents results of engineering studies and research and development efforts at RSC Energia to analyze and prove the feasibility of using the mass-produced oxygen-hydrocarbon engine 11D58M with 8.5 ton-force thrust as a basis for development of a high-performance multifunctional rocket engine with oxygen cooling and 5 ton-force thrust, which is optimal for upper stages (US), embodying a system that does not include a gas generator.\u0000 The multi-functionality of the engine implies including in it additional units supporting some functions that are important for US, such as feeding propellant from US tanks to the engine after flying in zero gravity, autonomous control of the engine automatic equipment to support its firing, shutdown, adjustments during burn and emergency protection in case of off-nominal operation, as well as generating torques for controlling the US attitude and stabilizing it during coasting, etc.\u0000 Replacing conventional engine chamber cooling that uses high-boiling hydrocarbon fuel with the innovative oxygen cooling makes it possible to get rid of the internal film cooling circuits and eliminate their attendant losses of fuel, while the use of the oxygen gasified in the cooling circuit of the chamber to drive the turbo pump assembly permits to design an engine that does not have a gas generator.\u0000 Key words: Multifunctional rocket engine, oxygen cooling, gas-generatorless design, upper stage.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"21 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-06-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114257618","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 : 2019-06-30DOI: 10.33950/SPACETECH-2308-7625-2019-2-91-106
Vladimir N. Bashmakov, Aleksander I. Koryakin Aleksander, Sergey A. Kropotin, A. N. Popov, N. N. Sevastyanov, A. Sokolov, B. Sokolov, Yu. I. Sukhov
The article summarizes the results of a 15-year operation of the Yamal-202 telecommunication spacecraft in geostationary orbit. The review of using electrical rocket engines in spacecraft in domestic and foreign projects is made. The questions of methodology for developing and testing the electrical rocket propulsion system for the Yamal-200 spacecraft are considered including features of the RSC Energia stand base, specific features of the equipment and methodology for filling tanks with working fluid such as xenon. Special attention is paid to the preliminary joint test of the power supply and control equipment with thruster modules in order to justify the long-term operation of electrical rocket engines. In the analysis of the 15-year operation of the electrical rocket propulsion system the initial operation phase of the spacecraft is shown with the cruise mode of electrical rocket thruster modules for installation at operating points 49 and 90 EL with the corresponding operating time of all thruster modules. The final data on the operating time of thruster modules KA-201 for 10.5 and KA-202 – for 15 years of operation is presented that gives significant statistics on the use of engines СПД-70. The estimate of the remaining mass of the working fluid and the capability of further operation of the electrical rocket propulsion system is made. Key words: geostationary orbit, electrical rocket engine, thruster module, united propulsion system, predelivery checkout tests, filling with working fluid.
{"title":"Methodology of development and test of the electrical rocket propulsion system for telecommunication spacecraft Yamal-200 (to the 15th anniversary of operation in space)","authors":"Vladimir N. Bashmakov, Aleksander I. Koryakin Aleksander, Sergey A. Kropotin, A. N. Popov, N. N. Sevastyanov, A. Sokolov, B. Sokolov, Yu. I. Sukhov","doi":"10.33950/SPACETECH-2308-7625-2019-2-91-106","DOIUrl":"https://doi.org/10.33950/SPACETECH-2308-7625-2019-2-91-106","url":null,"abstract":"The article summarizes the results of a 15-year operation of the Yamal-202 telecommunication spacecraft in geostationary orbit. The review of using electrical rocket engines in spacecraft in domestic and foreign projects is made. The questions of methodology for developing and testing the electrical rocket propulsion system for the Yamal-200 spacecraft are considered including features of the RSC Energia stand base, specific features of the equipment and methodology for filling tanks with working fluid such as xenon. Special attention is paid to the preliminary joint test of the power supply and control equipment with thruster modules in order to justify the long-term operation of electrical rocket engines. In the analysis of the 15-year operation of the electrical rocket propulsion system the initial operation phase of the spacecraft is shown with the cruise mode of electrical rocket thruster modules for installation at operating points 49 and 90 EL with the corresponding operating time of all thruster modules. The final data on the operating time of thruster modules KA-201 for 10.5 and KA-202 – for 15 years of operation is presented that gives significant statistics on the use of engines СПД-70. The estimate of the remaining mass of the working fluid and the capability of further operation of the electrical rocket propulsion system is made. \u0000Key words: geostationary orbit, electrical rocket engine, thruster module, united propulsion system, predelivery checkout tests, filling with working fluid.","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"358 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-06-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133132575","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 : 2019-06-30DOI: 10.33950/SPACETECH-2308-7625-2019-2-115-126
O. Belonogov
The paper contains results of development and study of iterative techniques for static anal-ysis of quad-orifice electrohydraulic steering engine, namely, techniques for calculating its static characteristics (force and velocity characteristics) taking into account parameters of local hydraulic resistance parameters, making it possible to do analysis at various values of power supply voltage and temperature. The proposed techniques are based on solving systems of non-linear algebraic and transcendental equations of math models of the steering actuator describing its static operational modes. Taken as a basis for development of techniques for static analysis of the steering actuator are methods of integrated simulation of physical properties of working fluids of steering actuators and hydraulic drives, iterative methods for calculating parameters of working fluids flow in connecting lines, channels, flow-through elements and valves, results of studies of operating processes for steering actuator constituent elements, as well as a modification of the Seidel method for solving a system of non-linear algebraic and transcendental equations. The paper provides the results of testing the developed static analysis iterative techniques of such a steering actuator. Key words: static analysis, electrohydraulic steering actuator, non-linear algebraic and transcendent equations
{"title":"Techniques for iterative static analysis of a quad-orifice electrohydraulic steering actuator of rocket stages","authors":"O. Belonogov","doi":"10.33950/SPACETECH-2308-7625-2019-2-115-126","DOIUrl":"https://doi.org/10.33950/SPACETECH-2308-7625-2019-2-115-126","url":null,"abstract":"The paper contains results of development and study of iterative techniques for static anal-ysis of quad-orifice electrohydraulic steering engine, namely, techniques for calculating its static characteristics (force and velocity characteristics) taking into account parameters of local hydraulic resistance parameters, making it possible to do analysis at various values of power supply voltage and temperature. The proposed techniques are based on solving systems of non-linear algebraic and transcendental equations of math models of the steering actuator describing its static operational modes. Taken as a basis for development of techniques for static analysis of the steering actuator are methods of integrated simulation of physical properties of working fluids of steering actuators and hydraulic drives, iterative methods for calculating parameters of working fluids flow in connecting lines, channels, flow-through elements and valves, results of studies of operating processes for steering actuator constituent elements, as well as a modification of the Seidel method for solving a system of non-linear algebraic and transcendental equations. The paper provides the results of testing the developed static analysis iterative techniques of such a steering actuator.\u0000Key words: static analysis, electrohydraulic steering actuator, non-linear algebraic and transcendent equations","PeriodicalId":384878,"journal":{"name":"Space engineering and technology","volume":"65 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-06-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121961734","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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