Keywords cloud
Over the past 66 years Yuzhnoye SDO has developed more than 40 liquid rocket engines (LRE) of various purpose, designed both to gas-generator cycle and to staged combustion cycle.
]]>2. New and advanced liquid rocket engines of the Yuzhnoye SDO
Organization:
Page: Kosm. teh. Raket. vooruž. 2024, (1); 9-18
DOI: https://doi.org/10.33136/stma2024.01.009
Language: Ukrainian
Annotation: Specialized design office for liquid engines was established on July 22, 1958 to develop engines and propulsion systems, powered by liquid propellants to be installed on the combat missile systems and integrated launch vehicles (LV), developed by Yuzhnoye SDO. Moreover, liquid engines design office was assigned with manufacturing and testing of the main rocket engines, developed by NPO Energomash and to be installed on Yuzhnoye-developed launch vehicles. Over the past 66 years Yuzhnoye SDO has developed more than 40 liquid rocket engines (LRE) of various purpose, designed both to gas-generator cycle and to staged combustion cycle. Seventeen of them were commercially produced by Yuzhmash PA and installed on launch vehicles. Nowadays Yuzhnoye propulsion experts keep working on development of the advanced liquid rocket engines powered both by cryogenic and hypergolic propellants, which satisfy the majority of launch service market demands. Within the framework of extensive cooperation with foreign space companies, on a contract basis, Yuzhnoye propulsion experts are working on the design and development testing of the liquid rocket engines, as well as their components. The accumulated vast experience in the development of liquid rocket engines nowadays enables high scientific and technical level in the creation of up-to-date engines, demanded in the world market. Significant steps in this area have been made by the experts from the Yuzhnoye propulsion division and then subsequent manufacture and delivery by Yuzhmash PA of the engine intended for the European rocket Vega Stage 4; and designing the individual components for the engines with thrusts ranging from 500 kgf to 200 tf ordered by foreign customers. This article provides the review of current and scheduled activities of the Yuzhnoye SDO to develop the liquid rocket engines within the thrust ranges from ~ 40 kgf to ~ 500 tf.
Key words: LOX-kerosene liquid rocket engines, hypergolic propellant liquid rocket engines, staged combustion cycle, main rocket engine, thrust, specific thrust impulse.
Bibliography:
- Zhidkostnye raketnye dvigateli, dvigatelnye ustanovki, bortovye istochniki moschnosti, razrabotannye KB dvigatelnykh ustanovok GP«KB «Yuzhnoye». Za nauk. red. akad. NAN Ukrainy S.M. Konyukhova, kand. tekhn. nauk V.M. Shnyakina. Dnipropetrovsk: DP «KB «Pivdenne», 2008. 466 ark.
- Prokopchyuk O. O., Shulga V. A., Khromyuk D. S., Sintyuk V. O. Zhidkostnye raketnye dvigateli GP«KB «Yuzhnoye»: nauk.-tekhn. zbirnyk. Za nauk. red. akademika NAN Ukrainy
O. V. Degtyareva. Dnipro: ART-PRES, 2019. 440 ark.
Full text (PDF) || Content 2024 (1)
Downloads: 54
Abstract views:
1388
Dynamics of article downloads
Dynamics of abstract views
Downloads geography
| Country | City | Downloads |
|---|---|---|
| USA | Buffalo; Buffalo; San Jose; Chicago; Chicago; Chicago; Saint Louis; Saint Louis; Chicago; Dublin; Ashburn; Dallas; Los Angeles; Los Angeles; Ashburn; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Los Angeles; San Francisco; Ashburn; Ashburn; Houston; Mountain View; Portland; San Mateo; Washington; Ashburn; Ashburn | 33 |
| Germany | Falkenstein; Düsseldorf; Falkenstein; Leipzig; Leipzig | 5 |
| Canada | Toronto; Toronto; Toronto; Toronto; Toronto | 5 |
| China | Pekin; Pekin; Shenzhen; Pekin | 4 |
| Ukraine | Kyiv; Kremenchuk; Kremenchuk | 3 |
| Singapore | Singapore | 1 |
| France | 1 | |
| Hungary | Budapest | 1 |
| Netherlands | Amsterdam | 1 |
Having analyzed the data presented, one may conclude that the Rocket Engines Design Office and Yuzhnoye SDO as a whole accumulated sufficient experience and knowledge allowing solving any problems that may arise when developing a new LRE turbopump unit, and successfully operating LRE with turbopump units, including those in the engines with generator gas afterburning created in recent years testify to a great value of accumulated experience.
