Search Results for “action time” – Collected book of scientific-technical articles https://journal.yuzhnoye.com Space technology. Missile armaments Tue, 23 Apr 2024 08:59:41 +0000 en-GB hourly 1 https://wordpress.org/?v=6.2.2 https://journal.yuzhnoye.com/wp-content/uploads/2020/11/logo_1.svg Search Results for “action time” – Collected book of scientific-technical articles https://journal.yuzhnoye.com 32 32 19.1.2020 Pyrobolts: types, design, development. Shear type pyrobolt developed at Yuzhnoye SDO https://journal.yuzhnoye.com/content_2020_1-en/annot_19_1_2020-en/ Wed, 13 Sep 2023 12:02:02 +0000 https://journal.yuzhnoye.com/?page_id=31074
Owing to the simple design, reliability and short action time, the pyrobolts have found wide application in aerospace engineering for separation of assemblies and bays, in particular, stages, head modules, launching boosters, etc.
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19. Pyrobolts: types, design, development. Shear type pyrobolt developed at Yuzhnoye SDO

Authors:

Samoilenko I. D., Voloshin V. V., Onofriienko V. I., Bezkorsyi D. M.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2020, (1); 170-176

DOI: https://doi.org/10.33136/stma2020.01.170

Language: Russian

Annotation: The pyrobolts, or explosive bolts, belong to the pyrotechnical devices with monolithic case consisting o f the cap, as a rule with hexagonal surface, and of cylindrical part with thread. The pyrobolts are separated into parts using the pyrotechnical charge placed inside the case. Owing to the simple design, reliability and short action time, the pyrobolts have found wide application in aerospace engineering for separation of assemblies and bays, in particular, stages, head modules, launching boosters, etc. So, for example, about 400 pyrobolts are used in the Proton launch vehicle. The designs of pyrobolts are markedly different. By method of explosive substance action on case structural elements, the pyrobolts are divided into two types: the pyrobolts using the shock wave formed at detonation of brisant explosive substance for case wall destruction and the pyrobolts using the pressure of gases arising at pyrotechnical charge blasting. By method of separation into parts, they are divided into fragmenting pyrobolts with ridge-cut, with piston, and shear pyrobolts. The paper deals with the design of various types of pyrobolts, their disadvantages are considered. The Yuzhnoye SDO-developed pyrobolt of shear type with segments is presented that uses radial shear forces of segments located in the hole of cylindrical part to separate the case parts. The above segments a re actuated using a rod with sealing rings and a piston connected to the rod through a rubber gasket; the piston moves under pressure of gases formed during pyro cartridge action. The following calculations are presen ted: strength analyses with determination of case load-carrying capacity; power analyses with justification of pyro cartridge selection for pyrobolt actuation. In the developed pyrobolt of shear type with segments, the case parts are separated without considerable shock loads and without high-temperature gases and fragments release into environment, ensuring reliable separation of bays and assemblies without damaging sensitive equipment.

Key words: explosive bolt, shock wave, brisant explosive substance, pyro cartridge, electric igniting fuse, high-temperature gases

Bibliography:
1. Mashinostroenie. Entsiklopediia / А. P. Adzhian i dr.; pod red. V. P. Legostaeva. М., 2012. Т. IV-22. V 2-kh kn. Kn. 1. 925 s.
2. Bement L. J., Schimmel M. L. A Manual for Pyrotechnic Design, Development and Qualification: NASA Technical Memorandum 110172. 1995.
3. Yumashev L. P. Ustroistvo raket-nositelei (vspomagatelnye sistemy): ucheb. posob. Samara, 1999. 190 s.
4. Lee J., Han J.-H., Lee Y., Lee H. Separation characteristics study of ridge-cut explosive bolts. Aerospace Science and Technology. 2014. Vol. 39. Р. 153-168. https://doi.org/10.1016/j.ast.2014.08.016
5. Yanhua L., Jingcheng W., Shihui X., Li C., Yuquan W., Zhiliang L. Numerical Study of Separation Characteristics of Piston-Type Explosive Bolt. Shock and Vibration. https://doi.org/10.1155/2019/2092796
6. Yanhua L., Yuan L., Xiaogan L., Yuquan W., Huina M., Zhiliang L. Identification of Pyrotechnic Shock Sources for Shear Type Explosive Bolt. Shock and Vibration. https://doi.org/10.1155/2017/3846236

