Keywords cloud
Analysis of development trends of design parameters and basic characteristics of missiles for the advanced multiple launch rocket systems Authors: Aksenenko A. 2020, (1); 13-25 DOI: https://doi.org/10.33136/stma2020.01.013 Language: Russian Annotation: The scientific and methodological propositions for the designing single-stage guided missiles with the solid rocket motors for advanced multiple launch rocket systems are defined. Key words: multiple launch rocket systems (MLRS) , ...Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Monroe; Ashburn; Ashburn; Ashburn; Houston; Ashburn; Mountain View; Tappahannock; Ashburn; Portland; Las Vegas; San Mateo; San Mateo; San Mateo; San Mateo; Ashburn; Des Moines; Boardman; Boardman; Boardman; Las Vegas; Seattle 44 Canada Toronto; Toronto; Toronto; Toronto; Toronto; Toronto; Toronto; Monreale 8 Singapore Singapore; Singapore; Singapore; Singapore; Singapore; Singapore 6 Ukraine Dnipro; Kovel'; Dnipro; Dnipro 4 Unknown ; 2 Latvia Riga; Riga 2 Netherlands Amsterdam; Amsterdam 2...
]]>2. Analysis of development trends of design parameters and basic characteristics of missiles for the advanced multiple launch rocket systems
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; The Institute of Technical Mechanics, Dnipro, Ukraine2
Page: Kosm. teh. Raket. vooruž. 2020, (1); 13-25
DOI: https://doi.org/10.33136/stma2020.01.013
Language: Russian
Annotation: The scientific and methodological propositions for the designing single-stage guided missiles with the solid rocket motors for advanced multiple launch rocket systems are defined. The guided missiles of multiple launch rocket system are intended for delivering munitions to the given spatial point with required and specified kinematic motion parameters at the end of flight. The aim of the article is an analysis of the development trends of the guided missiles with the solid rocket motors for the multiple launch rocket systems, identifying the characteristics and requirements for the flight trajectories, design parameters, control programs, overall dimensions and mass characteristics, structural layout and aerodynamic schemes of missiles. The formalization of the complex task to optimize design parameters, trajectory parameters and motion control programs for the guided missiles capable of flying along the ballistic, aeroballistic or combined trajectories is given. The complex task belongs to a problem of the optimal control theory with limitations in form of equa lity, inequality and differential constraints. To simplify the problem, an approach to program forming is proposed for motion control in the form of polynomial that brings the problem of the optimal control theory to a simpler problem of nonlinear mathematical programming. When trajectory parameters were calculated the missile was regarded as a material point of variable mass and the combined equations for center-of-mass motion of the guided missile with projections on axes of the terrestrial reference system were used. The structure of the mathematical model was given along with the calculation sequence of the criterion function that was used for determination of the optimal parameters, programs and characteristics. The mathematical model of the guided missile provides adequate accuracy for design study to determine depending on the main design parameters: overall dimensions and mass characteristics of the guided missile in general and its structural comp onents and subsystems; power, thrust and consumption characteristics of the rocket motor; aerodynamic and ballistic characteristics of the guided missile. The developed methodology was tested by determining design and trajectory parameters, overall dimensions and mass characteristics, power and ballistic characteristics of two guided missiles with wings for advanced multiple launch rocket systems produced by the People’s Republic of China, using the limited amount of information available in the product catalog.
Key words: multiple launch rocket systems (MLRS), complex problem of the optimal control theory, problem of nonlinear mathematical programming, main solid rocket motor, limitations for motion parameters and basic characteristics of the guided missiles
Bibliography:
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Rocket and space complexes feature the thermostatting system, which ensures the required humidity and temperature conditions in the integrated launch vehicles throughout all the phases of their pre-launch processing. Key words: rocket and space complex , launch vehicle , technological systems of the ground complex , thermostatting systems , open type system , versatility , modular design.