]]>4. Turbopump Units of Rocket Engines Developed by DO-4
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2018 (2); 25-33
DOI: https://doi.org/10.33136/stma2018.02.025
Language: Russian
Annotation: The article presents the experience of creating LRE turbopump units by the Rocket Engines Design Office (DO-4) at Yuzhnoye SDO. The best known turbopump units designs developed by DO are described. Both earlier developments of DO and the turbopump unit being now in final testing phase are considered. The design evolution of both separate assemblies and of entire unit is shown. The design evolution allowed increasing the unit’s lifetime dozens times. For example, the lifetime of the first turbopump units developed by DO did not exceed 150 s. Currently, the DO has in stock the engines with lifetime of ~19000 s. The information is presented on the problems that the designers faced in testing the turbopumop unit and the ways to solve them. The unique achievement are presented. At present, there are no analogs of some units in the world. The article presents the information on the latest achievements of DO, such as the face seal on pump vane discs whose use fully excludes unwanted leaks. Having analyzed the data presented, one may conclude that the Rocket Engines Design Office and Yuzhnoye SDO as a whole accumulated sufficient experience and knowledge allowing solving any problems that may arise when developing a new LRE turbopump unit, and successfully operating LRE with turbopump units, including those in the engines with generator gas afterburning created in recent years testify to a great value of accumulated experience.
Key words: liquid rocket engine, turbopump unit, pump, turbine
Bibliography:
1. Centrifugal Pump: Patent 1021816 А, USSR: MPK 7F04D1/00, 7F04D29/04 / Ivanov Y. N., Steblovtsev A. A.; Applicant and patent holder Yuzhnoye State Design Office. No. 3313928/25-06; claimed 06.07.1983, published 07.06.1984.
2. Auger-Centrifugal Pump: Patent 73783, Ukraine: MPK 7F04D29/66 / Ivanov Y. N., Pilipenko V. V., Zadontsev V. A., Drozd V. A.; Applicant and patent holder Yuzhnoye State Design Office. No. 2003021144; claimed 07.02.2003, published 15.09.2005.
3. End Seal. Patent 61082, Ukraine: MPK 7F16J15/34 / Ivanov Y. N., Chetverikova I. M.; Applicant and patent holder Yuzhnoye State Design Office. No. 990311536; claimed 19.03.1999, published 17.11.2003.
4. End Seal of High-Speed Shaft: Patent 48248, Ukraine: MPK F16J15/54, F04D29/10 / Ivanov Y. N., Steblovtsev A. A., Gameberger Y. A., Peredarenko V. M.; Applicant and patent holder Yuzhnoye State Design Office. No. 99031442; claimed 16.03.1999, published 15.08.2002.
5. Centrifugal Pump. Patent 84023, Ukraine: MPK F04D1/00 / Ivanov Y. N., Ivchenko L. F., Deshevykh S. A., Dan’kevich D. S.; Applicant and patent holder Yuzhnoye State Design Office. No. а200601399; claimed 13.02.2006, published 10.09.2008.
