Search Results for “ground operations” – Collected book of scientific-technical articles

10.1.2024 METHOD OF AUTONOMOUS DETERMINATION OF THE ROCKET’S REFERENCE ATTITUDE DURING PRE-LAUNCH PROCESSING

manager — Mon, 17 Jun 2024 08:44:04 +0000

10. Method of autonomous determination of the rocket’s reference attitude during pre-launch processing

Authors:

Borscheva O. V., Khorolskiy P. G.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2024, (1); 85-92

DOI: https://doi.org/10.33136/stma2024.01.085

Language: Ukrainian

Annotation: To solve the navigation tasks (determination of the apparent accelerations and angular velocities and calculation of rocket orientation angles) in the rocket engineering, the data from the sensing elements (angular velocity sensors and accelerometers) is used. Accuracy of reference attitude determination of the rocket in the steady mode (at lift-off) has great influence on accuracy of the received navigation data during the flight. Gimballess inertial navigation system, built on the basis of inertial MEMS-sensors of Industry class (three angular velocity sensors and three accelerometers), is taken as the navigation device. In the classical version, the integration of data from angular velocity sensors and from accelerometers is the basis of gimballess inertial navigation system operation. It results in accumulation of errors when solving the navigation task (in particular due to the integration of data from angular velocity sensors). Taking it into consideration, the alternative method of rocket’s reference attitude determination during the pre-launch processing is offered. This method does not use mathematical operations of integration and is autonomous. Initial data, received from the gimballess inertial navigation system, is used as the output data. This data is used to determine the rocket’s reference attitude (orientation of object-centered coordinates in the geographical reference system) in the steady mode. Orientation angles are determined without the integration of data picked up from the angular velocity sensors. The comparative analysis to define the processing efficiency of the navigation device initial data was held during the determination of the rocket’s orientation angles in the steady mode, using the proposed method and Runge-Kutta method. The received results showed that accuracy of the reference attitude determination with the proposed method is higher. Thus, the proposed method will help reduce the errors in determination of the rocket’s reference attitude in the steady mode that in the future will improve the accuracy in determination of navigational parameters during the rocket’s flight.

Key words: navigation system, mems-sensors, accelerometers, angular velocity sensors, reference attitude

Bibliography:

Meleshko V.V., Nesterenko O.I. Besplatformennye inertsialnye navigatsionnye systemy. Ucheb. posobie. Kirovograd: POLIMED – Service, 2011. 164 s.
Vlasik S.N., Gerasimov S.V., Zhuravlyov A.A. Matematicheskaya model besplatformennoy inertsialnoy navigatsionnoy systemy i apparatury potrebitelya sputnikovoi navigatsionnoy systemy aeroballisticheskogo apparata. Nauka i technika Povitryannykh Sil Zbroinykh Sil Ukrainy. 2013. № 2(11). s. 166-169.
Waldenmayer G.G. Protsedura pochatkovoi vystavki besplatformennoy inertsialnoy navigatsionoy systemy z vykorystannyam magnitometra ta rozshirennogo filtra Kalmana. Aeronavigatsini systemy. 2012. s. 8.
Korolyov V.M., Luchuk Ye.V., Zaets Ya.G., Korolyova O.I., Miroshnichenko Yu.V. Analiz svitovykh tendentsiy rozvytku system navigatsii dlya sukhoputnykh viysk. Rozroblennya ta modernizatsia OVT. 2011. №1(4). s.19-29. https://doi.org/10.33577/2312-4458.4.2011.19-29
Avrutov V.V., Ryzhkov L.M. Pro alternativniy metod avtonomnogo vyznachennya shyroty i dovgoty rukhomykh obiektiv. Mekhanika gyroskopichnykh system. 2021. №41. s. 122-131. https://doi.org/10.20535/0203-3771412021269255
Bugayov D.V., Avrutov V.V., Nesterenko O.I. Experimentalne porivnyannya algoritmiv vyznachennya orientatsii na bazi complimentarnogo filtru ta filtru Madjvika. Avtomatizatsiya technologichnykh i biznes-protsesiv. 2020. T. 12, №3. s. 10-19.
Chernyak M.G., Kolesnik V.O. Zmenshennya chasovykh pokhibok inertsialnogo vymiryuvalnogo modulya shlyakhom realizatsii yogo strukturnoi nadlyshkovosti na bazi tryvisnykh micromekhanichnykh vymiruvachiv. Mekhanika giroskopichnykh system. 2020. №39. s. 66-80. https://doi.org/10.20535/0203-3771392020229096
Rudik A.V. Matematichna model pokhibok accelerometriv bezplatformenoi inertsialnoi navigatsinoi systemy. Visnyk Vynnitskogo politechnychnogo institutu. 2017. №2. s. 7-13.
Naiko D.A., Shevchuk O.F. Teoriya iomovirnostey ta matematychna statistika: navch. posib. Vinnytsya: VNAU. 2020. 382 s.
Matveev V.V., Raspopov V.Ya. Osnovy postroeniya bezplatformennykh inertsialnykh navigatsionnykh system. SPb.: GNTs RF OAO «Kontsern «TsNII «Electropribor». 2009. 280 s.
Novatorskiy M.A. Algoritmy ta metody obchislen’ [Electronniy resurs]: navch. posib. dlya stud. KPI im. Igorya Sikorskogo. Kiyv: KPI im. Igorya Sikorskogo. 2019. 407 s.