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]]>9. General-purpose thermostating module – new approach in development of up-to-date thermostating systems for rocket and space complexes
Organization:
Page: Kosm. teh. Raket. vooruž. 2024, (1); 78-84
DOI: https://doi.org/10.33136/stma2024.01.078
Language: Ukrainian
Annotation: These days when creating any rocket space complex, it is important to ensure its advancement and competitive ability. To create such complex, the technical systems it consists of must be implemented with minimal economic and energy costs. Rocket and space complexes feature the thermostatting system, which ensures the required humidity and temperature conditions in the integrated launch vehicles throughout all the phases of their pre-launch processing. Development of the competitive rocket and space complex also requires the new approach in the development of the thermostatting system. One of the main tasks is to create a system that can be mass-produced and used as part of any rocket and space complex. Solving this problem will significantly reduce the cost of creating and operating the thermostatting systems and the whole rocket and space complex. One of the ways to solve this task is to create a general-purpose thermostatting system. The modular principle for such thermostatting system would be optimal, which means making up a system from separate modules. It simplifies the all-round installation of various system options and simplifies its setup and operation. The paper demonstrates the possibility and prospects of creating modular thermostatting systems, which enable air supply with the required parameters to different consumers. Characteristics and design of the general-purpose thermostatting module are specified, which can be used as the main component without changing anything in the composition of stationary and mobile thermostatting systems.
Key words: rocket and space complex, launch vehicle, technological systems of the ground complex, thermostatting systems, open type system, versatility, modular design.
Bibliography:
- . Tsiklon-4M. URL: https://www. yuzhnoye.com.
- . KRK «Tsiklon-4M». C4M YZH SPS 090 02 Technicheskoe zadanie na sostavnuyu chast’ OKR «Sistema termostatirovaniya rakety-nositelya i golovnogo bloka» GP «KB «Yuzhnoye». 78 s.
- . KRK «Tsiklon-4M». C4M YZH SPS 119 02 Technicheskoe zadanie na sostavnuyu chast OKR «Transportnaya systema termostatirovaniya» GP «KB «Yuzhnoye». 2018. 40 s.
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| Germany | Falkenstein; Düsseldorf; Limburg an der Lahn; Falkenstein; Leipzig; Leipzig | 6 |
| China | Pekin; Shenzhen; Pekin; Hangzhou | 4 |
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Keywords cloud
Method of autonomous determination of the rocket’s reference attitude during pre-launch processing Authors: Borscheva O. Taking it into consideration, the alternative method of rocket’s reference attitude determination during the pre-launch processing is offered. (2024) "Method of autonomous determination of the rocket’s reference attitude during pre-launch processing" Космическая техника. "Method of autonomous determination of the rocket’s reference attitude during pre-launch processing" Космическая техника.
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]]>10. Method of autonomous determination of the rocket’s reference attitude during pre-launch processing
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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Keywords cloud
This may play both negative (off-design increase of chamber pressure) and positive role (for example, increasing the launch thrust-to-weight ratio of the rocket). It is typical of the main SRMs of various rocket systems (multiple launch rocket systems, anti-aircraft guided missiles, tactical missiles, boosters). Content 2024 (1) Downloads: 46 Abstract views: 750 Dynamics of article downloads Dynamics of abstract views Downloads geography Country City Downloads USA Las Vegas; Columbus; Ashburn; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Seattle; Ashburn; Houston; Ashburn; Council Bluffs; Mountain View; Mountain View; Portland; San Mateo; Ashburn; Ashburn; Ashburn 24 Germany Falkenstein; Düsseldorf; Limburg an der Lahn;; Falkenstein; Leipzig; Leipzig 7 Canada Toronto; Toronto; Toronto; Toronto; Toronto 5 China...
]]>8. Theoretic-experimental evaluation of the solid-propellant grain erosive burning
Organization: Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2024, (1); 72-77
DOI: https://doi.org/10.33136/stma2024.01.072
Language: Ukrainian
Annotation: The high demands for the flow rate and thrust characteristics specified for the modern solid-propellant rocket motors (SRM) under the strict mass and overall dimensions constraints require high level of mass fraction of propellant. And in the process of propellant grain combustion, erosive burning often takes place (increase of propellant burning rate depending on combustion products flow rate along the grain channel). This may play both negative (off-design increase of chamber pressure) and positive role (for example, increasing the launch thrust-to-weight ratio of the rocket). It is typical of the main SRMs of various rocket systems (multiple launch rocket systems, anti-aircraft guided missiles, tactical missiles, boosters). This paper proposes a methodology for calculating the internal ballistic characteristics of a solid propellant rocket motor under erosive burning, which is relatively time and resource consuming. The methodology is based on equidistant model of propellant grain combustion, where grain is divided lengthwise into a number of intervals. For any point of time during the engine operation, burning area and port area of each interval are calculated, taking into account erosive impact on each interval; total burning area is the sum of all intervals burning areas. Gas flow rate in each interval of the grain channel is calculated using gas-dynamic equations. The motor mass flow rate is a mass input sum of all the intervals; and the burning rate in each interval is estimated with proper erosion factor. The combustion chamber pressure had been calculated for four erosive burning models proposed by different authors. All the models showed convergence with the experimental SRM test data sufficient for engineering estimate (in particular, for maximum chamber pressure and combustion time). Selected as a result erosive burning model may be used to design new motors with solid propellants similar in chemical composition, and the model parameters are to be further customized using the test specimens.