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19.1.2020 Pyrobolts: types, design, development. Shear type pyrobolt developed at Yuzhnoye SDO
19.1.2020 Pyrobolts: types, design, development. Shear type pyrobolt developed at Yuzhnoye SDO
19.1.2020 Pyrobolts: types, design, development. Shear type pyrobolt developed at Yuzhnoye SDO

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]]> 4.1.2020 Terminal guidance of the aircraft being maneuvering while descending in the atmosphere under conditions of aerodynamic balancing https://journal.yuzhnoye.com/content_2020_1-en/annot_4_1_2020-en/ Wed, 13 Sep 2023 05:51:26 +0000 https://journal.yuzhnoye.com/?page_id=31024
Based on the results of processing single calculations, the corresponding flight ranges of a flying vehicle and the lateral displacement of the touchdown points are determined, the point in time is predicted at which the flight range of the flying vehicle is equal to the specified one and the average lateral deviation is determined. Counteraction of the lateral displacement is introduced by adjusting the half-periods of flying vehicle movement along the angle of the precession.
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4. Terminal guidance of the aircraft being maneuvering while descending in the atmosphere under conditions of aerodynamic balancing

Authors:

Sirenko V. M., Levin O. S., Mashtak I. V., Sheptun A. D.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2020, (1); 34-43

DOI: https://doi.org/10.33136/stma2020.01.034

Language: Russian

Annotation: High-precision guidance of supersonic flying vehicles maneuvering while descending in the atmosphere with high degree of thermal protection ablation is a well-known problem of space ballistics. The existing methods for calculating the ablation of thermal protection and the subsequent calculation of aerodynamic characteristics lead to scatter of the landing points of a flying vehicle reaching 5 km or more. The functional guidance method, in principle, allows achieving the required guidance accuracy (hundreds of meters), however, it requires a reserve of power of the controls at a level 50% to counter the influence of disturbing factors. The known terminal guidance method, which has recently become widespread, is based on a highly accurate prediction of motion parameters and, in this regard, has little promise. The method has been described in the article that allows 15-20-fold reducing the flight range scatters caused by lack of knowledge (including due to coating ablation) of its current aerodynamic characteristics and ensuring that the accumulated lateral deviation is counteracted in the limit to 1-1.5 km. The method is applicable to the flying vehicles with weight asymmetry (“transverse” displacement of the center of mass), performing maneuvering under conditions of aerodynamic balancing. The method is based on the solution to increase the accuracy of hits by spinning the shells around longitudinal axis. It is proposed that when a flying vehicle moves in the dive mode by means of the onboard CVC, it is regular (at intervals) to calculate its flight path in the (conditionally) autorotation mode. Based on the results of processing single calculations, the corresponding flight ranges of a flying vehicle and the lateral displacement of the touchdown points are determined, the point in time is predicted at which the flight range of the flying vehicle is equal to the specified one and the average lateral deviation is determined. At this moment the angular movement of the flying vehicle is transferred to the autorotation mode. Counteraction of the lateral displacement is introduced by adjusting the half-periods of flying vehicle movement along the angle of the precession. An example of pointing a flying vehicle at a given range, and bringing it to the touchdown point, shifted to the right relative to the original flight path by 1 km. The error of the terminal guidance of a maneuvering while reducing the aircraft using the proposed guidance method is determined.

Key words: angular motion of flying vehicle; touchdown point, methodological error of guidance, guidance of maneuvering supersonic flying vehicle

Bibliography:
1. Eliasberg P. Е. Vvedenie v teoriiu poleta iskusstvennykh sputnikov Zemli. М., 1965. 540 s.
2. Lebedev А. А., Gerasiuta N. F. Ballistika raket. М., 1970. 244 s.
3. Levin A. S., Mashtak I. V., Sheptun А. D. Dinamika manevrirovaniia v atmosphere LA s vesovoi asimmetriei i elementami terminalnogo upravleniia na uchastke razvorota. Kosmicheskaia tekhnika. Raketnoe vooruzhenie: sb. nauch.-tekhn. statei / GP “KB “Yuzhnoye”. Dnipro, 2019. Vyp. 1. S. 4–14. https://doi.org/10.33136/stma2019.01.004
4. Chandler D. C., Smith I. E. Development of the iterative guidance mode with is application to varies vehicles and missions. Journal of Spacecraft and Rockets. 1967. Vol 1.4, №7. P. 898-903. https://doi.org/10.2514/3.28985