Full text (PDF) || Content 2018 (2)
Downloads: 72
Abstract views:
650
Dynamics of article downloads
Dynamics of abstract views
Downloads geography
| Country | City | Downloads |
|---|---|---|
| USA | Boardman; Ashburn; Ashburn; San Antonio; Matawan; Baltimore; North Bergen; Plano; Dublin; Columbus; Columbus; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Monroe; Ashburn; Ashburn; Seattle; Ashburn; Ashburn; Quinton; Houston; Houston; Seattle; Seattle; Tappahannock; Portland; Portland; San Mateo; San Mateo; San Mateo; Des Moines; Boardman; Boardman; Ashburn; Ashburn; Ashburn; Mountain View | 47 |
| Canada | Toronto; Toronto; Toronto; Toronto; Toronto; Monreale | 6 |
| Singapore | Singapore; Singapore; Singapore; Singapore; Singapore | 5 |
| Unknown | ; Hong Kong; | 3 |
| Ukraine | Dnipro; Dnipro | 2 |
| Germany | ; Falkenstein | 2 |
| Netherlands | Amsterdam; Amsterdam | 2 |
| Finland | Helsinki | 1 |
| The Republic of Korea | Daejeon | 1 |
| Malaysia | 1 | |
| Latvia | Riga | 1 |
| Romania | Voluntari | 1 |
Keywords cloud
Among them we should mention the RD858 and RD859 engines for the soviet lunar take-off-and –landing module of Block E, the unique RD857 and RD862 engines with afterburning of reducing generator gas and gas dynamic method of thrust vector control, the RD866 multifunctional engine of space tug ensuring multiple ignition in flight, and many others.
]]>1. Design Office of Liquid Rocket Engines is 60
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2018 (2); 3-7
DOI: https://doi.org/10.33136/stma2018.02.003
Language: Russian
Annotation: During 60 years of existence of specialized Liquid Rocket Engines Design Office – DO-4 as a part of Yuzhnoye Design Office, extensive experience was accumulated in development of liquid rocket engines of various purpose on storable and cryogenic propellant components. The required test benches and production base were created. When developing the engines, the DO-4 specialists widely use the experience accumulated during manufacturing and testing of the engines developed by the other design offices for Yuzhnoye SDO LVs that were manufactured by SE PA Yuzhny Machine-Building Plant and tested at Yuzhnoye SDO’s and Plant’s test benches. Along with the conventional ones, new original engine designs were developed to achieve high energy-mass characteristics, reliability and quality. Among them we should mention the RD858 and RD859 engines for the soviet lunar take-off-and –landing module of Block E, the unique RD857 and RD862 engines with afterburning of reducing generator gas and gas dynamic method of thrust vector control, the RD866 multifunctional engine of space tug ensuring multiple ignition in flight, and many others. At present, Yuzhnoye SDO jointly with SE PA Yuzhny Machine-Building Plant deliver the engine for the European Vega LV forth stage propulsion system under the contract with Avio company (Italy). Based on Yuzhnoye SDO–created engines, propulsions systems for ballistic missiles and space rockets that are unique by their characteristics and scope of functions, the engines, propulsions systems for spacecraft, LV upper stages and transfer orbit stages can be developed in short terms and at minimal costs.
Key words: liquid rocket engine, developed engines, testing, Yuzhnoye SDO, accumulated experience
Bibliography:
1. Liquid Rocket Engines, Propulsion Systems, Onboard Power Sources Developed by Propulsion Systems Design Office of Yuzhnoye SDO / Under scientific editorship of S. N. Konyukhov, Academician of NAS of Ukraine, V. N. Shnyakin, Candidate of Engineering Science. Dnepropetrovsk, 2008. 466 p.
2. Shnyakin V. N., Shulga V. A., Dibrivny A. V. Possibilities of Creating New LRE Based on Mature Technologies. Space Technology. Missile Armaments: Collection of scientific-technical articles. 2011. Issue 2. P. 61-71.