Key words: rocket motor, solid propellant, erosive burning, internal ballistic characteristics
Bibliography:
- Arkhipov V. Erosionnoe gorenie condensirovannykh system. Sb. tr. ІХ Vserossiyskoy nauch. conf. 2016 g. (FPPSM-2016). Tomsk, 2016.
- Mukunda S., Paul P. J. Universal behaviour in erosive burning of solid propellants. Combustion and flame, 1997. https://doi.org/10.1016/S0010-2180(96)00150-2
- Sabdenov K. , Erzda M., Zarko V. Ye. Priroda i raschet skorosti erozionnogo goreniya tverdogo raketnogo topliva. Inzhenerniy journal: nauka i innovatsii, 2013. Vyp. 4.
- Evlanova A., Evlanov A. A., Nikolaeva Ye. V. Identifikatsiya parametrov erozionnogo goreniya topliva po dannym ognevykh stendovykh ispytaniy. Izvestiya TulGU. Tekhn. nauki. 2014. Vyp. 12, ch. 1.
- Yanjie Ma, Futing Bao, Lin Sun, Yang Liu, and Weihua Hui. A New Erosive Burning Model of Solid Propellant Based on Heat Transfer Equilibrium at Propellant Surface. Hindawi International Journal of Aerospace Engineering, Vol. 2020, Article ID 8889333. https://doi.org/10.1155/2020/8889333
- Williams, Forman A., Combustion Theory. The Benjamin/Cummings Publishing , Menlo Park, 1985.
- Irov Yu. D., Keil E. V., Maslov B.N., Pavlukhin Yu. A., Porodenko V. V.,
Stepanov Ye. A. Gasodynamicheskie funktsii. Mashinostroenie, Moskva, 1965. - William Orvis. EXCEL dlya uchenykh, inzhenerov i studentov. Kiev: «Junior», 1999.
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| Germany | Falkenstein; Düsseldorf; Limburg an der Lahn;; Falkenstein; Leipzig; Leipzig | 7 |
| Canada | Toronto; Toronto; Toronto; Toronto; Toronto | 5 |
| China | Pekin; Pekin; Shenzhen; Pekin | 4 |
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| Singapore | Singapore | 1 |
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Keywords cloud
Experimental studies of the performance of pyrotechnic devices installed on the launch vehicle separation systems Автори: Boliubash Ye. 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. The research methodology, experimental scenario, in particular, a description of the research object and a scheme for measuring test results are presented.
]]>14. Experimental studies of the performance of pyrotechnic devices installed on the launch vehicle separation systems
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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Keywords cloud
Among the most significant are the following areas: training of the executive personnel and its reserve; training in the postgraduate courses of the enterprise; learning computer technologies; preparation of the pre-launch processing personnel and its reserve; activities with intellectual property; involvement of the leading institutes of higher education both for training of young specialists and to obtain particular scientific results etc. ...Angeles; Chicago; Chicago; Buffalo; Buffalo; Ashburn; New Haven; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Los Angeles; Los Angeles; Los Angeles; San Francisco; Ashburn; Buffalo; Seattle; Mountain View; Mountain View; Mountain View; Ashburn; Portland; San Mateo; Seattle 33 Germany Falkenstein; Düsseldorf; Falkenstein; Leipzig; Leipzig 5 China Pekin; Shenzhen; Pekin; Hangzhou 4 Canada Toronto; Toronto; Toronto; Toronto 4 Unknown ; 2 Ukraine Kremenchuk; Novomoskovsk 2 Singapore Singapore 1 France 1 Netherlands Amsterdam 1 Kuwait Kuwait...
]]>16. Educational tendencies as an element of innovative progress in the personnel training system for the state-of-the-art enterprises
Organization: Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2024, (1); 136-140.