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4.1.2020 Terminal guidance of the aircraft being maneuvering while descending in the atmosphere under conditions of aerodynamic balancing
4.1.2020 Terminal guidance of the aircraft being maneuvering while descending in the atmosphere under conditions of aerodynamic balancing
4.1.2020 Terminal guidance of the aircraft being maneuvering while descending in the atmosphere under conditions of aerodynamic balancing

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]]> 23.2.2018 On the Role of Space in Origination of Inertia Force Field, Earth Gravity Force Field and Zero Gravity of Material Body https://journal.yuzhnoye.com/content_2018_2-en/annot_23_2_2018-en/ Thu, 07 Sep 2023 12:35:25 +0000 https://journal.yuzhnoye.com/?page_id=30813
Solution of the problem rests on the example of the cantilever beam and mathematical model of the information reflection process, which for the first time takes into consideration previously unknown property of space reflection. Interaction of mechanical particles with the information inertia field in the configuration space generates physical inertia field of force, providing the real inertia under accelerated motion of the beam. Interaction of the body with specific mass with the vector information field of the Earth generates the physical force field of gravity. Time. Space and Time in Inanimate and Animate Nature. Space – Time, information – energy.
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23. On the Role of Space in Origination of Inertia Force Field, Earth Gravity Force Field and Zero Gravity of Material Body

Authors:

Muliar Yu. M., Fedorov V. M.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (2); 190-206

DOI: https://doi.org/10.33136/stma2018.02.190

Language: Russian

Annotation: Presented is the theoretical justification of the phenomenon of the inertia initiation under accelerated motion of the body, and gravity origin in the circumterrestrial space. There is no description of the physical nature of the inertia and gravity in the scientific publications. In the phenomenological approach under study, allowing for reflection properties of the space, earlier unknown interdependent information-physical link of the body and its mechanical particles with space under the accelerated motion was determined in the state of rest of the gravitation field as well as in the state of weightlessness. Alongside with the environment, eigenspace, i.e. configuration space of the body and corresponding metric lines of the space are considered. Idea of metric lines agrees with the concept of F. Wilczek, the American physicist, Nobel-Prize laureate, on the existence of the unobservable metric field in the real space. Solution of the problem rests on the example of the cantilever beam and mathematical model of the information reflection process, which for the first time takes into consideration previously unknown property of space reflection. Under the accelerated motion of the body reflection gains the acceleration vector dt d а     . In this case reflection manifests itself in the initiation of the beam of polarization vector under study   ~ in every point of the configuration space and is expressed as     ~ а . Value of the polarization vector equals the value of acceleration vector with negative sign. As a result metric lines of the configuration space under conditions of beam acceleration become polarized lines, generating vector information inertia field. Interaction of mechanical particles with the information inertia field in the configuration space generates physical inertia field of force, providing the real inertia under accelerated motion of the beam. (Relatively slow motion of bodies is studied as compared to the speed of light). According to the set forth unconventional approach the nature of the earth gravity is conditioned by the polarization of the radial metric lines of the circumterrestrial space. And polarization vector is directed to the center of the Earth and equals acceleration vector of the free fall with the same sign. Interaction of the body with specific mass with the vector information field of the Earth generates the physical force field of gravity. Article deals with the fundamental issues of theoretical physics and other fields of natural science. Materials of the conducted research are regarded as a potential scientific discovery.

Key words: configuration space, modified method of sections, information and vacuum environment, metric lines, property of space reflection, polarization, scalar information field, vector information field

