Search Results for “flight safety” – Collected book of scientific-technical articles https://journal.yuzhnoye.com Space technology. Missile armaments Fri, 17 May 2024 11:47:27 +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 “flight safety” – Collected book of scientific-technical articles https://journal.yuzhnoye.com 32 32 2.2.2019 Mathematical models for assessment of safety in the impact area of cluster ammunition of the warhead during missile complex testing https://journal.yuzhnoye.com/content_2019_2-en/annot_2_2_2019-en/ Sat, 16 Sep 2023 21:22:50 +0000 https://journal.yuzhnoye.com/?page_id=27204
In the process of flight tests of tactical and shortrange missiles with cassette warheads, the safety issues are topical. Key words: flight safety , flight tests , cassette warheards Bibliography: 1. flight safety , flight tests , cassette warheards .
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2. Mathematical models for assessment of safety in the impact area of cluster ammunition of the warhead during missile complex testing

Authors:

Hladkyi Ye. H.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019 (2); 11-17

DOI: https://doi.org/10.33136/stma2019.02.011

Language: Russian

Annotation: One of the main types of arming of modern tactical and short-range missiles are cassette warheads based on nonguided blast-fragmentation submunitions that are widely used to kill group targets. The fullscale testing (flight tests) is an integral part of their creation. In the process of flight tests of tactical and shortrange missiles with cassette warheads, the safety issues are topical. Based on the capabilities of existing test ranges, it is planned to conduct such tests for the tactical and short-range missiles, being under development in Ukraine, in the Black sea water area where the cassette warheads with nonguided blastfragmentation submunitions (or their equivalents) will pose major hazard for ships. In the paper, two mathematical models are proposed to assess probability of killing (risk) a ship that may be present in the impact area of submunitions (submunitions equivalents) of cassette warhead. The first model was constructed in the assumption that the coverage area of cassette warhead and group dispersion of submunitions are known. Such model may be used to determine safety in the initial phases of cassette warheads development. The second model assumes that the configuration of cassette warhead and the scheme of submunitions firing were finalized, and accordingly, the nominal impact points of submunitions and their group and ind ividual dispersion are considered to be known. Practical application of both models requires the use of numerical procedures.

Key words: flight safety, flight tests, cassette warheards

Bibliography:
1. Balaganskiy I. A., Merzhievskiy L. A. Deistvie sredstv porazheniya i boepripasov: ucheb. Novosibirsk, 2004. 408 s.
2 Gradstein I. S., Ryzhik I. M. Tablitsy integralov, summ, ryadov i proizvedeniy. M., 1963. 1100 s.

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2.2.2019 Mathematical models for assessment of safety in the impact area of cluster ammunition of the warhead during missile complex testing
2.2.2019 Mathematical models for assessment of safety in the impact area of cluster ammunition of the warhead during missile complex testing
2.2.2019 Mathematical models for assessment of safety in the impact area of cluster ammunition of the warhead during missile complex testing

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]]> 7.1.2020 Studying the motion of a launch vehicle and observed space debris objects during launch preparation https://journal.yuzhnoye.com/content_2020_1-en/annot_7_1_2020-en/ Wed, 13 Sep 2023 06:27:07 +0000 https://journal.yuzhnoye.com/?page_id=31031
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. method of launch time planning , safety of flight through space debris cluster .
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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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]]> 16.1.2017 Principal Directions for Creation of Integrated Launch Vehicle Autonomous Onboard Flight Safety System https://journal.yuzhnoye.com/content_2017_1/annot_16_1_2017-en/ Wed, 28 Jun 2023 12:02:33 +0000 https://journal.yuzhnoye.com/?page_id=29514
Principal Directions for Creation of Integrated Launch Vehicle Autonomous Onboard Flight Safety System Authors: Deno О. 2017 (1); 100-106 Language: Russian Annotation: The basic principles of building the flight safety systems for the space launch vehicles operated at present, the structure of autonomous onboard flight safety system that meets the requirements of the international regulatory documents in the field of space launch vehicle flight safety assurance, the feasibility of building the space launch vehicle autonomous onboard flight safety system developed in Ukraine are considered and the main directions of system’s components creation are defined. Ideology of Constructing Autonomous Flight Safety System: Technical Report / Yuzhnoye SDO. An Autonomous Flight Safety System. (2017) "Principal Directions for Creation of Integrated Launch Vehicle Autonomous Onboard Flight Safety System" Космическая техника.
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16. Principal Directions for Creation of Integrated Launch Vehicle Autonomous Onboard Flight Safety System

Authors:

Deno О. N., Filonenko А. V., Didenko O. V., Tkalenko G. V.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2017 (1); 100-106

Language: Russian

Annotation: The basic principles of building the flight safety systems for the space launch vehicles operated at present, the structure of autonomous onboard flight safety system that meets the requirements of the international regulatory documents in the field of space launch vehicle flight safety assurance, the feasibility of building the space launch vehicle autonomous onboard flight safety system developed in Ukraine are considered and the main directions of system’s components creation are defined.