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14.1.2024 EXPERIMENTAL STUDIES OF THE PERFORMANCE OF PYROTECHNIC DEVICES INSTALLED ON THE LAUNCH VEHICLE SEPARATION SYSTEMS

manager — Mon, 17 Jun 2024 07:52:20 +0000

14. Experimental studies of the performance of pyrotechnic devices installed on the launch vehicle separation systems

Автори: Bolyubash Ye. S.

Organization: Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2024, (1); 121-128

DOI: https://doi.org/10.33136/stma2024.01.121

Language: Ukrainian

Annotation: Pyrotechnic devices are important elements in rocket and space technology, which to a large degree determine the flight success of the launch vehicles, since they enable instantaneous operations to separate spent stages, change configurations, ensure safety, etc. Pyrotechnic devices are subject to strict requirements for reliability, safety, security and efficiency. The article presents an experimental study of the performance of a linear shaped charge of a launch vehicle stage separation system. This type of linear shaped charge is one of the most common types of linear shaped charge, which are used in launch vehicle separation systems being developed in Ukraine. One of the main characteristics of the linear shaped charge, which determines the efficiency and reliability of the separation process, is the depth of penetration of the cumulative jet into the obstacle. The work studied the effect of a cumulative jet of a linear shaped charge with a semi-cylindrical cumulative part. An experimental confirmation of the performance of this type of linear shaped charge is presented, using the example of a linear shaped charge with a diameter of 5 mm, acting on an obstacle made of aluminum alloy grade 2219. The research methodology, experimental scenario, in particular, a description of the research object and a scheme for measuring test results are presented. Depth of cumulative jet penetration into the obstacle was measured in 60 points along the cut line of the samples under study. A statistical analysis of the experimental results was carried out, in particular, the average penetration depth was determined. An improved formula is proposed for the practical calculation of the penetration depth of a cumulative jet for a linear shaped charge with a semi-cylindrical cumulative part, using an additional correction factor. It is noted that the depth of penetration of a cumulative jet into an obstacle is significantly influenced by technological aspects. Taking into account this influence, the lower limit of the one-sided tolerance interval was determined. Recommendations are provided to improve future experimental procedures. Based on the obtained results, it was established that the linear shaped charges under study are operational and meet the requirements for linear shaped charges, installed on launch vehicle separation systems.

Key words: cumulative effect, shaped charge, linear shaped charge, separation systems, pyrotechnic separation devices, linear shaped charge parameters.

Bibliography:

Petushkov V. G. Pod red. B.Ye.Patona, Priminenie vzryva v svarochnoy technike, K.: Nauk. dumka, 2005, 754 s.
Physika vzryva. Izd. tretie, t. ІІ. Pod red. L. P. Orlenko. Nauka, 2004, 644 s.
Baum F. A., Stanyukovich K. P., Shekhter B. I. Physika vzryva. Gos. izd. FM lit. M. 1959, 800 s.
Kolesnikov K. S., Kozlov V. I., Kokushkin V. V. Dynamika razdeleniya stupeney letatelnykh apparatov. M.: Mashinostroenie. 1977, 224 s.
Kumulyativniy efect ta iogo vykorystannya dlya rozdilennya raketno-kosmichnykh elementiv za dopomogou pyrotechnichnykh prystroiv. Ye. S. Bolyubash. Materialy XVII naukovykh chytan’ «Dniprovska orbita – 2022» (26–28 zhovtnya). Dnipro, 2022. 263 s.
ISO 16269-6:2003 Statistical interpretation of data – Part 6: Determination of statistical tolerance intervals (IDT).
Kobzar A. N. Prikladnaya matematicheskaya statistika. Dlya inzhenerov i nauchnykh rabotnikov. M.: Phizmatlit, 2006, 816 s.

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7.1.2020 Studying the motion of a launch vehicle and observed space debris objects during launch preparation

Вацлав Самусевич — Wed, 13 Sep 2023 06:27:07 +0000

7. Mechanics of a satellite cluster. Methods for estimating the probability of their maximal approach in flight

Authors:

Holubek O. V.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2020, (1); 76-84

DOI: https://doi.org/10.33136/stma2020.01.076

Language: Russian

Annotation: The mathematic modeling was performed of the flight of light-class three-stage launch vehicle injecting a payload into sun-synchronous orbit of 700 km altitude and a cluster of observed space debris objects in the conditions of dynamically changing cataloged space situation. It is shown that as the launch moment becomes closer, the cataloged space situation is ascertained, which leads to the constant change of the quantity of hazardous space debris objects observed in the vicinity of launch vehicle trajectory and to the change of the parameters of their approach to the launch vehicle: minimal relative distance, relative velocity, rendezvous angle and launch moment for which hazardous approach is revealed. The hazardous approaches for the launch vehicle trajectory under consideration are more often observed with the relative velocities of more than 8 km/s and rendezvous angles less than 90 deg and their variations within the launch window do not exceed 1.2 m/s and 0.035 deg respectively. In this case, the histograms of distribution of relative distance, relative velocity, and rendezvous angle from catalog to catalog vary insignificantly. The distribution of hazardous approaches in launch time within launch window is not uniform, the regions are observed with low quantity of hazardous approaches and with high quantity. The hazard of launch vehicle collision with observed space debris objects in a launch is confirmed. In all, in the launch day time window under consideration, more than ten hazardous approaches are revealed, for two of them the approach to minimal distance of less than 1 km is predicted. This testifies to the necessity of taking measures to increase safety of launch vehicle flight through observed space debris cluster. In order to increase Ukrainian launch vehicles miss ion safety in the conditions of near space pollution, it is proposed to create the system of pre -flight space analysis, whose tasks are periodic analysis of space situation not less than once in a day, revealing of hazardous approaches, determination of their parameters, and preparation of data to make decision on launch time.