Bibliography:
1. Vilchek F. Fine Physics. Mass, Ester and Unification of World Forces. Collection of publications, 2018. 336 p.
2. Sivukhin D. V. General Course of Physics. Vol. 1. М., 1989. 576 p.
3. Logunov А. А. Lectures on Relativity Theory and Gravitation. Modern Analysis of Problem. М., 1987. 272 p.
4. Feinman R., Layton R., Sands M. Feinman Lectures in Physics. Vol. 1. Modern Natural Science. The Laws of Mechanics. Vol. 2. Space. Time. Motion / Translation from English. М., 1976. 439 p.
5. Mulyar Y. M. On Stability of Compressed Rod. Technical mechanics. Dnepropetrovsk, 2000. No. 2. P. 51-57.
6. Mulyar Y. M., Perlik V. I. On Mathematical Model Representation of Information Field in Loaded Deformed System. Information and Telecommunication Technologies. М., 2012. No. 15. P. 61-74.
7. Vernadsky V. I. Reflections of Natural Scientist. Space and Time in Inanimate and Animate Nature. М., 1975. 173 p.
8. Ursul A. D. Reflection and Information. М., 1973. 231 p.
9. Vladimirov Y. S. Metaphysics. М., 2002. 550 p.
10. Author’s Certificate 181066 USSR. Energy Absorber / А. М. Buyanovsky, Y. М. Mulyar. Discoveries. Inventions. 1993. No. 15. P. 101.
11. Cacku M. Physics of Impossible / Translation from English. М., 2016. 456 p.
12. Proceedings of the International Scientific Conference “Problems of Ideality in Science”. М., 2001. 352 p.
13. Mulyar Y. M., Fyodorov V. M., Tryasuchev L. M. On the Impact of Initial Imperfections on Rod Stability Loss in Conditions of Axial Compression. Space Technology. Missile Armaments: Collection of scientific-technical articles. 2017. Issue 1 (113). P. 48-58.
14. Dyomin A.I. Paradigm of Dualism. Space – Time, information – energy. М., 2007. 320 p.
15. Lisin A.I. Paradigm of Dualism. Ide: Reality of ideality. Part 1. М., 1999. 382 p.

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23.2.2018 On the Role of Space in Origination of Inertia Force Field, Earth Gravity Force Field and Zero Gravity of Material Body
23.2.2018 On the Role of Space in Origination of Inertia Force Field, Earth Gravity Force Field and Zero Gravity of Material Body
23.2.2018 On the Role of Space in Origination of Inertia Force Field, Earth Gravity Force Field and Zero Gravity of Material Body

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]]> 15.2.2018 Topical Issues of Creation of Space Rocket Thermostatic System Mating Points https://journal.yuzhnoye.com/content_2018_2-en/annot_15_2_2018-en/ Thu, 07 Sep 2023 12:09:41 +0000 https://journal.yuzhnoye.com/?page_id=30786
Besides, the methodological principles based on problematic, systematic, and structuralfunctional approach were applied using the theoretical and empirical capabilities, attraction of general scientific and special investigation methods, as well as historical and logical methods. As a result, it was ascertained that the joints can be made of simpler and at the same time failure-free design in the form of combined triune rubber hose fitted with a metal fixation/release unit installed on a sealing flange in a special groove.
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15. Topical Issues of Creation of Space Rocket Thermostatic System Mating Points

Authors:

Bigun S. O.1, Khorolskyi M. S.2

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; State Enterprise “Ukrainian Research Design-Technological Institute of Elastomer Materials and Products”, Dnipro, Ukraine2

Page: Kosm. teh. Raket. vooruž. 2018 (2); 132-138

DOI: https://doi.org/10.33136/stma2018.02.132

Language: Russian

Annotation: The problem is defined of designing the space rocket low-pressure air thermostating systems joints. The basic requirements imposed to the joints from the side of space rocket and ground complex are determined and stated. For this purpose, the analysis of operating conditions and possible situations during rocket launches is made. Besides, the methodological principles based on problematic, systematic, and structuralfunctional approach were applied using the theoretical and empirical capabilities, attraction of general scientific and special investigation methods, as well as historical and logical methods. The list of topical issues is reflected for implementation in joint’s design. The ways are proposed to create the joints meeting the requirements imposed. As a result, it was ascertained that the joints can be made of simpler and at the same time failure-free design in the form of combined triune rubber hose fitted with a metal fixation/release unit installed on a sealing flange in a special groove. Of special note is the versatility of the proposed technical solution for use in any of the space launch systems known in the world’s practice. The article is concluded with following: the basic requirements have been formulated for ground complexes thermostating systems joints to ensure space rockets prelaunch processing and launch, in doing so, the topical problems were defined; the scientific principles were proposed to design the thermostating systems joints for comprehensive solution of the topical problems , including potential critical situations; the thermostating systems joints have been developed, manufactured and have successfully passed the ground development tests with simulation of the conditions maximally close to operating ones at static operating air pressures and in off-nominal situations.