Full text (PDF) || Content 2018 (2)
Downloads: 69
Abstract views:
403
Dynamics of article downloads
Dynamics of abstract views
Downloads geography
| Country | City | Downloads |
|---|---|---|
| USA | Boardman; Ashburn; Matawan; Baltimore; North Bergen; Plano; Ashburn; Columbus; Detroit; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Monroe; Ashburn; Ashburn; Seattle; Seattle; Seattle; Ashburn; Ashburn; Mountain View; Ashburn; North Charleston; Mountain View; Mountain View; Mountain View; Ashburn; Mountain View; Seattle; Seattle; Tappahannock; Portland; San Mateo; San Mateo; Ashburn; Des Moines; Boardman; Boardman; Ashburn | 47 |
| Singapore | Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore | 7 |
| Canada | Toronto; Toronto; Monreale | 3 |
| Unknown | ; | 2 |
| Netherlands | Amsterdam; Amsterdam | 2 |
| Morocco | Casablanca | 1 |
| Indonesia | Medan | 1 |
| Cambodia | Phnom Penh | 1 |
| China | Pekin | 1 |
| Finland | Helsinki | 1 |
| Germany | Falkenstein | 1 |
| Romania | Voluntari | 1 |
| Ukraine | Dnipro | 1 |
Keywords cloud
Typical stages of development and introduction of the pressurization generating systems are shown: development of generators, their development testing, study of the composition and parameters of gas. Accounting of the correlation between the flow rate and the generator gas temperature improved the output performance, as well as simplified and reduced the amount of development testing of the pressurization system. Key words: gas generator , sprayer , propulsion system , tank , gas pressure , gas temperature Bibliography: 1. gas generator , sprayer , propulsion system , tank , gas pressure , gas temperature .
]]>7. Experience of Development and Use of Generator Pressurization System for Tanks of Launch Vehicles on High-Temperature Propellants
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2019, (1); 45-53
DOI: https://doi.org/10.33136/stma2019.01.045
Language: Russian
Annotation: Long-term experience in development, development testing and use of generating systems of fuel tanks pressurization for rockets powered by nitrogen tetroxide and unsymmetrical dimethylhydrazine is summarized. Replacement of gas bottle pressurization systems with generating ones on such launch vehicles as 15A14, 15A15, 11K68 (8K67), 15A18M substantially simplified operation, reduced the pneumohydraulic feed system mass at least twice and its cost – by five times. Typical stages of development and introduction of the pressurization generating systems are shown: development of generators, their development testing, study of the composition and parameters of gas. The important steps were the development of methodology for pressurization system parameters calculation, which enabled achievement of the substantial improvements of their characteristics, appearance of the high-performance hightemperature (up to ~ 1000o C) unsymmetrical dimethylhydrazine tank pressurization system, study of the degree of impact of each of the pressurization system parameters on the tank pressure. Accounting of the correlation between the flow rate and the generator gas temperature improved the output performance, as well as simplified and reduced the amount of development testing of the pressurization system. Important role of the gas sprayer design in pressurization system parametric configuration is described, and the advanced versions are shown taking into account g-loads, changes in temperature, pressure and propellant level inside the tank. Significant phase in the development of the generating pressurization system was the effective use of the high-temperature pressurization of the fuel tank with submerged propulsion system. Besides for the first time the effect of mechanical temperature destratification of the propellant in the tanks was observed, which occurs during the propulsion systems shutdown. Due to this effect, the Dnepr LV payload capability enhanced. Successful engineering solutions in the design of the pressurization system were defended by ~80 copyright certificates and patents of invention, ~40 of which were successfully implemented.
Key words: gas generator, sprayer, propulsion system, tank, gas pressure, gas temperature
Bibliography:
1. Belyaev N. M. Systemy nadduva toplivnykh bakov raket. M.: Mashinostroenie, 1976. 336 p.
2. Logvinenko A. I. Osnovnyie napravlenia sovershenstvovania PGS sovremennykh RN / Dokl. Mezhd. astronavt. kongress. IAA. C4.1 IAC-63. Naples, Italia, 2012.
3. Kozlov A. A., Novikov V. N., Soloviev Ye. V. Systemy pitania i upravlenia zhidkostnykh raketnykh dvigatelnykh ustanovok. M.: Mashinostroenie, 1988. 352 p.
4. Logvinenko A. I. Tendentsii razvitia system nadduva toplivnykh bakov RN// Tez. dokl. Mezhdunar. astronavt. congressa IAC–05–C4.1.10, IAC-56. Fukuoka, Japan, 2005.