DOI: https://doi.org/10.33136/stma2024.01.136
Language: Ukrainian
Annotation: Yuzhnoye SDO is one of the most state-of-the-art and hi-tech enterprises of the Ukraine’s space and rocket branch. To maintain its scientific and productive potential, among other things, the enterprise needs to have professional specialists, who are development-orientated and eager to enhance their professional skills. To solve this problem there is personnel training system at the enterprise. Responsibility to provide the Yuzhnoye SDO with the skilled specialists is shared, within their authority, between the staff department and the scientific-educational center of the enterprise, which directly report to the General Director. The goal-oriented educational areas, realized at the enterprise, occupy the special role in these activities. The goal-oriented educational areas represent a complex of actions of several divisions at the enterprise, supervised by the scientific-educational center, which aim to provide the corresponding professional level of the employees busy with fulfilment of current job assignments. Among the most significant are the following areas: training of the executive personnel and its reserve; training in the postgraduate courses of the enterprise; learning computer technologies; preparation of the pre-launch processing personnel and its reserve; activities with intellectual property; involvement of the leading institutes of higher education both for training of young specialists and to obtain particular scientific results etc. All these areas have already been proven and some of them run on continuing basis. Thus it can be concluded that the personnel training system is effective. It proves itself and can serve as an example of introduction at any manufacturing enterprise. Besides, orientation of training process at the individual goal-oriented educational areas involves and unites efforts of several interested enterprise divisions to reach particular and necessary results within certain timetable.
Key words: system of specialist training, goal-oriented educational area, training at the enterprise, professional training.
Bibliography:
1. Upravlenie personalom. Uchebnik dlya vuzov. Pod red. T.Yu. Bazarova, B.L. Yeremina.
2-e izd. peredel. i dop. M., YuNITI. 2002. 560 s.
2. Zevako V. S. Pidgotovka naukovo-pedagogichnykh kadriv dlya naukoemnogo pidpriemstva. Svit naukovykh doslidzhen’. Zbirnyk tez mizhnarodnoi naukovo-praktychnoi internet-conferentsii 24-25 bereznya 2022 r. Vyp. 7. S. 90 – 91.
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Keywords cloud
cold-launched» separation) is given and their technical substance with advantages and drawbacks is described. Spaceflightinsider.com/missions/iss/ng-18-cygnus-cargo-ship-to-launch-new-science-to-iss/Antares (data zvernennya 30.10.2023). ...Dynamics of article downloads Dynamics of abstract views Downloads geography Country City Downloads USA Ashburn; San Jose; Chicago; Chicago; Washington; Buffalo; Dublin; Buffalo; Ashburn; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; San Francisco; Los Angeles; Seattle; Ashburn; Ashburn; Mountain View; Mountain View; Portland; Portland; San Mateo; Ashburn; Mountain View 28 Germany Falkenstein; Düsseldorf; Falkenstein; Leipzig; Leipzig 5 China Pekin; Pekin; Shenzhen; Pekin 4 Canada Toronto; Toronto; Toronto; Toronto 4 Ukraine Berdyans...
]]>7. Selection of the functional units for the Cyclone-4M ILV separation system
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2024, (1); 61-71
DOI: https://doi.org/10.33136/stma2024.01.061
Language: Ukrainian
Annotation: Separation of the spent LV stages is one of the important problems of the rocket technology, which
requires the comprehensive analysis of different types of systems, evaluation of their parameters and
structural layouts. Basic requirements are specified that need to be taken into account when engineering
the separation system: reliable and safe separation, minimal losses in payload capability, keeping sufficient
distance between the stages at the moment of the propulsion system start. Detailed classification of their
types («cold», «warm», «hot», «cold-launched» separation) is given and their technical substance with
advantages and drawbacks is described. Certain types of «cold» and «warm» separation of the spent stages
of such rockets as Dnepr, Zenit, Antares, Falcon-9 with different operating principle are introduced – braking
with the spent stage and pushing apart two stages. Brief characteristics of these systems are given, based
on the gas-reactive nozzle thrust, braking with solid-propellant rocket engines, separating with spring or
pneumatic pushers. Development of the separation system for the advanced Cyclone-4M ILV is taken as an
example and design sequence of stage separation is suggested: determination of the necessary separation
velocity and capability of the separation units, determination of the number of active units, calculation of
design and energy parameters of the separation units, analysis of the obtained results followed by the
selection of the separation system. Use of empirical dependences is shown, based on the great scope of
experimental and theoretical activities in the process of design, functional testing and flight operation of
similar systems in such rockets as Cyclone, Dnepr and Zenit. According to the comparative analysis results,
pneumatic separation system to separate Cyclone-4M Stages 1 and 2 was selected as the most effective
one. Its basic characteristics, composition, overall view and configuration are specified. Stated materials
are of methodological nature and can be used to engineer the separation systems for LV stages, payload
fairings, spacecraft etc.