Key words: method of launch time planning, safety of flight through space debris cluster

Bibliography:

1. ESA Operations. For the first time ever, ESA has performed a ‘collision avoidance manoeuvre’ to protect one of its satellites from colliding with a ‘mega constellation’. Electronic resource. – Access mode: https://twitter.com/esaoperations/status/ 1168533241873260544 (Access date 12.09.2019).

2. Klinkrad H. Space Debris – Models and Risk Analysis. Chichester, UK: Praxis Publishing Ltd, 2006. 430 p.

3. Johnson N. L. Orbital Debris: The Growing Threat to Space Operations / Advances in the Astronautical Sciences. 2010. Vol. 137. P. 3-11.

4. Orbital Debris. A Technical Assessment. Washington, D.C.: National Academy Press, 1995. 210 p.

5. Bandyopadhyay P., Sharma R.K., Adimurthy V. Space debris proximity analysis in powered and orbital phases during satellite launch / Advances in Space Research. 2004. Vol. 34. P. 1125-1129. https://doi.org/10.1016/j.asr.2003.10.043

6. Adimurthy V., Ganeshan A. S. Space debris mitigation measures in India / Acta Astronautica. 2005. Vol. 58. P. 168-174. https://doi.org/10.1016/j.actaastro.2005.09.002

7. Schultz E. D., Schultz E. D., Wilde P. D. Mitigation of Collision Hazard for the International Space Station from Globally Launched Objects / 6th IAASS Conference Safety is Not an Option. 21-23 May 2013. Montreal, Canada. Electronic resource. Access mode: https://iaassconference2013.-space-safety.org/ wp-content/uploads/sites/-19/2013/06/ 1420_Shultz.pdf (Access date 12.09.2019).

8. Brevdik G. D., Strub J. E. Determination of acceptable launch windows for satellite collision avoidance / AAS/AIAA Astrodyna-mics Conference. 19-21 August 1991 Pt1. Durango USA. Astrodynamics. P. 345-356.

9. Hejduk M. D., Plakalovic D., New-man L. K., Ollivierre J. C., Hametz M. E., Beaver B. A., Thompson R. C. Trajectory Error and Covariance Realism for Launch Cola Operations / Advances in the Astronautical Sciences. 2013. Vol. 148. P. 2371-2390.

10. Hejduk M. D., Plakalovic D., New-man L. K., Ollivierre J. C., Hametz M. E., Beaver B. A., Thompson R. C. Recommended Risk Assessment Techniques and Thresholds for Launch Cola Operations / Advances in the Astronautical Sciences. 2014. Vol. 150. P. 3061-3080.

11. Handschuh D. A., Wang C., Vidal B. Operational Feedback on Four Years of Collision Risk Avoidance at Launch in Europe / 7th IAASS Conference Space Safety is No Accident, 20-22 October 2014. Fredrichschafen, Germany. P. 355-363. https://doi.org/10.1007/978-3-319-15982-9_42

12. Ihdalov I. М., Kuchma L. D., Poliakov N. V., Sheptun Yu. D. Dinamicheskoe proektirovanie raket. Zadachi dinamiki raket i ikh kosmicheskikh stupenei: mohografiia / pod red. akad. S. N. Koniukhova. Dnepropetrovsk, 2010. 264 s.

13. NIMA TR 8350.2. Department of Defense world geodetic system 1984: Its definition and relationships with local geodetic systems. 3-d ed. National Geospatial-Intelligence Agency, 2000. 174 p.

14. NGA EGM2008 – WGS 84 version. Electronic resource. Access mode to page: http://earth-info.nga.mil/GandG/ wgs84/gravitymod/egm2008/ gm08_wgs84.html. (Access date 12.09.2019).

15. Holubek А. V. Sblizheniie rakety-nositelia s katalogizirovannymi kosmicheskimi ob’ektami v processe vyvedeniia na orbity s nizkim nakloneniem / Izvestiia vysshikh uchebnykh zavadenii. Mashinostroenie. 2018. №2 (695). S. 86-98.

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8.2.2018 Development of Nozzle Blocks New Manufacturing Technology without Blazing

Вацлав Самусевич — Thu, 07 Sep 2023 11:21:51 +0000

8. Development of Nozzle Blocks New Manufacturing Technology without Blazing

Authors:

Kovalenko A. M.¹, Kirsanov D. V.¹, Mirosidi M. A.¹, Shelyagin V. D.², Bernatsky A. V.², Siora O. V.²

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine¹; STC «Paton Welding Institute», Kiev, Ukraine²

Page: Kosm. teh. Raket. vooruž. 2018 (2); 68-75

DOI: https://doi.org/10.33136/stma2018.02.068

Language: Russian

Annotation: The article describes the problems of manufacturing large-size nozzle blocks by classical for Ukrainian space industry method of high-temperature brazing. The Yuzhnoye SDO-selected way of solving this problem and the first strides on the way to organization of new production using innovative technologies of laser welding and surfacing are presented. The step-by-step sequence and procedure of research work to develop and test a new technology of cooled nozzle block manufacturing are described. Four phases are identified, out of which the first two phases have already been successfully performed. The laser welding and surfacing technology will allow avoiding the use of costly and unique equipment and will allow reducing and optimizing the technological manufacturing cycle rejecting the long –term and energy-consuming technological operations. The scientific-and-technological works performed showed the principle feasibility of making connection between the external jacket and internal wall of a nozzle block using laser welding. The test samples manufactured confirmed the high strength characteristics, which had been preliminary obtained by the theoretical calculation methods. The sections obtained by surfacing demonstrate good metallurgical connection between the layers. On the test samples, the technique was tried-out allowing repairing defect areas in a welded seam obtained by laser welding method. This is especially important from the technological and economic viewpoints, as the technology of high-temperature brazing applied currently does not allow making guaranteed repair of brazed joints.