5. Logvinenko A. Gas-generation pressurization system experimental development method of the LV propellant tanks / Acta Astronautica. 2009. AA3161. №64. Р. 84-87. https://doi.org/10.1016/j.actaastro.2008.06.008
6. Ivanitskiy G. M., Logvinenko A. I., Tkachev V. A. K voprosu rascheta temperatury gazanadduva v bakakh raket / Systemne proektuvannya aerokosmichnoi techniki. 2001. T. III. P. 44-47.
7. Pat. 72330 Ukraina, MPK (2006) F02K 9/44 (2006.1), F02K 11/00, В64Д 37/00. Sposib vyroblennya zalyshku palyva v rushiniy ustanovtsi riddinoi rakety/ Ivanitskiy G. M., Kubanov S. M., Logvinenko A. I., Yushin G. I.; zayavnil I vlasnyk DP KB “Pivdenne”. №20021210267; zayvl. 18.12.2002; opubl. 15.02.2005, Bul. №2/2005.
8. Voloshin M. L., Kuda S. A., Mikhalchishin R. V. Complex meropriyatiy po povysheniyu energeticheskykh kharakteristic RN// Kosmicheskaya technika. Raketnoye vooruzhenie: Sb. nauch.-techn. st. Dnepr: GP KB «Yuzhnoye». 2017. Vyp. 2. P. 29-34.
Full text (PDF) || Content 2019 (1)
Downloads: 62
Abstract views:
592
Dynamics of article downloads
Dynamics of abstract views
Downloads geography
| Country | City | Downloads |
|---|---|---|
| USA | Boardman; Matawan; Baltimore; Plano; Ashburn; Ashburn; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Monroe; Ashburn; Seattle; Seattle; Seattle; Seattle; Ashburn; Ashburn; Ashburn; Houston; Seattle; Tappahannock; San Mateo; San Mateo; San Mateo; San Mateo; Des Moines; Boardman; Boardman; Ashburn; West Lafayette; Seattle | 38 |
| Singapore | Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore | 8 |
| Canada | Toronto; Toronto; Toronto; Toronto; Monreale | 5 |
| Ukraine | Berdyans'k; Dnipro; Dnipro | 3 |
| Netherlands | Amsterdam; Amsterdam | 2 |
| Cambodia | Phnom Penh | 1 |
| Finland | Helsinki | 1 |
| Philippines | 1 | |
| Great Britain | London | 1 |
| Germany | Falkenstein | 1 |
| Romania | Voluntari | 1 |
Keywords cloud
2019, (1); 114-121 DOI: https://doi.org/10.33136/stma2019.01.114 Language: Russian Annotation: This article considers essentially new versions of small-sized solid propellant rocket engines (SRE), designed for rocket and spacecraft flight control with serial artillery pyroxiline powder taken as grain and solidpropellant gas generators discretely operating into the receiver.
]]>17. Development of Prospective Small-Size Auxiliary SMR of New Type
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2019, (1); 114-121
DOI: https://doi.org/10.33136/stma2019.01.114
Language: Russian
Annotation: This article considers essentially new versions of small-sized solid propellant rocket engines (SRE), designed for rocket and spacecraft flight control with serial artillery pyroxiline powder taken as grain and solidpropellant gas generators discretely operating into the receiver. Preliminary results of design and experimental activities, performed in Yuzhnoye SDO, showed the possibility in principle and practicability to develop two new types of advanced small-sized SRE. Testing SRE with pyroxiline powder grain showed that the optimum design of the engine can be developed only with the application of the specially developed design procedure of the gas-dynamic flow pattern of powder gases in the engine chamber with definition of field of pressure and velocity. Such procedure has been developed based on Ansys software package. The article describes areas of further design and experimental activities, fulfilment of which will provide development of production models of the described engines. Intraballistic characteristics design procedure, mentioned in the article, can be used to design new type of micropulse SRE with less than 0.1 s burn time. This article will also facilitate definition of the application area for discrete solid-propellant propulsion systems, where they get the edge over the cold gas gas-jet systems.