Key words: separation system, functional units of separation, «cold separation», «warm separation», pneumatic pusher, spring pusher, SPRE, gas-reactive nozzles, Zenit LV, Dnepr LV, Falcon 9 rocket, Cyclone-4М LV.
Bibliography:
- Pankratov Yu. , Novikov A. V., Tatarevsky K. E., Azanov I. B. Dynamika perekhodnykh processov. 2014.
- Sinyukov A. M., Morozov N. I. Konstruktsia upravlyaemykh ballisticheskykh raket. 1969.
- Kabakova Zh. V., Kuda S. A., Logvinenko A. I., Khomyak V. A. Opyt razrabotki pneumosystemy dlya otdelenita golovnogo aerodynamicheskogo obtekatelya. Kosmicheskaya technika. Raketnoe vooruzhenie. 2017. Vyp. 2 (114).
- Kolesnikov K. S., Kozlov V. V., Kokushkin V. V. Dynamika razdeleniya stupeney letatelnykh apparatov. 1977.
- Antares – Spaceflight Insider: web site. URL: https://www. Spaceflightinsider.com/missions/iss/ng-18-cygnus-cargo-ship-to-launch-new-science-to-iss/Antares (data zvernennya 30.10.2023).
- Falcon 9 – pexels: website. URL: https://www. pexels.com/Falcon 9 (data zvernennya 31.10.2023).
- Kolesnikov K. , Kokushkin V. V., Borzykh S. V., Pankova N. V. Raschet i proektirovanie system razdeleniya stupeney raket. 2006.
- Cyclone-4M – website URL: https://www.yuzhnote.com (data zvernennya 31.10.2023)
- Logvinenko A. Sozdanie gasoreaktivnykh system otdeleniya i uvoda otrabotavshykh stupeney – noviy shag v RKT. Kosmicheskaya tekhnika. Raketnoe vooruzhenie, KBU, NKAU, vyp. 1, 2001.
- Logvinenko A. I., Porubaimekh V. I., Duplischeva O. M. Sovremennye metody ispytaniy system i elementov konstruktsiy letatelnykh apparatov. Monografia. Dnepr, KBU, 2018.
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Keywords cloud
Assessment of risk of toxic damage to people in case of a launch vehicle accident at flight Authors: Hladkyi E. 2024, (1); 40-50 DOI: https://doi.org/10.33136/stma2024.01.040 Language: English Annotation: Despite stringent environmental requirements, modern launch vehicles/integrated launch vehicles (LV/ILV) burn toxic propellants such as NTO and UDMH. A zone dangerous for people was constructed using the proposed model for the case of the failure of the Dnepr launch vehicle, where the risks of toxic damage exceed the permissible level (10–6).
Not found: sea
]]>5. Assessment of risk of toxic damage to people in case of a launch vehicle accident at flight
Organization:
Page: Kosm. teh. Raket. vooruž. 2024, (1); 40-50
DOI: https://doi.org/10.33136/stma2024.01.040
Language: English
Annotation: Despite stringent environmental requirements, modern launch vehicles/integrated launch vehicles (LV/ILV)
burn toxic propellants such as NTO and UDMH. Typically, such propellants are used in the LV/ILV upper
stages, where a small amount of propellant is contained; however, some LV/ILV still use such fuel in all
sustainer propulsion stages. For launch vehicles containing toxic rocket propellants, flight accidents may result
in the failed launch vehicle falling to the Earth’s surface, forming large zones of chemical damage to people
(the zones may exceed blast and fire zones). This is typical for accidents occurring in the first stage flight
segment, when an intact launch vehicle or its components (usually individual stages) with rocket propellants
will reach the Earth’s surface. An explosion and fire following such an impact will most likely lead to a massive
release of toxicant and contamination of the surface air. An accident during the flight segment of the LV/ILV
first stage with toxic rocket propellants, equipped with a flight termination system that implements emergency
engine shutdown in case of detection of an emergency situation, has been considered. To assess the risk
of toxic damage to a person located at a certain point, it is necessary to mathematically describe the zone
within which a potential impact of the failed LV/ILV will entail toxic damage to the person (the so-called zone
of dangerous impact of the failed LV/ILV). The complexity of this lies in the need to take into account the
characteristics of the atmosphere, primarily the wind. Using the zone of toxic damage to people during the fall
of the failed launch vehicle, which is proposed to be represented by a combination of two figures: a semicircle
and a half-ellipse, the corresponding zone of dangerous impact of the failed LV/ILV is constructed. Taking into
account the difficulties of writing the analytical expressions for these figures during the transition to the launch
coordinate system and further integration when identifying the risk, in practical calculations we propose to
approximate the zone of dangerous impact of the failed LV/ILV using a polygon. This allows using a known
procedure to identify risks. A generalization of the developed model for identifying the risk of toxic damage
to people involves taking into account various types of critical failures that can lead to the fall of the failed
LV/ILV, and blocking emergency engine shutdown during the initial flight phase. A zone dangerous for people
was constructed using the proposed model for the case of the failure of the Dnepr launch vehicle, where the
risks of toxic damage exceed the permissible level (10–6). The resulting danger zone significantly exceeds the
danger zone caused by the damaging effect of the blast wave. Directions for further improvement of the model
are shown, related to taking into account the real distribution of the toxicant in the atmosphere and a person’s
exposure to a certain toxic dose.