Key words: liquid rocket engine nozzles, laser, laser welding, laser surfacing

Bibliography:

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2.1.2018 Dehydration of Hydrocarbon Fuels by Method of Over-Saturation Drop

Вацлав Самусевич — Mon, 04 Sep 2023 12:45:06 +0000

2. Dehydration of Hydrocarbon Fuels by Method of Over-Saturation Drop

Authors:

Salo М. P., Tereschenko K. O., Ivanitsky G. М.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (1); 6-12

DOI: https://doi.org/10.33136/stma2018.01.006

Language: Russian

Annotation: An alternative method of kerosene dehydration is proposed, which is based on application of cyclic technology of supersaturation decrease using dry nitrogen. A comparison of nitrogen and time specific consumption in dehydration operations is done and recommendations are given for their use in the cosmodromes’ launch complexes fuel storage and preparation facilities.

Key words:

Bibliography:

1. Zrelov V. N., Seryogin E. P. Liquid Rocket Propellants. М., 1975. 320 p.
2. Energy-Intensive Fuels for Aircraft and Rocket Engines / Under the editorship of L. S. Yanovsky. М., 2009. 400 p.
3. Soyuz-2. URL: https://ru.wikipedia.org/wiki/Soyuz-2_(launch vehicle family).
4. Angara. URL: https://ru.wikipedia.org/wiki/Angara_(launch vehicle).
5. Zenit-2. URL: https://ru.wikipedia.org/wiki/Zenit-2_(launch vehicle).
6. Leshchiner L. B., Ul’yanov I. E. Designing of Aircraft Fuel Systems. М., 1975. 344 p.
7. Zenit Space Launch System from the Eyes of its Developers / Under the editorship of e.d. professor V. N. Solov’yov, e.d. professor G. P. Biryukov, N. S. Kozhukhov, N. I. Kursenkova. М., 2003. 213 p.
8. Space Rocketry Ground Infrastructure Technological Facilities: Engineering Manual. Book 1. М., 2005. 416 p.
9. Investigation of Prospective Propellant Preparation Technologies: Scientific-Technical Report 21.18258.173ОТ / Yuzhnoye SDO. 2016. 115 p.
10. Shleifer A. A., Litvinov A. N. Prospective Technologies to Prepare Propellants with Improved Performance Properties. Ul’yanovsk, 1989. 215 p.
11. Englin B. A. Use of Liquid Propellants at Low Temperatures. 3-rd edition revised and enlarged. М., 1980. 207 p.
12. Volkov A. I., Zharsky I. M. Big Chemical Guide. Minsk, 2005. 608 p.
13. Calculated Evaluation and Experimental Check of RPC Degassing and Saturation by Helium for Filling Cyclone-4 LV: Technical Note Cyclone-4. 22.6849.123 СТ / Yuzhnoye SDO. 2005. 29 p.

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8.1.2019 Virtual Tests of Cassette Reentry Vehicle Dash Elements Attachment System during Ground Operation

manager — Thu, 25 May 2023 12:09:45 +0000

8. Virtual Tests of Cassette Reentry Vehicle Dash Elements Attachment System during Ground Operation

Authors:

Tonkonozhenko A. M.¹, Kozharin V. Y.¹, Martynenko G. Y.³, Chernobryvko M. V.², Avramov K. V.²

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine¹; Pidgorny A. Intsitute of Mechanical Engineering Problems, Kharkiv, Ukraine²; National Technical University “Kharkiv Polytechnic Institute”, Kharkiv, Ukraine³

Page: Kosm. teh. Raket. vooruž. 2019, (1); 54-63

DOI: https://doi.org/10.33136/stma2019.01.054

Language: Russian

Annotation: This paper describes the effective approach for the technology of the rocket airframe development testing, based on the method of numerical modelling, which enables the virtual experimental runs prior to the beginning of the development testing to check the performance of the standard airframes and predict issues of concern. The method is realized based on the computer models developed in the ANSYS Workbench environment. Based on the offered method the complex mechanical system, which attaches the cluster projectiles in the conditions of the temperature exposure and heat cycling, underwent the virtual tests. Computational models, criteria and test procedures necessary for the analysis of the mechanical condition and prediction of the performance of the actual airframe of the warhead were developed. Moreover, computational models consider all the design and technological features of the airframe: layout of the projectiles attachments, initial stress-strain state of the system after the tightening of the threaded connections, friction between the components of the system and their mutual displacement, temperature dependence of the physical and mechanical characteristics and ultimate stress of materials. For the specified loading conditions during the ground operations with the warhead, the most dangerous computational cases are determined which have been implemented during the virtual tests. Test results were used to conduct the static analysis of the mechanical condition, strength and conditions for performance of the actual structure of the attachment under the impact of the operating levels of temperature exposure and heat cycling. Results of the virtual tests confirm the performance of the projectiles attachment system and are introduced into production in the phase of engineering development.