Key words:

Bibliography:
1. Convention on International Responsibility for Damage Caused by Space Objects. Adopted by Resolution 2777 (XXVI) of the UN General Assembly of 29.11.1971.
2. Ideology of Constructing Autonomous Flight Safety System: Technical Report / Yuzhnoye SDO. Dnipropetrovsk, 2015. 91 p.
3. Safety Requirements of Western and Eastern Ranges: Maintenance Work Request 127-1. Т. 1. 1997. P. 1-24.
3. Bull James B., Lanzi Raymond J. An Autonomous Flight Safety System. 2016. URL: https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20080044860.pdf.

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16.1.2017 Principal Directions for Creation of Integrated Launch Vehicle Autonomous Onboard Flight Safety System
16.1.2017 Principal Directions for Creation of Integrated Launch Vehicle Autonomous Onboard Flight Safety System
16.1.2017 Principal Directions for Creation of Integrated Launch Vehicle Autonomous Onboard Flight Safety System
]]> 2.1.2023 How Yuzhnoye develops models for flight safety index evaluation for the case of a rocket failure during the flight https://journal.yuzhnoye.com/content_2023_1-en/annot_2_1_2023-en/ Fri, 12 May 2023 16:10:21 +0000 https://test8.yuzhnoye.com/?page_id=26986
It is shown that the flight safety assurance of the launch vehicle is based on the experience of combat missile systems. Flight safety during the launch vehicle launches is provided by laying flight paths through sparsely populated (unpopulated) territories and using special onboard flight safety systems. Recently flight safety process is organized based on the acceptable risk concept. Formation of the risk-oriented approach to flight safety in Yuzhnoye SDO is shown. Key moment in this process is to develop the separate structural unit, which started working on rocket and space complexes flight safety assurance and analysis. The basic model for assessing the risks of damage to facilities and people is analyzed, using the maximum impact zone of an emergency launch vehicle, which is realized in case of loss of control and flight safety system activation. launch vehicle , acceptable risk , launch vehicle failure in the flight phase , flight safety system , emergency launch vehicle impact zone , risk of damage to facilities , collection risk .
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2. How Yuzhnoye develops models for flight safety index evaluation for the case of a rocket failure during the flight

Authors:

Hladkyi Ye. H., Perlyk V. I.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2023 (1); 14-30

DOI: https://doi.org/10.33136/stma2023.01.014

Language: Ukrainian

Annotation: Safety of the up-to-date rocket and space complexes remains a topical problem for the developers of rocket and space technology. The integral component of this problem along with the safety of operations during launch vehicle ground pre-launch processing is organization of flight safety. The basic task of this rocket and space complexes safety component is to prevent or minimize serious consequences in case of launch vehicle failure in the flight leg, after all such accidents can cause damage to the population and facilities (including personnel and facilities of the ground complex), located along the flight paths. It is shown that the flight safety assurance of the launch vehicle is based on the experience of combat missile systems. Flight safety during the launch vehicle launches is provided by laying flight paths through sparsely populated (unpopulated) territories and using special onboard flight safety systems. This system limits the size of impact zones of emergency launch vehicle and its debris by emergency engine shutdown. Recently flight safety process is organized based on the acceptable risk concept. It is based on a risk assessment for the ground-based facilities and people, and it should not exceed the established standards. Such approach requires development and upgrading of the mathematical models of risk assessment in case of launch vehicle failure in the flight phase. Formation of the risk-oriented approach to flight safety in Yuzhnoye SDO is shown. Key moment in this process is to develop the separate structural unit, which started working on rocket and space complexes flight safety assurance and analysis. The basic model for assessing the risks of damage to facilities and people is analyzed, using the maximum impact zone of an emergency launch vehicle, which is realized in case of loss of control and flight safety system activation. The main directions of the basic model improvement are shown, which led to the development of a number of new original models of flight safety assessment in the Yuzhnoye SDO. First of all, the developed models take into account the flight safety system specifics, which are used to equip the launch vehicles, developed by Yuzhnoye SDO: criteria of activation, blocking of the engine emergency shutdown in the initial flight phase and Fe functional. Such models allow to take into account the different nature of emergency situations in the launch vehicle flight phase and ways of their representation, representation of the damage areas of facilities in the form of convex polygons, possible fragmentation of the emergency launch vehicle at the free- fall leg etc. The developed models have found wide application in the practice of assessing flight safety indicators in the Yuzhnoye SDO projects.

