Search Results for “Yangel Yuzhnoye State Design Office, Dnipro, Ukraine” – Collected book of scientific-technical articles https://journal.yuzhnoye.com Space technology. Missile armaments Fri, 26 Apr 2024 09:07:56 +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 “Yangel Yuzhnoye State Design Office, Dnipro, Ukraine” – Collected book of scientific-technical articles https://journal.yuzhnoye.com 32 32 10.2.2019 Dynamic performance of the gas drive with jet motor https://journal.yuzhnoye.com/content_2019_2-en/annot_10_2_2019-en/ Tue, 03 Oct 2023 11:52:15 +0000 https://journal.yuzhnoye.com/?page_id=32366
Organization: Yangel Yuzhnoye State Design Office, Dnipro, Ukraine Page: Kosm.
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10. Dynamic performance of the gas drive with jet motor

Authors:

Oliinyk V. P., Kaluger L. G.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (2); 71-79

DOI: https://doi.org/10.33136/stma2019.02.071

Language: Russian

Annotation: The use of servo drives on flying vehicles determines the requirements to their dynamic characteristics. The problems of dynamics of drive with jet motor are not practically covered in publications. The task arises of selection of structure and parameters of devices consisting of several subsystems whose dynamic characteristics must be brought into agreement with each other in optimal way. The purpose of this work is to develop mathematical dependences for calculation of dynamic characteristics. The functional arrangement of the drive is considered consisting of jet motor based on Segner wheel with de Laval nozzle, mechanical transmission, pneumatic distributing device – jet pipe controlled by electromechanical converter. The layout is presented of mechanical segment of servo drive with jet motor with screw-nut transmission. The dynamic model is presented and the algebraic relations to determine natural frequencies of the drive are given. The motion equations of output rod at full composition of load are given. Using Lagrange transformation as applied to ball screw transmission, the expression for reduced mass of output element was derived. The reduced mass of load depends on the jet motor design and exerts basic influence on the drive’s natural frequencies. The evaluation is given of reduced mass change from the jet motor moment of inertia and reducer transmission coefficient. Based on the proposed algorithms, the dynamic characteristics of servo drive were constructed: transient process and amplitude-frequency characteristic. The drive has relatively low pass band, which is explained by the value of reduced mass of load.

Key words: pneumatic drive, functional arrangement, hydrodynamic force, reduced mass, Lagrange transformations, ball screw transmission, transient process, frequency characteristic

Bibliography:
1. Pnevmoprivod system upravleniya letatelnykh apparatov /V. A. Chaschin, O. T. Kamladze, A. B. Kondratiev at al. M., 1987. 248 s.
2. Berezhnoy A. S. Sovershenstvovanie rabochikh characteristic struino-reaktivnogo pnevmoagregata na osnove utochneniya modeli rabochego processa: dis. cand. techn. nauk: 05.05.17. Zaschischena 03.10.14. Sumy, 2014. 157 s.
3. Oleinik V. P., Yelanskiy Yu. A., Kovalenko V. N. et al. Staticheskie characteristiki gazovogo privoda so struinym dvigatelem /Kosmicheskaya technika. Raketnoe vooruzhenie: Sb. nauch.-techn. st. 2016. Vyp. 2. S. 21-27.
4. Abramovich G. N. Prikladnaya gazovaya dynamika. M., 1976. 888 s.
5. Strutinskiy V. B. Matematichne modelyuvannya processiv ta system mechaniki. Zhitomir, 2001. 612 s.
6. Shalamov A. V., Mazein P. G. Dynamicheskaya model’ sharikovintovoi pary/ Izv. Chelyabinskogo nauchnogo centra UrO RAN. №4. Chelyabinsk, 2002. S.161-170.
7. Kripa K.Varanasi, Samir A. Nayfer. The Dynamics of Lead-Screw Drivers: Low-Order Modeling and Experiments /Journal of Dynamic System, Measurement and Control. June 2004. Vol. 126. P. 388-395. https://doi.org/10.1115/1.1771690

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10.2.2019 Dynamic performance of the gas drive with jet motor
10.2.2019 Dynamic performance of the gas drive with jet motor
10.2.2019 Dynamic performance of the gas drive with jet motor