Key words: computer modelling, computational models, ground operations, mechanical condition, performance

Bibliography:

1. Birger I. A., Iosilevich G. B. Rezbovye i flantsevye soedineniya. M.: Mashinostroenie, 1990. 368 p.
2. Kukhling Ch. Spravochnik po phisike. M.: Mir, 1985. 520 p.
3. Nikolskiy B. P., Rabinovich V. A. Spravochnil chimika. T. 6. L.: Chimiya, 1967. 1009 p.
4. Stali I splavy. Marochnik: Sprav. izd. / pod red. V. G. Sorokina, M. A. Gervasieva. M.: Intermet Engineering, 2001. 608 p.
5. Numerical simulation of missile warhead operation / G. Martynenko, M. Chernobryvko, K. Avramov, V. Martynenko, A. Tonkonozhenko, V. Kozharin, D. Klymenko / Advances in Engineering Software. 2018. Vol. 123. P. 93-103. https://doi.org/10.1016/j.advengsoft.2018.07.001

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6.1.2019 Investigation into Peculiarities of Delivery to Launch Base of Rocket Propellant with Specified Gasing

manager — Thu, 25 May 2023 12:09:32 +0000

6. Investigation into Peculiarities of Delivery to Launch Base of Rocket Propellant with Specified Gasing

Authors:

Pozdieiev H. L., Kucherenko R. A., Kucherenko T. V.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (1); 38-44

DOI: https://doi.org/10.33136/stma2019.01.038

Language: Russian

Annotation: This article considers the issue of achievement of the specified value of propellants saturation by helium after their delivery from the manufacturers to the launch site. Knowing the fact that propellants gas saturation or gas separation processes are labour-consuming and costly this issue is of immediate interest. In order to solve this problem number of factors have been considered, which determine the value of gas saturation in the propellants delivered to the launch site and procedure to control the value of gas saturation by the fuel manufacturer has been developed. This procedure implies that shipping tank container is pressurized after being fueled with propellants at the manufacturer’s, the pressure is characterized by the value of the known initial deficit or excess of gas in the propellants, following which tank container is delivered to the launch site. During transportation tank container is subjected to various kinds of mechanical actions (vibration, rolling and pitching in the sea, braking, transshipment), therefore intensive mixing of propellants occur. As propellants mix, process of propellant saturation occurs when certain amount of gas transits from tank container’s gas volume into the liquid, therefore certain gas saturation is reached. Article includes the measuring results of the gas liquid medium parameters inside the tank containers with fuel in the process of fuel transportation to Ukraine from PRC factories and estimations of the measuring results using the developed model which confirmed the quantitative nature of the mass exchange processes, included in the model, going on in the gas liquid medium during transportation of the tank container with fuel equipment. It has been determined that due to inevitable errors in the measuring of the specified parameters by the tank container, the achievement of the specified gas saturation with high precision is problematic. In spite of the fact that this procedure does not provide exact value of the specified gas saturation, its application will accelerate and make cheaper the process of fuel preparation for filling operations at the launch site, which is especially relevant in case of fuel saturation by helium. Based on this fuel saturation by helium procedure, the complex technology is suggested, providing controlled gas saturation during fuel delivery and subsequent adjustment of gas saturation using launch site equipment. Therefore, this article develops and studies the original model of the controlled gas saturation of the fuel during its delivery to the consumer. Alternative of the practical use of the study results is suggested in the form of the complex technology of fuel saturation by helium, delivered in the tank containers from the manufacturer to the launch site.

Key words: oxidizer, fuel, saturation by helium, tank container, transportation

Bibliography:

1. Volskiy A. P. Kosmodrom. M.: Voenizdat, 1977. 311 p.
2. Stepanov A. N., Vorobiev A. M., Grankin B. K. Kompleksy zapravki raket I kosmicheskikh apparatov. SPB:OM-PRESS, 2004. 26 p.
3. Kiriyanova A. N., Matveeva O. P. Opredelenie kolebania davlenia v gazovoy polosti hermetychikh emkostey transportnozapravochnykh containerov dlya raketnykh topliv pri temperaturnykh vozdeistviyakh/ Nauka i innovatsii. 2016. Vyp. 7.
4. Berezhkovskiy M. I. Khranenie i transportirovka khimicheskykh produktov. – M.: Khimia, 1973. – 272 s.
5. Perepelkin K. Ye., Matveev V. S. Gazovye emulsii. L.:Khimia, 1979. 200 p.
6. Issledovanie protsessov degazirovaniya komponentov topliva v conteinere-tsisterne pri dostavke topliva potrebitelyu. Cyclone4M 21.18425.174 OT: Techn. report. Dnepropetrovsk: Yuzhnoye SDO, 2017. 39 p.

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5.1.2019 Methodology of Normative Principles of Justification of Launch Vehicle Launching Facility Structures Lifetime

manager — Thu, 25 May 2023 12:09:25 +0000

5. Methodology of Normative Principles of Justification of Launch Vehicle Launching Facility Structures Lifetime

Authors:

Hudramovych V. S.¹, Sirenko V. M.², Klimenko D. V.², Daniyev Y. F.¹, Hart Ye. L.³

Organization:

The Institute of Technical Mechanics, Dnipro, Ukraine¹; Yangel Yuzhnoye State Design Office, Dnipro, Ukraine²; Oles Honchar Dnipro National University, Dnipro, Ukraine³