Key words: launch vehicle, acceptable risk, launch vehicle failure in the flight phase, flight safety system, emergency launch vehicle impact zone, risk of damage to facilities, collection risk

Bibliography:

1. Gladkiy E.G. Opredelenie kollektivnogo riska v cluchae avarii rakety-nositelya «Tsiklon-4M» na etape poleta s ispolzovaniem predstavlenniya naselennyh territoriy v vide mnogougolnikov. Kosmichna nauka i tehnologia. K., 2020. T. 26. № 3. S. 32–41. https://doi.org/10.15407/knit2020.03.032
2. Gladkiy E.G. Opredelenie riska dlya obiektov startovogo kompleksa s uchetom ih obvalovki v cluchae avarii rakety-nositelya na nachalnom uchastke poleta. Tehnicheskaya mehanika. Dnepropetrovsk: ITM NAN i GKA Ukrainy, 2020. №1. S. 31–41.
3. Gladkiy E.G. Otsenka riska porazheniya lineynogo obiekta v cluchae avarii rakety-nositelya na etape poleta. Kosmichna nauka i tehnologia. Kiev: GAO, 2019. T. 25. № 4. S. 22–28.
4. Gladkiy E.G. Protsedura otsenki poletnoy bezopasnosti raket-nositeley, ispolzuyuschaya geometricheskoe predstavlenie zony porazheniya obiekta v vide mnogougolnika. Kosmicheskaya tehnika. Raketnoe vooruzhenie: Sb. nauch. tr. Dnepropetrovsk: GPKBU, 2015. Vyp. 3. S. 50–56.
5. Gladkiy E.G., Kryukov A.V. Opredelenie veroyatnosti padenia avariynoy rakety-nositelya na ploschadnye obiekty, raspolozhennye bdol trassy vyvedennia. Kosmicheskaya tehnika. Raketnoe vooruzhenie: Sb. nauch. tr. Dnepropetrovsk: GPKBU, 2008. Vyp. 1. S. 81−90.
6. Gladkiy E.G., Perlik V.I. Vybor interval vremeni blokirovki avriynogo vykluchenniya dvigatelya na nachalnom uchastke poleta pervoy stupeni. Kosmicheskaya tehnika. Raketnoe vooruzhenie: Sb. nauch. tr. Dnepropetrovsk: GPKBU, 2011. Vyp. 2. S. 266–280.
7. Gladkiy E.G., Perlik V.I. Matematicheskie modeli otsenki riska dlya nazemnyh obiektov pri puskah raket-nositeley. Kosmicheskaya tehnika. Raketnoe vooruzhenie: Sb. nauch. tr. Dnepropetrovsk: GPKBU, 2010. Vyp. 2. S. 3–19.
8. Gladkiy E.G., Perlik V.I. Model otsenki urovnya bezopasnosti raketno-kosmicheskyh system. Kosmicheskaya tehnika. Raketnoe vooruzhenie: Sb. nauch. tr. Dnepropetrovsk: GPKBU. 2006. Vyp. 1−2. S. 45–57.
9. Metodika opredeleniya pokazateley bezopasnosti po trassam puskov i v raionah padeniya otdelyauschihsya chastey raket-nositeley. OOO «NTTs «Ekon TsNIImash», 2006.
10. Programma «Grom-2». Operativno-takticheskiy raketniy kompleks. Poletnaya bezopasnost. GR2 YZH ANL 016 00 [Isp. Gladkiy E.G. Zheludkov A.V. i dr.]
11. Programma «Tsiklon-4M». Raketno-kosmicheskiy kompleks. Analiz poletnoy bezopasnosti RKK. C4M YZH ANL 062 00. 2018. Vyp. 1. 92 s. [Isp. Gladkiy E.G., Zheludkov A.V. i dr.].
12. Proekt TKRK Analiz priemlimosti alternativnoy tochki # 7 dlya razmescheniya KPTs ТКРК SL-YN-TD-R-009
13. Razrabotka metodicheskyh materialov po otsenke stepeni riska po trasse poleta i v rayonah padeniya otdelyauschihsya chastey pri puskah sredstv vyvedeniya. Kniga 1. Metodicheskie materialy. NTO. TSNIImash. 1990. 68 s.
14. Raketa kosmicheskogo naznacheniya «Tsiklon-4». Utochnenie characteristic zon padeniya RKN «Tsiklon-4» v cluchae avarii. Otsenka bezopasnosti vybrannyh mest rameschenniya obiktov NK KRK «Tsiklon-4». Tsiklon-4 21.16011.117 OT: Tehn. onchet. Dnepropetrovsk: GP «KB «Yuzhnoye», 2008. 110 s.
15. Raketa kosmicheskogo naznacheniya «Tsiklon-4». Opasnye zony pri avariynom poete RKN «Tsiklon-4». Tsiklon-4 21.16522.635 OT: Tehn. otchet. Dnepropetrovsk: GP «KB «Yuzhnoye», 2009. 69 s.
16. Uvyazka KA Lybid s RKK «Zenit-M»: Poyasnitelnaya zapiska Zenit-M. Lybid PZ, 2012. 363 s.
17. Hanley E., Jim Kumamato J. Nadezhnost tehnicheskyh system i otsenki riska: Pod obsch. red. V. S. Syromyatnikova. M.: Mashinostroenie, 1984. 528 s.
18. Shatrov Ya.T. Issledovanie problem vybora trass puskov i sokrascheniya zon onchuzhdeniya dlya perspektivnyh system vyvedeniya s uchetom faktorov bezopasnosti i ekonomichnosti. Kand. dis., TsNIImash, 1980, 207 s.
19. 14 CFR, Commercial space transportation, Federal aviation administration, Department of transportation Subchapter C – Licensing, part 420 – License to Operate a Launch Site, 2000
20. E. Gladky Mathematical Models of the Safety Assessment of Ground Facilities in Case of Failure of Launch Vehicle Equipped with Onboard Automatic Emergency Engine Shutdown/ Proceedings of the International Astronautical Congress, IAC. 2015. P. 9665 – 9675.