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]]> 9.2.2019 Gas-dynamic simulation of the supersonic stream in the pulsed wind tunnel https://journal.yuzhnoye.com/content_2019_2-en/annot_9_2_2019-en/ Tue, 03 Oct 2023 11:48:27 +0000 https://journal.yuzhnoye.com/?page_id=27211
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9. Gas-dynamic simulation of the supersonic stream in the pulsed wind tunnel

Authors:

Sirenko V. M., Zhivotov O. Yu.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (2); 63-70

DOI: https://doi.org/10.33136/stma2019.02.063

Language: Russian

Annotation: A promising experimental bench – a shock wind tunnel was put into operation at Yuzhnoye SDO. The shock wind tunnel is designed to simulate the incident flow during rocket flight at high supersonic and hypersonic velocities. To solve actual design problems facing Yuzhnoye SDO, it was necessary to expand the range of velocities under investigation in a shock wind tunnel by low supersonic Mach numbers (Mа=1.5; 2; 3). As a result of this work, a modernized configuration of the shock wind tunnel was developed, which allows simulating flow parameters at low supersonic velocities. The results of aerodynamic experiment performed in the modernized shock wind tunnel, which are close to full scale ones, can be obtained using as much data on peculiarities of supersonic flow formation in it as possible. Therefore, the study of the distribution of Mach numbers profiles in the working section of the modernized shock wind tunnel at low and high supersonic velocity was chosen as the main line of research. The results of the research presented in the article are based on the use of numerical simulation methods, as well as data obtained experimentally. As a result of gasdynamic simulation of a supersonic flow conducted for the nozzle Mа=4 and the nozzle Mа=2, the calculated and experimental data on the distribution pattern and field values of Mach numbers in the working section of the tunnel were obtained. A comparative analysis was carried out. The boundaries of the region of equal velocities, within which the condition of quasistatic supersonic flow is satisfied, and the lifetime of the operating mode for the selected nozzle type were determined. At the flow from the nozzle Mа=2, a peculiarity was revealed in the distribution pattern of Mach numbers fields associated with the appearance of “blocking” effect of the supersonic flow. The methods for eliminating the effect of flow “blocking” at low supersonic velocities are proposed.

Key words: incident flow modeling, velocity fields in the wind tunnel working section, aerodynamic experiment

Bibliography:
1. Zvegintsev V. I. Gasodynamicheskie ustanovki kratkovremennogo deistviya. V dvuh chastyakh. Ch. 1. Ustanovki dlya nauchnykh issledovaniy. Novosibirsk, 2014. 551 s.
2. Computerno-vymiryuvalni tekhnologii kontrolu ta upravlinnya raketno-kosmichnoi techniki / monogr. pid zagal. red. prof. V. P. Malaichuka. Dnipro, 2018. 344 s.
3. «Sirius-18». Systema izmereniya i upravleniya impulsnoi aerodynamicheskoi truboi. Rukovodstvo po ekspluatatsii. ELVA4.044.901 RE. 2018. 45 s.
4. Abramovich G.N. Prikladnaya gazovaya dynamika. M., 1978. 888 s.
5. Raschet vnutrennego davlenia v otsekakh RN. YSF YZH UMN 041 01. Rukovodstvo operatora. 2016. 138 s.
6. Issledovania characteristic hyperzvukovoi aerodynamicheskoi truby AT-303. Ch. 1. Polya skorostey / A. M. Kharitonov at al. Teplophysika i aeromekhanika. 2006. T. 13, № 1. S. 1–17.