Key words: procedure, microSRE, gas-jet system, heat-transfer factor
Bibliography:
1. Kovalenko N. D., Kukushkin V. I. Triumph I tragediya systemy upravleniya vektorom tyagi dvigatelya ZD65 vduvom kamernogo gaza v soplo// Kosmicheskaya technika. Raketnoe vooruzhenie: Sb. nauch.-techn. st. 2014. Vyp. 1. Dnepropetrovsk: GP KB «Yuzhnoye». P. 97-106.
2. Oglykh V. V., Vakhromov V. A., Kirichenko A. S., Kosenko M. G. Razrabotka porokhovykh accumulyatorov davlenia dlya minometnogo starta raket – vazhneishee uslovie ego uspeshnoy realizatsii / Kosmicheskaya technika. Raketnoe vooruzhenie: Sb. nauch.-techn. st. 2016. Vyp. 1. Dnepropetrovsk: GP KB «Yuzhnoye». P. 88-92.
3. Golubev K. S., Svetlov V. G. Proektirovanie zenitnykh upravlyaemykh raket. M.: Izd-vo MAH, 2001. 730 p.
4. Oglykh V. V., Tolochyants G. E., Mikhailov N. S., PopkovV. N. Eksperimentalnye issledovania vozmozhnosti sozdania impulsnogo RDTT s malym vremenem raboty/ Kosmicheskaya technika. Raketnoe vooruzhenie: Sb. nauchn.-techn. st. 2016. Vyp. 2. Dnepr: GP KB «Yuzhnoye». P. 30-34.
5. Belyaev N. M., Belik N. P., Uvarov Ye. I. Reaktyvnye systemy upravleniya kosmicheskykh letatelnykh apparatov. M.: Mashinostroenie, 1979. 232 p.
6. Gubertov A. M., Mironov V. V., Borisov D. M. Gazodynamicheskie i teplophysicheskie process v raketnykh dvigatelyakh na tverdom toplive. M.: Mashinostroenie, 2004.
7. Kutateladze S. S. Teploperedacha i hydrodynamicheskoe soprotivlenie. Energoatomizdat, 1990. 368 p.
8. Scherbakov M. A. Opredelenie coeffitsientov teplootdachi pri modelirovanii zadach v Ansys CFX // Dvigateli i energoustanovki aerokosmicheskykh letatelnykh apparatov: Sb. nauch. statey. M.: Nauch.- techn. Centr im. A. Lyulki, 2014.
9. Moskvichev A. V. Primenimost’ modeley turbulentnosti, realizovannykh v Ansys CFX dlya issledovaniya gasodynamiki v schelevom kanale TNA ZhRD. Voronezhskiy gosudarstvenniy technicheskiy universitet, 2015.
10. Magdin E. K., Oglykh V. V., Rozlivan A. B. Tverdotoplivnaya dvigatelnaya ustanovka orientatsii I stabilizatsii descretnogo deistviya dlya upravleniya kosmicheskimi obiektami / Vestn. dvigatelestroiteley. 2017. Vyp. 2. P. 108-111.
Full text (PDF) || Content 2019 (1)
Downloads: 58
Abstract views:
1088
Dynamics of article downloads
Dynamics of abstract views
Downloads geography
| Country | City | Downloads |
|---|---|---|
| USA | ; Baltimore;; Plano; Miami; Dublin; Columbus; Detroit; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Monroe; Ashburn; Seattle; Seattle; Ashburn; Houston; Ashburn; Mountain View; Mountain View; Mountain View; Seattle; Seattle; Tappahannock; Portland; Portland; San Mateo; San Mateo; Des Moines; Boardman; Boardman; Ashburn; Ashburn; Ashburn; Ashburn; Seattle | 41 |
| Singapore | Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore | 8 |
| Ukraine | Kyiv; Dnipro | 2 |
| Canada | Toronto; Toronto | 2 |
| Netherlands | Amsterdam; Amsterdam | 2 |
| India | Kolkata | 1 |
| Germany | Falkenstein | 1 |
| Romania | Voluntari | 1 |
Keywords cloud