Key words: planetary roving vehicle, self-propelled modular platform, generic module, interchangeability

Bibliography:
1. Bigun S. A., Khorolsky M. S et al. Types and Design Features of Thermostating System Mating Points of Launch Vehicle Payload Units and Launch Vehicle and Spacecraft Bays. Space Technology. Missile Armaments: Collection of scientific-technical articles. 2013. Issue 1. 123 p.
2. Bigun S. A., Khorolsky M. S et al. Experimental Investigations of Cyclone-4 ILV Thermostating System Mating Points Test Results. Space Technology. Missile Armaments: Collection of scientific-technical articles. 2016. Issue 2. 105 p.

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15.2.2018 Topical Issues of Creation of Space Rocket Thermostatic System Mating Points
15.2.2018 Topical Issues of Creation of Space Rocket Thermostatic System Mating Points
15.2.2018 Topical Issues of Creation of Space Rocket Thermostatic System Mating Points

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]]> 5.2.2018 Electromagnetic Valves Developed by Yuzhnoye SDO Liquid Rocket Engines Design Office https://journal.yuzhnoye.com/content_2018_2-en/annot_5_2_2018-en/ Thu, 07 Sep 2023 11:01:49 +0000 https://journal.yuzhnoye.com/?page_id=30749
They are used in the operating pressure range of 0.5…56 MPa, at that, the action time is 0.025…0.15 s. This electrohydraulic valve is operable at the pressure below 8 MPa, the action time is 0.08…0.12 s. Recently, Yuzhnoye State Design Office develops the apogee RD840 LRE with 400 N thrust, for the conditions of which the direct-action electrohydraulic valve was developed and tested with the following characteristics: pressure – up to 2.15 MPa, consumed power in operation mode – less than 7.1 W, action time – not more than 0.02 s, mass – 0.19 kg. Key words: electrohydraulic valve , electropneumatic valve , pneumohydraulic system , direct-action electric valve , electric valve with amplification , action time Bibliography: 1. electrohydraulic valve , electropneumatic valve , pneumohydraulic system , direct-action electric valve , electric valve with amplification , action time .
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5. Electromagnetic Valves Developed by Yuzhnoye SDO Liquid Rocket Engines Design Office

Authors:

Konokh V. I., Boiko V. S., Troyak A. B., Ivashura A. V.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (2); 34-48

DOI: https://doi.org/10.33136/stma2018.02.034

Language: Russian

Annotation: In the pneumohydraulic systems of liquid rocket engines and propulsion systems, electromagnetic valves that allow making the pneumohydraulic systems more simple and ensuring multiple ignition of liquid rocket engines have found wide application. The Yuzhnoye-developed electromagnetic valves are designed according to two schemes – of direct and indirect action. In the direct-action electromagnetic valves, the shutting-off device opens (closes) the throat with the force developed by electric magnet. They have gained acceptance in the pneumohydraulic systems with the working medium pressure of ~8.5 MPa, they are of simple design and have high operating speed (0.001…0.05 s). In the electromagnetic valves with amplification, the electromagnet armature is connected with control valve and the main shutting-off device moves due to the force from working medium pressure drop on it. They are used in the operating pressure range of 0.5…56 MPa, at that, the action time is 0.025…0.15 s. For the European Vega launch vehicle fourth stage main engine assembly that has pressure propellant feeding system, the electrohydraulic valve with amplification and drainage was developed. The dependence of this electrohydraulic valve high speed from the line’s output length is decreased to the maximum due to the installation of Venturi nozzle at the output connecting branch. This electrohydraulic valve is operable at the pressure below 8 MPa, the action time is 0.08…0.12 s. The present-day spacecraft gas-jet orientation and stabilization systems use as propulsion devices the electromagnetic valves with nozzles whose thrust is, as a rule, not more than 30 N and the working medium pressure is up to 24 MPa. Yuzhnoye State Design Office developed for 15B36 gas-jet system the electropneumatic valve with amplification and nozzle, which is operable at the pressure below 45 MPa, ensures the action frequency of up to 10 Hz and is capable of creating the thrust of 100 N on gaseous argon. To solve the task of decreasing the dependence of operability and high speed of electromagnetic valves with drainage and amplification on geometry of lines in which a valve is installed, the electropneumatic valve was developed that has spool elements ensuring reliable and quick action with long input lines of 0.004 m diameter. Its mass is 2…2.5 times lower than the mass of analogs. Recently, Yuzhnoye State Design Office develops the apogee RD840 LRE with 400 N thrust, for the conditions of which the direct-action electrohydraulic valve was developed and tested with the following characteristics: pressure – up to 2.15 MPa, consumed power in operation mode – less than 7.1 W, action time – not more than 0.02 s, mass – 0.19 kg. The presented electromagnetic valves by their technical and operational characteristics meet the highest world requirements and have found wide utility in liquid rocket engines and propulsion systems.