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9.2.2019 Gas-dynamic simulation of the supersonic stream in the pulsed wind tunnel
9.2.2019 Gas-dynamic simulation of the supersonic stream in the pulsed wind tunnel
9.2.2019 Gas-dynamic simulation of the supersonic stream in the pulsed wind tunnel

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]]> 3.1.2020 Analysis of the unsteady stress-strain behavior of the launch vehicle hold-down bay at liftoff https://journal.yuzhnoye.com/content_2020_1-en/annot_3_1_2020-en/ Fri, 29 Sep 2023 18:22:49 +0000 https://journal.yuzhnoye.com/?page_id=32230
2 Organization: Yangel Yuzhnoye State Design Office, Dnipro, Ukraine 1 ; Pidgorny A.
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3. Analysis of the unsteady stress-strain behavior of the launch vehicle hold-down bay at liftoff

Authors:

Degtiarov М. O.1, Avramov K. V.2

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; Pidgorny A. Intsitute of Mechanical Engineering Problems, Kharkiv, Ukraine2

Page: Kosm. teh. Raket. vooruž. 2020, (1); 26-33

DOI: https://doi.org/10.33136/stma2020.01.026

Language: Russian

Annotation: The study of thermal strength of the hold-down bay is considered. The hold-down bay is a cylindrical shell with the load-bearing elements as the standing supports. The case of the hold-down bay consists of the following structural elements: four standing supports and the compound cylindrical shell with two frames along the top and bottom joints. The purpose of this study was the development of a general approach for the thermal strength calculation of the hold-down bay. This approach includes two parts. Firstly, the unsteady heat fields on the hold-down bay surface are calculated by means of the semi-empirical method, which is based on the simulated results of the combustion product flow of the main propulsion system. The calculation is provided by using Solid Works software. Then the unsteady stress-strain behavior of the hold-down bay is calculated, taking into consideration the plastoelastic deformations. The material strain bilinear diagram is used. The finiteelement method is applied to the stress-strain behavior calculation by using NASTRAN software. The thermal field is assumed to be constant throughout the shell thickness. As a result of the numerical simulation the following conclusions are made. The entire part of the hold-down bay, which is blown by rocket exhaust jet, is under stress-strain behavior. The stresses of the top frame and the shell are overridden the breaking strength that caused structural failure. The structure of the hold-down bay, which is considered in the paper, is unappropriated to be reusable. The hold-down bay should be reconstructed by reinforcement in order to provide its reusability.

Key words: stress-strain behavior, finite-element method, plastoelastic deformations, breaking strength, reusability

Bibliography:

1. Elhefny A., Liang G. Stress and deformation of rocket gas turbine disc under different loads using finite element modeling. Propulsion and Power Research. 2013. № 2. P. 38–49. https://doi.org/10.1016/j.jppr.2013.01.002
2. Perakis N., Haidn O. J. Inverse heat transfer method applied to capacitively cooled rocket thrust chambers. International Journal of Heat and Mass Transfer. 2019. № 131. P. 150–166. https://doi.org/10.1016/j.ijheatmasstransfer.2018.11.048
3. Yilmaz N., Vigil F., Height J., et. al. Rocket motor exhaust thermal environment characterization. Measurement. 2018. № 122. P. 312–319. https://doi.org/10.1016/j.measurement.2018.03.039
4. Jafari M. Thermal stress analysis of orthotropic plate containing a rectangular hole using complex variable method. European Journal of Mechanics A /Solids. 2019. № 73. P. 212–223. https://doi.org/10.1016/j.euromechsol.2018.08.001
5. Song J., Sun B. Thermal-structural analysis of regeneratively cooled thrust chamber wall in reusable LOX / Methane rocket engines. Chinese Journal of Aeronautics. 2017. № 30. P. 1043–1053.
6. Ramanjaneyulu V., Murthy V. B., Mohan R. C., Raju Ch. N. Analysis of composite rocket motor case using finite element method. Materials Today: Proceedings. 2018. № 5. P. 4920–4929.
7. Xu F., Abdelmoula R., Potier-Ferry M. On the buckling and post-buckling of core-shell cylinders under thermal loading. International Journal of Solids and Structures. 2017. № 126–127. P. 17–36.
8. Wang Z., Han Q., Nash D. H., et. al. Thermal buckling of cylindrical shell with temperature-dependent material properties: Conventional theoretical solution and new numerical method. Mechanics Research Communications. 2018. № 92. P. 74–80.
9. Duc N. D. Nonlinear thermal dynamic analysis of eccentrically stiffened S-FGM circular cylindrical shells surrounded on elastic foundations using the Reddy’s third-order shear de-formation shell theory. European Journal of Mechanics A /Solids. 2016. № 58. P. 10–30.
10. Trabelsi S., Frikha A., Zghal S., Dammak F. A modified FSDT-based four nodes finite shell element for thermal buckling analysis of functionally graded plates and cylindrical shells. Engineering Structures. 2019. № 178. P. 444–459.
11. Trinh M. C., Kim S. E. Nonlinear stability of moderately thick functionally graded sandwich shells with double curvature in thermal environment. Aerospace Science and Technology. 2019. № 84. P. 672–685.
12. Лойцянский Л. Г. Механика жидкости и газа. М., 2003. 840 с.
13. Launder B. E., Sharma B. I. Application of the energy dissipation model of turbulence to the calculation of flow near a spinning disc. International Journal of Heat and Mass Transfer. 1974. № 1. P. 131–138.
14. Михеев М. А., Михеева И. М. Основы теплопередачи. М., 1977. 345 с.
15. Малинин Н. Н. Прикладная теория пластичности и ползучести. М., 1968. 400 с.