Page: Kosm. teh. Raket. vooruž. 2019, (1); 28-37

DOI: https://doi.org/10.33136/stma2019.01.028

Language: Russian

Annotation: This article contains results of methodology and standards development for life prediction of launch site structures to launch various types’ launch vehicles into near-earth orbit. Launch sites have been built in various countries of the world (European Union, India, China, Korea, Russia, USA, Ukraine, France, Japan, etc.). In different countries they have their own characteristics, depending on the type and performance of the launch vehicles, infrastructure features (geography of the site, nomenclature of the space objects, development level of rocket and space technology), problems that are solved during launches, etc. Solution of various issues, arising in the process of development of the standards for justification of launch site life is associated with the requirement to consider complex problems of strength and life of nonuniform structural elements of launch sites and structures of rocket and space technology. Launch sites are the combination of technologically and functionally interconnected mobile and fixed hardware, controls and facilities, designed to support and carry out all types of operations with integrated launch vehicles. Launch pad, consisting of the support frame, flue duct lining and embedded elements for frame mounting, is one of the principal components of the launcher and to a large extent defines the life of the launch site. Main achievements of Ukrainian scientists in the field of strength and life are specified, taking into account the specifics of various branches of technology. It is noted that the physical nonlinearity of the material and statistical approaches determine the strength analysis of useful life. Main methodological steps of launch site structures life prediction are defined. Service limit of launch site is suggested to be the critical time or the number of cycles (launches) over this period, after which the specified limiting states are achieved in the dangerous areas of the load-bearing elements: critical cracks, destruction, formation of unacceptable plastic deformations, buckling failure, corrosion propagation, etc. Classification of loads acting on the launch sites is given. The useful life of launch site is associated with estimation of the number of launches. Concept of low and multiple-cycle fatigue is used. Developing strength standards and useful life calculation basis, it is advisable to use modern methods of engineering diagnostics, in particular, holographic interferometry and acoustic emission, and to develop the high-speed circuits of numerical procedures for on-line calculations when testing the designed systems.

Key words: classification of loads and failures; shock wave, acoustic and thermal loads; low-cycle fatigue; hierarchical approach in classification; projection-iterative schemes of numerical procedur

Bibliography:

1. Vidy startovykh kompleksov: GP KB «Yuzhnoye»: Rezhim dostupa. http://www.yuzhnoe.com/presscenter/media/ photo/techique/launch-vehique.
2. Modelyuvannya ta optimizatsia v nermomechanitsi electroprovidnykh neodnoridnykh til: u 5 t. / Pid. zag. red. akad. NANU R. M. Kushnira. Lvyv: Spolom, 2006–2011. T. 1: Termomechanika bagatokomponentnykh til nyzkoi electroprovodnosti. 2006. 300 p. T. 2: Mechanotermodiffusia v chastkovo prozorykh tilakh. – 2007. 184 p. T. 3: Termopruzhnist’ termochutlyvykh til. 2009. 412 p. T. 4: Termomechanica namagnychuvannykh electroprovodnykh nermochutlyvykh til. 2010. 256 p. T. 5. Optimizatsia ta identifikatsia v termomechanitsi neodnoridnykh til. 2011. 256 p.
3. Prochnost’ materialov I konstruktsiy / Pod obsch. red. acad. NANU V. T. Troschenko. K.: Academperiodika, 2005.1088 p.
4. Bigus G. A. Technicheskaya diagnostica opasnykh proizvodstvennykh obiektov/ G. A. Bigus, Yu. F. Daniev. М.: Nauka, 2010. 415 p.
5. Bigus G. A., Daniev Yu. F., Bystrova N. A., Galkin D. I. Osnovy diagnostiki technicheskykh ustroistv I sooruzheniy. M.: Izdatelstvo MVTU, 2018. 445 p.
6. Birger I. A., Shorr B. F., IosilevichG. B. Raschet na prochnost’ detaley machin: spravochnik. M.: Mashinostroenie, 1993. 640 p.
7. Hudramovich V. S. Ustoichivost’ uprugoplasticheskykh obolochek. K.: Nauk. dumka, 1987. 216 p.
8. Hudramovich V. S. Teoria polzuchesti i ee prilozhenia k raschetu elementov konstruktsiy. K.: Nauk. dumka, 2005. 224 p.
9. Hudramovich V. S., Klimenko D. V., Gart E. L. Vliyanie vyrezov na prochnost’ cylindricheskykh otsekov raketonositeley pri neuprugom deformirovanii materiala/ Kosmichna nauka i technologia. 2017. T. 23, № 6. P. 12–20.
10. Hudramovich V. S., Pereverzev Ye. S. Nesuschaya sposobnost’ sposobnost’ i dolgovechnost’ elementov konstruktsiy. K.: Nauk. dumka, 1981. 284 p.
11. Hudramovich V. S., SIrenko V. N., Klimenko D. V., Daniev Yu. F. Stvorennya metodologii nornativnykh osnov rozrakhunku resursu konstruktsii startovykh sporud ksomichnykh raket-nosiiv / Teoria ta practika ratsionalnogo proektuvannya, vygotovlennya i ekspluatatsii machinobudivnykh konstruktsiy: materialy 6-oy Mizhnar. nauk.-techn. conf. (Lvyv, 2018). Lvyv: Kinpatri LTD, 2018. P. 5–7.
12. Hudramovich V. S., Skalskiy V. R., Selivanov Yu. M. Golografichne ta akustico-emissine diagnostuvannya neodnoridnykh konstruktsiy i materialiv: monografia/Za red. akad. NANU Z. T. Nazarchuka. Lvyv: Prostir-M, 2017. 492 p.
13. Daniev Y. F. Kosmicheskie letatelnye apparaty. Vvedenie v kosmicheskuyu techniku/ Pod obsch. red. A. N. Petrenko. Dnepropetrovsk: ArtPress, 2007. 456 p.
14. O klassifikatsii startovogo oborudovania raketno-kosmicheskykh kompleksov pri obosnovanii norm prochnosti/ A. V. Degtyarev, O. V. Pilipenko, V.S. Hudramovich, V. N. Sirenko, Yu. F. Daniev, D. V. Klimenko, V. P. Poshivalov// Kosmichna nauka i technologia. 2016. T. 22, №1. P. 3–13. https://doi.org/10.15407/knit2016.01.003
15. Karmishin A. V. Osnovy otrabotky raketno -kosmicheskykh konstruktsiy: monografia. M.: Mashinostroenie, 2007. 480 p.
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20. TEchnologicheskie obiekty nazemnoy infrastructury raketno-kosmicheskoy techniki: monografia/ Pod red. I. V. Barmina. M.: Poligrafiks RPK, 2005. Kn. 1. 412 p.; 2006. Kn. 2. 376 p.
21. Нudrаmоvich V. S. Соntact mechanics of shell structures under local loading/ International Аррlied Месhanics. 2009. Vol. 45, № 7. Р. 708– 729. https://doi.org/10.1007/s10778-009-0224-5
22. Нudrаmоvich V. Еlесtroplastic deformation of nonhomogeneous plates / I. Eng. Math. 2013. Vol. 70, Iss. 1. Р. 181–197. https://doi.org/10.1007/s10665-010-9409-5
23. Нudrаmоvich V. S. Mutual influence of openings on strength of shell-type structures under plastic deformation / Strenght of Materials. 2013. Vol. 45, Iss. 1. Р. 1–9. https://doi.org/10.1007/s11223-013-9426-5
24. Mac-Ivily A. J. Analiz avariynykh razrusheniy / Per. s angl. M.: Technosfera, 2010. 416 p.
25. Наrt Е. L. Ргоjесtion-itеrаtive modification оf the method of local variations for problems with a quadratic functional / Journal of Аррlied Мahtematics and Meсhanics. 2016. Vol. 80, Iss. 2. Р. 156–163. https://doi.org/10.1016/j.jappmathmech.2016.06.005
26. Mesarovich M. Teoria ierarkhicheskykh mnogourovnevykh system/ M. Mesarovich, D. Makho, I. Tohakara / Per. s angl. M.: Mir, 1973. 344 p.