Key words: launch vehicle, critical failure, flight accident, zone of toxic damage to people, zone of dangerous impact of the failed launch vehicle, risk of toxic damage to people.
Bibliography:
- Hladkiy E. H. Protsedura otsenky poletnoy bezopasnosti raket-nositeley, ispolzuyuschaya geometricheskoe predstavlenie zony porazheniya obiekta v vide mnogougolnika. Kosmicheskaya technika. Raketnoe vooruzhenie: sb. nauch.-techn. st. Dnepropetrovsk: GP «KB «Yuzhnoye», 2015. Vyp. 3. S. 50 – 56. [Hladkyi E. Procedure for evaluation of flight safety of launch vehicles, which uses geometric representation of object lesion zone in the form of a polygon. Space Technology. Missile Weapons: Digest of Scientific Technical Papers. Dnipro: Yuzhnoye SDO, 2015. Issue 3. Р. 50 – 56. (in Russian)].
- Hladkiy E. H., Perlik V. I. Vybor interval vremeni blokirovki avariynogo vyklucheniya dvigatelya na nachalnom uchastke poleta pervoy stupeni. Kosmicheskaya technika. Raketnoe vooruzhenie: sb. nauch.-tech. st. Dnepropetrovsk: GP «KB «Yuzhnoye», 2011. Vyp. 2. s. 266 – 280. [Hladkyi E., Perlik V. Selection of time interval for blocking of emergency engine cut off in the initial flight leg of first stage. Space Technology. Missile Weapons: Digest of Scientific Technical Papers. Dnipro: Yuzhnoye SDO, 2011. Issue 2. Р. 266 – 280. (in Russian)].
- Hladkiy E. H., Perlik V. I. Matematicheskie modeli otsenki riska dlya nazemnykh obiektov pri puskakh raket-nositeley. Kosmicheskaya technika. Raketnoe vooruzhenie: sb. nauch.-techn. st. Dnepropetrovsk: GP «KB «Yuzhnoye», 2010. Vyp. 2. S. 3 – 19. [Hladkyi E., Perlik V. Mathematic models for evaluation of risk for ground objects during launches of launch-vehicles. Space Technology. Missile Weapons: Digest of Scientific Technical Papers. Dnipro: Yuzhnoye SDO, 2010. Issue 2. P. 3 – 19. (in Russian)].
- NPAOP 0.00-1.66-13. Pravila bezpeki pid chas povodzhennya z vybukhovymy materialamy promyslovogo pryznachennya. Nabrav chynnosti 13.08.2013. 184 s [Safety rules for handling explosive substances for industrial purposes. Consummated 13.08.2013. 184 p.
(in Ukranian)]. - AFSCPMAN 91-710 RangeSafetyUserRequirements. Vol. 1. 2016 [Internet resource]. Link : http://static.e-publishing.af.mil/production/1/afspc/publicating/
afspcman91-710v1/afspcman91-710. V. 1. pdf. - 14 CFR. Chapter III. Commercial space transportation, Federal aviation administration, Department of transportation, Subchapter C – Licensing, part 417 – Launch Safety, 2023 [Internet resource]. Link: http://law.cornell.edu/cfr/text/14/part-417.