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3.1.2020 Analysis of the unsteady stress-strain behavior of the launch vehicle hold-down bay at liftoff
3.1.2020 Analysis of the unsteady stress-strain behavior of the launch vehicle hold-down bay at liftoff
3.1.2020 Analysis of the unsteady stress-strain behavior of the launch vehicle hold-down bay at liftoff

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2 Organization: Yangel Yuzhnoye State Design Office, Dnipro, Ukraine 1 ; The Institute of Technical Mechanics, Dnipro, Ukraine 2 Page: Kosm.
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2. Analysis of development trends of design parameters and basic characteristics of missiles for the advanced multiple launch rocket systems

Authors:

Aksenenko A. V.1, Hurskyi O. I.1, Klochkov A. S.1, Kondratiuk Ye. A.1, Senkin V. S.2, Siutkina-Doronina S. V.2

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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4. Reaktivnye sistemy zalpovogo ognia zarubezhnykh stran: obzor po materialam otkrytoi pechati za 1987–2016 gg. i interneta. Dnipro, 2016. Ч. I. 205 s.
5. Upravliaemye OTRK i TRK stran mira: obzor po materialam otkrytoi otechestvennoi i zarubezhnoi pechati za 2008–2014 gg. i interneta. Dnipro, 2014. 162 s.
6. Tail controlled rocket demonstrates near-vertical impact at extended range. URL: https://www.army.mil/article-amp/207357/tail_controlled_rocket_demonstrates_near_vertical_impact_at_extended_range (Access date 01.09.2019).
7. SY-400 Short-Range Ballistic Missile. URL: http://www.military-today.com/missiles/sy_400.htm (Access date 01.09.2019).
8. Vohniana “Vilkha”: nova vysokotochna systema zalpovoho vohnyu. Vpershe – detalno. URL: https://defence-ua.com/index.php/statti/4588-vohnyana-vilkha-nova-vysokotochna-systema-zalpovoho-vohnyu-vpershe-detalno (Access date 01.09.2019).
9. Gurov S. V. Reaktivnye sistemy zalpovogo ognia: obzor. 1-е izd. Tula, 2006. 432 s.
10. The new M30A1 GMLRS Alternate Warhead to replace cluster bombs for US Army Central 71601171. URL: https://www.armyrecognition.com/weapons_defence_industry_military_technology_uk/the_new_m30a1_gmlrs_alternate_warhead_to_replace_cluster_bombs_for_us_army_central_71601171.html (Access date 01.09.2019).
11. High-Mobility Artillery Rocket System (HIMARS), a member of MLRS family. URL: https://army-technology.com/projects/himars/ (Access date 01.09.2019).
12. SR-5 Multiple Launch Rocket System. URL: http://www.military-today.com/artillery/sr5.htm (Access date 01.09.2019).
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22. Aksenenko A. V., Baranov E. Yu., Hursky A. I., Klochkov A. S., Morozov A. S., Alpatov A. P., Senkin V. S., Siutkina-Doronina S. V. Metodicheskoe obespechenie dlia optimizatsii na nachalnom etape proektirovaniia proektnykh parametrov, parametrov traektorii i programm upravleniia dvizheniem raketnogo ob’ekta. Kosmicheskaia tekhnika. Raketnoe vooruzhenie: sb. nauch.-tekhn. st. / GP “KB “Yuzhnoye”. Dnipro, 2018. Vyp. 2 (116). S. 101–116. https://doi.org/10.33136/stma2018.02.101
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2.1.2020 Analysis of development trends of design parameters and basic characteristics of missiles for the advanced multiple launch rocket systems
2.1.2020 Analysis of development trends of design parameters and basic characteristics of missiles for the advanced multiple launch rocket systems
2.1.2020 Analysis of development trends of design parameters and basic characteristics of missiles for the advanced multiple launch rocket systems