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13.1.2019 Prediction of Solid Propellant Burnout Time in Launch Vehicle Propulsion System in Flight

manager — Wed, 24 May 2023 16:00:19 +0000

13. Prediction of Solid Propellant Burnout Time in Launch Vehicle Propulsion System in Flight

Authors:

Holubek O. V., Filippenko I. M., Tatarevsky K. E.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (1); 87-94

DOI: https://doi.org/10.33136/stma2019.01.088

Language: Russian

Annotation: This article considers the problem of determination of propulsion system solid fuel burn-out time in the extraatmospheric flight segment taking the apparent acceleration and apparent speed measured by the inertial navigation system. Correlation analysis of the realized and nominal dependencies of the apparent acceleration and apparent speed of the launch vehicle on relative operating time of the propulsion system is suggested to be used to forecast the fuel burn-out time. In order to improve the accuracy of the forecast, and to decrease the amplitude and vibration rate of its results several channels simultaneously are suggested to be used for calculations with subsequent majority voting and digital filtration. As a result of the study, the procedure to forecast the time of solid fuel burn-out in the launch vehicle propulsion system in flight has been developed. Operability of the suggested procedure has been verified using the mathematical simulation of the launch vehicle flight for two operating modes of the propulsion system different from the nominal ones. Based on the statistical processing of the deviations of the predicted time of solid fuel burn-out versus the realized one it was determined that the forecast based on the results of apparent acceleration measurement has the greatest accuracy with the minimal number of operations. Suggested procedure is easily realized as the multistage adaptive algorithm and can be used in the guidance system of the solid-propellant launch vehicle in the extra-atmospheric flight segment for the numerical forecast of the reachable terminal parameters of flight, definition of command vector and development of the relevant thrust vector control commands.

Key words: guidance system, correlation analysis, procedure, mathematical simulation

Bibliography:

1. Osnovy teorii avtomaticheskogo upravleniya raketnymi dvigatelnymi ustanovkami / A. I. Babkin, S. I. Belov, N.B. Rutovskiy i dr. – M.: Mashinostroenie, 1986. – 456 s.
2. Proektirovanie system upravleniya obiektov raketno-kosmicheskoy techniki. T. 1. Proektirovanie system upravlenia raket-nositeley: Uchebnik/Yu. S. Alekseev, Yu. Ye. Balabey, T. A. Baryshnikova i dr.; Pod obshey red. Yu. S. Alekseeva, Yu. M. Zlatkina, V. S. Krivtsova, A. S. Kulika, V. I. Chumachenko. – Kh.: NAU «KhAI», NPP «Khartron-Arkos», 2012. – 578 s.
3. Sikharulidze Yu. G. Ballistika letatelnykh apparatov. – M.: Nauka, 1982. – 352 s.
4. Lysenko L. N. Navedenie I navigatsia ballisticheskykh raket: Ucheb. posobie. – M.: Izd-vo MGTU im. N. E. Baumana, 2007. – 672 s.
5. Systemy upravleniya letatelnymi apparatami (ballisticheskimi raketami I ikh golovnymi chastyami): Uchebnik dlya VUZov/ G. N. Razorenov, E. A. Bakhramov, Yu. F. Titov; Pod red. G. N. Razorenova. – M.: Mashinostroenie, 2003. – 584 s.
6. Siouris G. M. Missile guidance and control systems. – New York: Springer-Verlag New York, Inc., 2004. – 666 p. https://doi.org/10.1115/1.1849174
7. Zarchan P. Tactical and Strategic missile guidance. – American Institute of Aeronautics and Astronautics, Inc., 2012. – 989 p. https://doi.org/10.2514/4.868948
8. Balakrishnan S. N. Advances in missile guidance, control, and estimation / S. N. Balakrishnan, A. Tsourdos, B.A. White. – New York: CRC Press, Taylor & Francis Group. 2013. – 682 p.
9. Shneydor N. A. Missile guidance and pursuit: kinematics, dynamics and control. – Horwood Publishing Chichester, 1998. – 259 p. https://doi.org/10.1533/9781782420590
10. Yanushevsky R. Modern missile guidance. – CRC Press, Taylor & Francis Group, 2008. – 226 p. https://doi.org/10.1201/9781420062281