- 14 CFR. Chapter III. Commercial space transportation, Federal aviation administration, Department of transportation, Subchapter C – Licensing, part 420 License to Operate a Launch Site. 2022 [Internet resource]. Link: http://law.cornell.edu/cfr/text/14/part-420.
- ISO 14620-1:2018 Space systems – Safety requirements. Part 1: System safety.
- 9 GOST 12.1.005-88. Systema standartov bezopasnosti truda. Obschie sanitarno-gigienicheskie trebovaniya k vozdukhu rabochei zony. [GOST 12.1.005-88. Labor safety standards system. General sanitary and hygienic requirements to air of working zone].
- 10 Rukovodyaschiy material po likvidatsii avarijnykh bolshykh prolivov okislitelya АТ (АК) i goruchego NDMG. L.:GIPKh, 1981, 172 s. [Guidelines on elimination of large spillages of oxidizer NTO and fuel UDMH. L.:GIPH, 1981, 172 p. (in Russian)].
- 11 Kolichestvennaya otsenka riska chimicheskykh avariy. Kolodkin V. M., Murin A. V., Petrov A. K., Gorskiy V. G. Pod red. Kolodkina V. M. Izhevsk: Izdatelskiy dom «Udmurtskiy universitet», 2001. 228 s. [Quantitative risk assessment of accident at chemical plant. Kolodkin V., Murin A., Petrov A., Gorskiy V. Edited by Kolodkin V. Izhevsk: Udmurtsk’s University. Publish house, 2001. 228 p. (in Russian)].
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| Germany | Falkenstein; Düsseldorf; Falkenstein; Leipzig; Leipzig | 5 |
| Canada | Toronto; Toronto; Toronto; Toronto; Toronto | 5 |
| China | Pekin; Shenzhen; Pekin; Hangzhou | 4 |
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Keywords cloud
2024, (1); 9-18 DOI: https://doi.org/10.33136/stma2024.01.009 Language: Ukrainian Annotation: Specialized design office for liquid engines was established on July 22, 1958 to develop engines and propulsion systems, powered by liquid propellants to be installed on the combat missile systems and integrated launch vehicles (LV), developed by Yuzhnoye SDO. Seventeen of them were commercially produced by Yuzhmash PA and installed on launch vehicles.
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]]>2. New and advanced liquid rocket engines of the Yuzhnoye SDO
Organization:
Page: Kosm. teh. Raket. vooruž. 2024, (1); 9-18
DOI: https://doi.org/10.33136/stma2024.01.009
Language: Ukrainian
Annotation: Specialized design office for liquid engines was established on July 22, 1958 to develop engines and propulsion systems, powered by liquid propellants to be installed on the combat missile systems and integrated launch vehicles (LV), developed by Yuzhnoye SDO. Moreover, liquid engines design office was assigned with manufacturing and testing of the main rocket engines, developed by NPO Energomash and to be installed on Yuzhnoye-developed launch vehicles. Over the past 66 years Yuzhnoye SDO has developed more than 40 liquid rocket engines (LRE) of various purpose, designed both to gas-generator cycle and to staged combustion cycle. Seventeen of them were commercially produced by Yuzhmash PA and installed on launch vehicles. Nowadays Yuzhnoye propulsion experts keep working on development of the advanced liquid rocket engines powered both by cryogenic and hypergolic propellants, which satisfy the majority of launch service market demands. Within the framework of extensive cooperation with foreign space companies, on a contract basis, Yuzhnoye propulsion experts are working on the design and development testing of the liquid rocket engines, as well as their components. The accumulated vast experience in the development of liquid rocket engines nowadays enables high scientific and technical level in the creation of up-to-date engines, demanded in the world market. Significant steps in this area have been made by the experts from the Yuzhnoye propulsion division and then subsequent manufacture and delivery by Yuzhmash PA of the engine intended for the European rocket Vega Stage 4; and designing the individual components for the engines with thrusts ranging from 500 kgf to 200 tf ordered by foreign customers. This article provides the review of current and scheduled activities of the Yuzhnoye SDO to develop the liquid rocket engines within the thrust ranges from ~ 40 kgf to ~ 500 tf.
Key words: LOX-kerosene liquid rocket engines, hypergolic propellant liquid rocket engines, staged combustion cycle, main rocket engine, thrust, specific thrust impulse.