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]]> 12.1.2017 Static Performance Prediction of Hot-Gas Flapper-Nozzle Actuator https://journal.yuzhnoye.com/content_2017_1/annot_12_1_2017-en/ Fri, 22 Sep 2023 15:14:35 +0000 https://journal.yuzhnoye.com/?page_id=31702
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12. Static Performance Prediction of Hot-Gas Flapper-Nozzle Actuator

Authors:

Tsyganov V. M.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2017 (1); 78-83

Language: Russian

Annotation: The basic mathematical relations are considered to construct static characteristics of nozzle-shutter twostage piston pneumatic drive with the working medium – powder combustion products.

Key words:

Bibliography:
1. Oleinik V. P. et al. Static Characteristics of Gas Drive with Jet Engine / V. P. Oleinik, Y. A. Yelansky, V. N. Kovalenko, L. G. Kaluger, Е. V. Vnukov. Space Technology. Missile Armaments: Collection of scientific-technical articles. 2015. Issue. 1. P. 21-27.
2. Kornilov Y. G. et al. Pneumatic Elements and Systems. К., 1968. 143 p.
3. Hydraulic and Pneumatic Power Control System / Under the editorship of J. Blackborn, H. Reethoff, G. L. Sherer. М., 1962. 614 p.
4. Mertaf S. A. Tutorial on the Theory of Electrohydraulic Servo Mechanism with Acceleration Control Operating in Switchover Mode. Problems of Rocket Engineering. 1961. No. 2. P. 74-95.
5. Banshtyk A. М. Electrohydraulic Servo Mechanisms with Pulse-Width Control. М., 1972. 144 p.

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12.1.2017 Static Performance Prediction of Hot-Gas Flapper-Nozzle Actuator
12.1.2017 Static Performance Prediction of Hot-Gas Flapper-Nozzle Actuator
12.1.2017 Static Performance Prediction of Hot-Gas Flapper-Nozzle Actuator
]]> 13.1.2017 Reliability Evaluation of ILV Thermostating System Mating Hoses https://journal.yuzhnoye.com/content_2017_1/annot_13_1_2017-en/ Fri, 22 Sep 2023 15:13:28 +0000 https://journal.yuzhnoye.com/?page_id=29483
2 Organization: Yangel Yuzhnoye State Design Office, Dnipro, Ukraine 1 ; State Enterprise “Ukrainian Research Design-Technological Institute of Elastomer Materials and Products”, Dnipro, Ukraine 2 Page: Kosm.
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13. Reliability Evaluation of ILV Thermostating System Mating Hoses

Authors:

Bigun S. O.1, Khorolskyi M. S.2, Skokov O. I.2

Organization:

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

Page: Kosm. teh. Raket. vooruž. 2017 (1); 84-87

Language: Russian

Annotation: The technique is proposed of reliability evaluation of space launch vehicle low pressure air thermostating system joints hoses. By calculation method, high reliability level was confirmed of hoses of joints being an interface elements of launch vehicle launch complexes.

Key words:

Bibliography:
1. Development of Single Action Units’ Hoses of Cyclone-4 Space Launch System Thermostating System: SOW for R&D 2G40.12.8599.608TЗ/Yuzhnoye SDO. 2009. 41 p.
2. Abramov E. I., Kolesnichenko K. A., Maslov V. T. Hydraulic Actuator Elements (Guide). Kyiv, 1969. 320 p.
3. Shor Y. B., Kuzmin F. I. Tables for Reliability Analysis and Control. М, 1968. 286 p.
4. Ventsel E. S. Theory of Probability. М., 1964. 576 p.