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2.1.2023 How Yuzhnoye develops models for flight safety index evaluation for the case of a rocket failure during the flight
2.1.2023 How Yuzhnoye develops models for flight safety index evaluation for the case of a rocket failure during the flight
2.1.2023 How Yuzhnoye develops models for flight safety index evaluation for the case of a rocket failure during the flight

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]]> Сollected book of scientific-technical articles https://journal.yuzhnoye.com/ Thu, 04 May 2023 07:56:30 +0000 https://enovathemes.com/samatex2/?page_id=41
spaceflight and studies of the Moon and other planets; – issues of aerodynamics, heat-mass exchange, flight theory, loading and strength of the structures; – issues of efficiency, reliability, safety and feasibility of the rocket and space systems; –
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Collected scientific and technical articles «Космічна техніка. Ракетне озброєння. Space Technology. Missile Armaments» is the specialized professional edition, where new results of the theoretical and experimental research in the rocket and space area are published.

Subject matter of the collected articles covers the issues of creation and operation of the up-to-date missile and space launch systems, spacecraft and satellite systems, as well as their component parts, in particular:
– design and development of the launch-vehicles/integrated launch vehicles, missiles, ground complexes;
– design and development of the components parts for the launch vehicles/integrated launch vehicles, missiles (solid- and liquid-propellants engines, power supply systems, control systems, separation systems, arming etc.);
– design and development of the component parts for the ground complexes (buildings, filling systems, pre-launch processing systems etc.);
– design and development of the spacecraft and their component parts;
– spaceflight and studies of the Moon and other planets;
– materials and up-to-date technologies in the rocket and space technology;
– issues of aerodynamics, heat-mass exchange, flight theory, loading and strength of the structures;
– issues of efficiency, reliability, safety and feasibility of the rocket and space systems;
– other aspects that directly relate to the creation and operation of the rocket and space systems.

The collected articles edition publishes the results of scientific research of the scientists, scholars and research and educational personnel of the scientific institutions and institutions of higher educations to get nominated for the degrees of Candidate of Engineering (Doctor of Philosophy), Doctor of Engineering Sciences and Doctor of Physical and Mathematical Sciences. The collected articles cover the following fields: 134 – Aviation and rocket & space technology; 142 – Power engineering; 151 – Automation and computer-integrated technologies.

About the collected articles

ISSN 2617-5525; e-ISSN 2617-5533

obl1

ISSN 2617-5525;
e-ISSN 2617-5533

Until 1993 the collected scientific and technical articles «Космічна техніка. Ракетне озброєння. Space Technology. Missile Armaments» was published under the title of «Calculations, design, development and testing of the ballistic missiles».

Publisher: State Enterprise «Yuzhnoye» State Design Office».

Languages of publication: Ukrainian, English.

Frequency of edition: twice a year.

State registration of the printed media in the Ukraine’s National board for the broadcasting activities: media identifier – R30-01817 of 04.12.2023.

Сollected book of scientific-technical articles
Сollected book of scientific-technical articles
Сollected book of scientific-technical articles
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