Bibliography:
- Zhidkostnye raketnye dvigateli, dvigatelnye ustanovki, bortovye istochniki moschnosti, razrabotannye KB dvigatelnykh ustanovok GP«KB «Yuzhnoye». Za nauk. red. akad. NAN Ukrainy S.M. Konyukhova, kand. tekhn. nauk V.M. Shnyakina. Dnipropetrovsk: DP «KB «Pivdenne», 2008. 466 ark.
- Prokopchyuk O. O., Shulga V. A., Khromyuk D. S., Sintyuk V. O. Zhidkostnye raketnye dvigateli GP«KB «Yuzhnoye»: nauk.-tekhn. zbirnyk. Za nauk. red. akademika NAN Ukrainy
O. V. Degtyareva. Dnipro: ART-PRES, 2019. 440 ark.
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| Germany | Falkenstein; Düsseldorf; Falkenstein; Leipzig; Leipzig | 5 |
| Canada | Toronto; Toronto; Toronto; Toronto; Toronto | 5 |
| China | Pekin; Pekin; Shenzhen; Pekin | 4 |
| Ukraine | Kyiv; Kremenchuk; Kremenchuk | 3 |
| Singapore | Singapore | 1 |
| France | 1 | |
| Hungary | Budapest | 1 |
| Netherlands | Amsterdam | 1 |
Keywords cloud
2017 (2); 57-59 Language: Russian Annotation: The remote control method of launch vehicle hydrosystem detachable joints airtightness by mass spectrometer at the Launch Complex in conditions of limited access to hydrosystem elements is under consideration. The additional design development of hydrosystems prior to article roll-out to the launch side is provided for control. ...Dublin; Columbus; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Monroe; Ashburn; Ashburn; Seattle; Seattle; Ashburn; Quinton; Ashburn; Ashburn; Ashburn; Seattle; Tappahannock; Portland; San Mateo; San Mateo; San Mateo; Des Moines; Boardman; Boardman; Ashburn; Seattle 34 Singapore Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore 10 Canada Toronto; Toronto; Toronto; Monreale 4 Germany Frankfurt am Main; Frankfurt am Main; Falkenstein 3 Unknown Brisbane; 2 Ukraine Dnipro; Dnipro...
]]>11. Remote Monitoring Method of Pneudraulic System Structural Elements Integrity
Organization:
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine
Page: Kosm. teh. Raket. vooruž. 2017 (2); 57-59
Language: Russian
Annotation: The remote control method of launch vehicle hydrosystem detachable joints airtightness by mass spectrometer at the Launch Complex in conditions of limited access to hydrosystem elements is under consideration. The additional design development of hydrosystems prior to article roll-out to the launch side is provided for control.
Key words:
Bibliography:
1. Volkov V. P., Kulik A. V. et al. Technological Processes of Strength and Leak Tests in Space Rocketry Production / Under the editorship of L. D. Kuchma. Dnepropetrovsk, 2014. 264 p.
2. Sanin F. P. et al. Leak-Tightness in Space Rocketry: Tutorial / F. P. Sanin, E. O. Dzhur, L. D. Kuchma, V. A. Naidyonov. Dnipropetrovsk, 1995. 168 p.
3. Babkin V. T., Zaichenko A. A. et al. Leak-Tightness of Hydraulic Systems Fixed Connections. М., 1977. 120 p.
4. OST 92-1527-89. Leak Tests of Products Using Mass-Spectrometer Helium Leak Detectors. Test Methods. 138 p.
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Downloads geography
| Country | City | Downloads |
|---|---|---|
| USA | Boardman; Matawan; Baltimore; Plano; Dublin; Columbus; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Phoenix; Monroe; Ashburn; Ashburn; Seattle; Seattle; Ashburn; Quinton; Ashburn; Ashburn; Ashburn; Seattle; Tappahannock; Portland; San Mateo; San Mateo; San Mateo; Des Moines; Boardman; Boardman; Ashburn; Seattle | 34 |
| Singapore | Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore | 10 |
| Canada | Toronto; Toronto; Toronto; Monreale | 4 |
| Germany | Frankfurt am Main; Frankfurt am Main; Falkenstein | 3 |
| Unknown | Brisbane; | 2 |
| Ukraine | Dnipro; Dnipro | 2 |
| Netherlands | Amsterdam; Amsterdam | 2 |
| Belgium | Brussels | 1 |
| Finland | Helsinki | 1 |
| Romania | Voluntari | 1 |