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9.1.2023 Methodology for selecting design parameters of solid-propellant sustainer engines. Mathematical support and software

manager — Fri, 12 May 2023 16:11:14 +0000

9. Methodology for selecting design parameters of solid-propellant sustainer engines. Mathematical support and software

Authors:

Yenotov V. H., Kushnir B. I., Pustovharova O. V., Chubarov A. M.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2023 (1); 77-87

DOI: https://doi.org/10.33136/stma2023.01.077

Language: Ukrainian

Annotation: Substantiation of the research tools has been performed as a part of methodology development for the air and missile defense system. The problem under consideration is very complex due to the multifactorial nature of the research object, its qualitative variety and manifold structure, incomplete definition of the problem statement. Furthermore, the ability of modern technologies to produce different arms systems, which are capable of carrying out same class tasks, considerably increases the risk of making not the best decisions. Based on this, as well as taking into account the sharp increase in the cost of weaponry, the considered problem is classified as an optimization one that should be solved through the theory of operations research. In this theory, such task is viewed as a mathematical problem, and mathematical simulation is the basic method of research. The main types of mathematical models, their areas of application have been considered as a part of the analysis. The classification of mathematical models has been indicated according to the scale of reproduced operations, purpose, and goal orientation. Quantitative and qualitative correlation of forces has been accepted as the efficiency criterion, which determines a goal orientation of the model. The problems related to this have been shown. In particular, searching for the compromise between simplicity of the mathematical model and its adequacy to the research object is among these problems. Two of the basic approaches to principles of the military operation model construction and its assessment have been considered. The first is implemented through modeling of the combat operations. The second approach is based on the assumption that different armament types can be compared based on their contribution to the outcome of the operation, and on the possibility to assign «a weighting coefficient» named as a combat potential to each of these types. The modern level of problem solving related to this method has been shown. The reasonability of its application in the considered task, including the definition of forces correlation of the opposing parties, has been substantiated. The basic regulations of the construction concept of the required mathematical model and tools for its research have been formulated based on the analysis results: the assigned problem should be solved by analytical methods through the theory of operations research; the analytical model is the most acceptable conception of the analyzed level of the military operation; the synthesis of the model should be based on the idea of a combat potential. At the same time, it should be taken into account that the known approach to the definition of forces correlation, which uses the combat potential method, has a number of essential limitations, including the methodological ones. Therefore, within the bounds of further research, this approach requires the development both in terms of improving the reliability of the single assessment and in terms of giving the system qualities to the synthesized mathematical model.

Key words: multifunctional system, mathematical model, military unit, combat potential, correlation of forces, defensive sufficiency

Bibliography:

1. Pavlyuk Yu. S. Ballisticheskoe proektirovanie raket: ucheb.-metod, posobie dlya vuzov. UDK623.451.8. Izd-vo ChGTU, Chelyabinsk, 1996. 92 s.
2. Nikolaev Yu. M., Solomonov Yu. S. Inzhenernoe proektirovanie upravlyaemykh ballisticheskikh raket s RDTT. M., 1979. 240 s.
3. Enotov V. G., Kirichenko A. S., Pustovgarova Ye. V. Osobennosti rascheta i vybora raskhodnoy diagrammy dvukhrezhimnykh marshevykh RDTT: ucheb.-metod. posobie. Pod red. akadem. A. V. Degtyreva. Dnepr, 2019. 68 s.
4. Enotov V. G., Kushnir B. I., Pustovgarova Ye. V. Metodika-programma proektnoy otsenki characteristic marshevykh dvigateley na tverdom toplive s korpusami iz vysokoprochnykh metallicheskikh materialov, statsionarnymi soplami i postanovka ee na avtomatizirovanniy raschet: ucheb.-metod. posobie. Vtoroe izd., pererabot. i dop. Pod red. A. S. Kirichenko. Dnep, 2019. 91 s.
5. Enotov V. G., Kirichenko A. S., Kushnir B. I., Pustovgarova Ye. V. Metodika proektnoy otsenki characteristic marshevykh dvigatelnykh ustanovok na tverdom toplive s povorotnymi upravlyayuschimi soplami, plastikovymi tselnomotannymi korpusamy i postanovka ee na avtomatizirovanniy raschet: ucheb.-metod. posobie. Vtoroe izd., pererabot. i dop. Pod red. akadem. A. V. Degtyareva. Dnepr. 2019. 149 s.
6. Alemasov V. Ye., Dregalin A. F., Tishin A. P. Teoriya raketnykh dvigateley. M., 1980. 55 s.
7. Raschetnye materialy dlya podgotovki i vydachi iskhodnykh dannykh na razrabotku uzlov marshevykh dvigatelnykh ustanovok na tverdom toplive. Raschet ID metodom avtomatizirovannogo proektirovaniya operativno-takticheskikh raket: inzhenern. zapiska 553-376 IZ. GP «KB «Yuzhnoye». Dnepropetrovsk, 2017. 30 s.
8. Metodika avtomatizirovannogo proektirovaniya operativno-takticheskikh raket: nauch.-tekhn. Otchet 03-453/32 NTO. GP «KB «Yuzhnoye». Dnepropetrovsk, 2010. 127 s.

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