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13.1.2017 Reliability Evaluation of ILV Thermostating System Mating Hoses
13.1.2017 Reliability Evaluation of ILV Thermostating System Mating Hoses
13.1.2017 Reliability Evaluation of ILV Thermostating System Mating Hoses
]]> 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
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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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1. Optimization of the trajectory of the antiaircraft guided missile

Authors:

Izhko V. O., Yemelyanova I. O., Reznik I. M., Khorolskiy P. G.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (2); 3-10

DOI: https://doi.org/10.33136/stma2019.02.003

Language: Russian

Annotation: The article is devoted to optimization of a trajectory of the antiaircraft guided missile performed in design phase. The review of existing solutions on this issue confirmed the topicality of the problem. The analytical solution cannot be obtained, therefore, according to modern tendencies, optimization by numerical method of original development was performed. The basis of the method is two-level optimization which is carried out, in turn, by two different numerical methods and for two different criteria functions. At the top level, by method of random search and as a variant, by method of coordinate descent, the search was carried out for a fixed set of intermediate for the specified flight range trajectory points which co-ordinates in aggregate provide the necessary optimum. At the bottom level, for each pair of consecutive intermediate points, the boundary problem of falling into distant point by one-dimensional optimization was solved. The coordinate descent method was used for search for the simplified flight program. As optimization criteria for top level, minimum flight time or maximum final speed, for bottom  terminal criterion were used. The control program selected the angle of attack  program. As a result, the optimum and suboptimum (additionally ensuring minimum calculation time) trajectories and flight programs to maximum range and different altitudes were obtained. The analysis of results showed practical proximity of trajectories of minimum flight time and maximum final speed.

Key words: anti-aircraft missile, optimization, angle of attack program, trajectory

Bibliography:
1. Letov A. M. Dynamika poleta i upravlenie. M., 1969. 360 s.
2. Ushan’ V. N. Metod synteza optymalnykh traektoriy dlya vyvoda dynamicheskykh obiektov v zadannuyu tochku. Systemy obrobky informatsii. 2014. № 1 (117). S. 67-71.
3. Zarubinskaya A. L. Optimalnoe upravlenie dvizheniem letatelnykh apparatov v atmosfere ot starta do tochek vstrechi. Technicheskaya mekhanika. 1997. № 5. S. 23-28.
4. Grabchak V. I. Osnovni aspekty opysu zadachi pro optimalnu shvidkodiu keruvanny rukhom rakety. Systemy ozbroyennya i viyskova tekhnika. 2014. № 4(40). S. 13-20.
5. Shaw Y. Ong. Optimal Planar Evasive Aircraft Maneuvers Against Proportional Navigation Missiles. Journal of guidance, control and dynamics. 1996. Vol. 19, № 6. Р. 1210-1215. https://doi.org/10.2514/3.21773
6. Renjith R. Kumar. Near-Optimal Three-Dimensional Air-to-Air Missile Guidance Against Maneuvering Target. Journal of guidance, control and dynamics. 1995. Vol. 18, № 3. Р. 457-464. https://doi.org/10.2514/3.21409
7. Paul J. Enright. Conway Discrete Approximations to Optimal Trajectories Using Direct Transcription and Nonlinear Programming. Journal of guidance, control, and dynamics. 1992. Vol. 15, № 4. Р. 994-1002. https://doi.org/10.2514/3.20934
8. Craig A. Phillips. Trajectory Optimization for a Missile Using a Multitier Approach. Journal of Spacecraft and Rockets. 2000. Vol. 37, № 5. Р. 653-662. https://doi.org/10.2514/2.3614
9. Lebedev A. A., Gerasyuta N. F. Ballistila raket. M., 1970. 244 s.
10. Proektirovanie zenitnykh upravlyaemykh raket / I. I. Arkhangelskiy i dr.; pod red. I. S. Golubeva i V. G. Svetlova. M., 2001. 732 s.
11. Drakin I. I. Osnovy proektirovania letatelnykh apparatov s uchetom ekonomicheskoy effektivnosti. M., 1973. 224 s.
12. Beiko I. V., Bublik B. N., Zinko P. N. Metody i algoritmy resheniya zadach optimizatsii. K., 1983. 512 s.
13. Krinetskiy Ye. I. Systemy samonavedeniya. M., 1970. 236 s.