Key words: electrohydraulic valve, electropneumatic valve, pneumohydraulic system, direct-action electric valve, electric valve with amplification, action time

Bibliography:
1. Electric Hydraulic Valve: Patent 89948 Ukraine: MPK F 16K 32/02 / Shnyakin V. M., Konokh V. I., Kotrekhov B. I., Troyak A. B., Boiko V. S.; Applicant and patent holder Yuzhnoye State Design Office. а 2006 02543; claimed 09.03.2006; published 25.03.2010, Bulletin No. 6.
2. Boiko V. S., Konokh V. I. Stabilization of Opening Time of Electric Hydraulic Valve with Boost in Liquid Rocket Engine Hydraulic System. Problems of Designing and Manufacturing Flying Vehicle Structures: Collection of scientific works. 2015. Issue 4 (84). P. 39-48.
3. Electric Valve: Patent 97841, Ukraine: MPK F 16K 32/02 / Shnyakin V. M., Konokh V. I., Kotrekhov B. I., Troyak A. B., Boiko V. S., Ivashura A. V.; Applicant and patent holder Yuzhnoye State Design Office. а 2009 12002; claimed 23.11.2009; published 26.03.2012, Bulletin No. 6.
4. Boiko V. S., Konokh V. I. Increase of Action Stability of Electric Pneumatic Valve with Boost in the System with Increased Inlet Hydraulic Resistance. Aerospace Engineering and Technology: Scientific-Technical Journal. 2013. Issue 3 (100). P. 90-95.
5. Flying Vehicles Pneumatic Systems Units / Lyaskovsky I. F., Shishkov A. I., Romanenko N. T., Romanenko M. T., Chernov M. T., Yemel’yanov V. V. / Under the editorship of N. T. Romanenko. М., 1976. 176 p.

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5.2.2018 Electromagnetic Valves Developed by Yuzhnoye SDO Liquid Rocket Engines Design Office
5.2.2018 Electromagnetic Valves Developed by Yuzhnoye SDO Liquid Rocket Engines Design Office
5.2.2018 Electromagnetic Valves Developed by Yuzhnoye SDO Liquid Rocket Engines Design Office

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]]> 6.2.2017 Set of Actions on Enhancement of Launch Vehicle Payload Capability https://journal.yuzhnoye.com/content_2017_2/annot_6_2_2017-en/ Tue, 08 Aug 2023 12:39:31 +0000 https://journal.yuzhnoye.com/?page_id=29754
Set of Actions on Enhancement of Launch Vehicle Payload Capability Authors: Voloshin M. 2017 (2); 29-34 Language: Russian Annotation: The paper presents a complex of analytical calculation measures that allow increasing tanks useful volume and ensure engines’ additional operational lifetime by the example of a launch vehicle, one of Yuzhnoye SDO developments. Determination of 2 Stage PHSS Operability Limits at Increased RE Autonomous Operation Mode Time (after ME Shutdown): Technical Report  21.16234.123 ОТ / Yuzhnoye SDO. (2017) "Set of Actions on Enhancement of Launch Vehicle Payload Capability" Космическая техника. "Set of Actions on Enhancement of Launch Vehicle Payload Capability" Космическая техника. quot;Set of Actions on Enhancement of Launch Vehicle Payload Capability", Космическая техника. Set of Actions on Enhancement of Launch Vehicle Payload Capability Автори: Voloshin M.
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6. Set of Actions on Enhancement of Launch Vehicle Payload Capability

Authors:

Voloshin M. L., Kuda S. А., Mikhalchishin R. V.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2017 (2); 29-34

Language: Russian

Annotation: The paper presents a complex of analytical calculation measures that allow increasing tanks useful volume and ensure engines’ additional operational lifetime by the example of a launch vehicle, one of Yuzhnoye SDO developments. The calculated-experimental confirmation is set forth of the operability of pneumohydraulic supply system in the changed conditions that ensure considerable increase of launch vehicle power and mass characteristics.

Key words:

Bibliography:
1. Logvinenko A. I. Development Prospects of Modern LV Pneumohydraulic Systems. Space Technology. Missile Armaments: Collection of scientific-technical articles. 2014. Issue 1. Dnepropetrovsk.
2. Increasing Dnepr LV 1 and 2 Stages Propellant Filling Doses due to Decrease of their Temperature, Initial Gas Volumes in Tanks and Change of Filling Technology: Technical Report 21.16850.123 ОТ / Yuzhnoye SDO. 54 p.
3. Determination of 2 Stage PHSS Operability Limits at Increased RE Autonomous Operation Mode Time (after ME Shutdown): Technical Report 21.16234.123 ОТ / Yuzhnoye SDO. 75 p.
4. Ostoslavsky I. V. Flight Dynamics. Flying Vehicles Trajectories / I. V. Ostoslavsky, I. V. Strazheva. М., 1969. 499 p.

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6.2.2017 Set of Actions on Enhancement of Launch Vehicle Payload Capability
6.2.2017 Set of Actions on Enhancement of Launch Vehicle Payload Capability
6.2.2017 Set of Actions on Enhancement of Launch Vehicle Payload Capability
]]> 14.1.2017 Design Studies into Dynamic and Structural Characteristics of Two-Stage Direct-Action Solenoid-Operated Hydraulic Valve https://journal.yuzhnoye.com/content_2017_1/annot_14_1_2017-en/ Wed, 28 Jun 2023 11:39:18 +0000 https://journal.yuzhnoye.com/?page_id=29497
Design Studies into Dynamic and Structural Characteristics of Two-Stage Direct-Action Solenoid-Operated Hydraulic Valve Authors: Boiko V. 2017 (1); 88-94 Language: Russian Annotation: The configuration is considered of direct-action electrohydraulic valve ensuring wider operating range of the working fluid flow rate and pressure. As a result of the investigations, the calculated dependencies were obtained that enable evaluating the design parameters impact on valve opening time when designing an electrohydraulic valve of given type. Space Flying Vehicles Reaction Control Systems Valves / O. (2017) "Design Studies into Dynamic and Structural Characteristics of Two-Stage Direct-Action Solenoid-Operated Hydraulic Valve" Космическая техника.
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14. Design Studies into Dynamic and Structural Characteristics of Two-Stage Direct-Action Solenoid-Operated Hydraulic Valve

Authors:

Boiko V. S.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2017 (1); 88-94

Language: Russian

Annotation: The configuration is considered of direct-action electrohydraulic valve ensuring wider operating range of the working fluid flow rate and pressure. The mathematical model of electrohydraulic valve is presented and the computational investigations of dynamic characteristics were performed. As a result of the investigations, the calculated dependencies were obtained that enable evaluating the design parameters impact on valve opening time when designing an electrohydraulic valve of given type.

Key words:

Bibliography:
1. Flying Vehicles Pneumatic Systems Units / I. F. Lyaskovsky, А. I. Shishkov, N. T. Romanenko, М. Т. Romanenko, М. Т. Chernov, V. V. Yemel’yanov; Under the editorship of N. T. Romanenko. М., 1976. 176 p.
2 Rotmansky O. I. Space Flying Vehicles Reaction Control Systems Valves / O. I. Rotmansky, I. R. Krichker. М., 1980. 136 p.
3. Useful Model Patent 95379 Russian Federation, MPK F16K32/02. Electromagnetic Stop Valve (Options) / Applicants and patent holders V. V. Zakharenkov, V. I. Kotelnikov. №2010106035/22; Claimed 19.02.2010; Published 20.08.2014, Bulletin No. 23. 4 p.: il.
4. Roters G. Electromagnetic Mechanisms. М., 1949. 522 p.
5. Patent 89948 Ukraine, MPK F16K32/02. Electrohydraulic Valve / V. M. Shnyakin, V. I. Konokh, B. I. Kotrekhov, А. B. Troyak, V. S. Boiko; Applicant and patent holder Yuzhnoye State Design Office, Dnipropetrovsk. а 2006 02543; Claimed 09.03.2006; Published 25.03.2010, Bulletin No. 6. 4 p.: il.
6. Gutovsky M. V. Reference Book on Designing and Calculation of Aviation Electric Equipment Elements / М. V. Gutovsky, V. F. Korshunov. М., 1962. 165 p.
7. Mathematic Modeling of Liquid Rocket Engines Working Process / Е. N Belyayev, V. K. Chvanov, V. V. Chervakov; Under the editorship of V. K. Chvanov. М., 1999. 228 p.

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14.1.2017 Design Studies into Dynamic and Structural Characteristics of Two-Stage Direct-Action Solenoid-Operated Hydraulic Valve
14.1.2017 Design Studies into Dynamic and Structural Characteristics of Two-Stage Direct-Action Solenoid-Operated Hydraulic Valve
14.1.2017 Design Studies into Dynamic and Structural Characteristics of Two-Stage Direct-Action Solenoid-Operated Hydraulic Valve
]]> 7.2.2019 On critical stress of the longitudinal stability of the stiffened cylindrical shells. Dynamic problem https://journal.yuzhnoye.com/content_2019_2-en/annot_7_2_2019-en/ Mon, 15 May 2023 15:45:47 +0000 https://journal.yuzhnoye.com/?page_id=27209
There is a snap action when zero frequency is achieved for the first time by one of the oscillatory modes.
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7. On critical stress of the longitudinal stability of the stiffened cylindrical shells. Dynamic problem

Authors:

Kaplya P. G.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (2); 50-57

DOI: https://doi.org/10.33136/stma2019.02.050

Language: Russian

Annotation: New theoretical results were obtained in definition of the stability longitudinal stress of the stiffened cylindrical shells both with internal and external arrangement of the stiffened stacks. They were obtained due to application of the dynamic approach to the solution of the refined equilibrium equations, introduction of the Qfactor of the structural elements into the system of equations, definition and application of the forces and moments in the calculation, that act in the sections of the joint bending of the shell and elements of stiffening. Expressions are given, which define the process of stability loss, including parameters of wave generation and amplitude of shell oscillation from the moment of application of the axial compressive force P0 up to the moment of snap action. With dynamic approach to the solution of the problem of the shell’s longitudinal stability the achievement of the first zero frequency by one of the higher modes of bending oscillations of the shell will indicate the loss of stability under the impact of the axial compressive force P0. This process is most obvious during testing of the absolutely flexible shells, which permit multiple loading. In the initial step of shell loading with axial compressive force P0, high-frequency bending oscillations with m, n ˃˃ 1 modes and low amplitudes occur. With a rise in force P0 oscillation frequency begins to drop, and amplitude to increase, with oscillatory mode remaining unchanged. There is a snap action when zero frequency is achieved for the first time by one of the oscillatory modes. This fact allowed formulation of the basic principles of nondestructive method for estimation of the critical stability stress of the flight-ready shell, main point of which is in the comparison of the theoretical curve of the frequency drop due to force P0 action on the structure versus the actual curve of the frequency drop of the flight-ready structure under the impact of the same values of P0 in the elastic range.

Key words: shell rigidity, dynamical problem, nondestructive testing

Bibliography:
1. Kaplya P. G. K voprosu o kriticheskykh napryazheniyakh prodolnoy ustoichivosti gladkykh tsilendricheskikh obolochek. Kosmicheskaya technika. Raketnoe vooruzhenie: sb. nauchn.- techn. st. / GP “KB “Yuzhnoye”. Dnepr, 2017. Vyp. 1. S. 8-17.
2. Kaplya P. G., Pinyagin V. D. K voprosu dinamiki podkreplennykh tsilendricheskikh obolochek. Kosmicheskaya technika. Raketnoe vooruzhenie: sb. nauchn.- techn. st. / GP “KB “Yuzhnoye”. Dnepr, 2009. Vyp. 2. S. 59–73.
3. Timoshenko S. P. Ustoichivost’ sterzhney, plastin I obolochek. M., 1971. S. 257–259, 457–472.
4. Volmir A. S. Ustoichivost’ uprugykh system. M., 1963. S. 463–471, 491–495, 541.
5. Tikhonov V. I. Statisticheskaya radiotechnika. M., 1966. S. 112–115.

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7.2.2019 On critical stress of the longitudinal stability of the stiffened cylindrical shells. Dynamic problem
7.2.2019 On critical stress of the longitudinal stability of the stiffened cylindrical shells. Dynamic problem
7.2.2019 On critical stress of the longitudinal stability of the stiffened cylindrical shells. Dynamic problem

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Plagiarism in all forms represents unethical actions and is unacceptable. Experimental or theoretical investigation may sometimes serve as basis for criticizing the work of another researcher.
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