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1.2.2019 Optimization of the trajectory of the antiaircraft guided missile
1.2.2019 Optimization of the trajectory of the antiaircraft guided missile
1.2.2019 Optimization of the trajectory of the antiaircraft guided missile

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21. Contemporary approaches to the improvement of methods of space launch system operation for commercial launches of ILV

Authors:

Hlechkov V. H.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2020, (1); 184-192

DOI: https://doi.org/10.33136/stma2020.01.184

Language: Russian

Annotation: The article deals with the problems of applying new approaches to formation and improvement of operation system. Turning of space hardware and services into marketable commodity requires their new qualities that determine competitiveness. The main task of presented works was approbation of new approaches to improvement of space launch systems operation quality and operation process effectiveness by the example of prospective Cyclone-4M space rocket complex. The works to form and improve its operation system were performed using the methods based on general theory of space systems operation and the pocedures based on the results of research work conducted by Yuzhnoye SDO in 2015 for analytical evaluation of launch services costs. The topicality of the article is confirmed by the results of practical application of new approaches in main directions of Cyclone-4M space rocket complex operation system improvement, which allowed increasing commercial attractibility of Yuzhnoye SDO-developed systems due to reduction of direct recurring costs and annual expenses. The article describes the course of development of operation model of a created object; based on investigation of the processes of this model, the object’s performance characteristics are detemined. The basis of the article are the organizational-and-technical decisions used herewith and the results obtained for Cyclone-4M space rocket complex. The article is of practical interest for specialists involved in creation of space rocket complexes and other sophisticated systems where the operation system is a multi-level organizational-technical system.

Key words: space hardware, launch services, performance characteristics, operation model, organizational-and-technical decisions

Bibliography:
1. Analiticheskaia otsenka ob’ema rabot i zatrat na puskovye uslugi i napravleniia rabot dlia ikh snizheniia v perspektivnykh RKK razrabotki GP “KB “Yuzhnoye”: tekhn. otchet / GP “KB “Yuzhnoye”. Dnepropetrovsk, 2015. 344 s.
2. Teoriia i praktika ekspluatatsii ob’ektov kosmicheskoi infrastruktury: monografiia / N. D. Anikeichik i dr. SPb., 2006. Т. 1: Ob’ekty kosmicheskoi infrastruktury. 400 s.
3. Ispytaniia i ekspluatatsiia raketnykh kompleksov: kurs lektsii / А. V. Agarkov i dr.; pod red. А. V. Degtyareva. GP “KB “Yuzhnoye”. Dnipro, 2016. Kn. 1. 505 s.

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21.1.2020 Contemporary approaches to the improvement of methods of space launch system operation for commercial launches of ILV
21.1.2020 Contemporary approaches to the improvement of methods of space launch system operation for commercial launches of ILV
21.1.2020 Contemporary approaches to the improvement of methods of space launch system operation for commercial launches of ILV

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Organization: Yangel Yuzhnoye State Design Office, Dnipro, Ukraine Page: Kosm.
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20. Studying the possibility of alternating delivery of rocket propellant wastes to a common thermal neutralization facility

Authors:

Shynkorenko О. I., Kostenko М. V.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2020, (1); 177-183

DOI: https://doi.org/10.33136/stma2020.01.177

Language: Russian

Annotation: The possibility is considered of using rocket propellant thermal neutralization units for decontamination of dangerous industrial wastes. The advantages of thermal neutralization units are considered, their operating principle is described, by the example of high-temperature toxic rocket propellants, the chemical reactions that take place in combustion chamber are formulated. The combustion chamber is a component of the neu tralization unit, it is in the combustion chamber, in the environment of created high temperatures, that the process of elimination of dangerous substances takes place. Taking into consideration the high cost of neutralization units, which will be a factor hindering the wide-scale introduction of neutralization units to decrease technogenic load on environment of Ukraine, the option is proposed of reducing the costs during the use of thermal neutralization units by way of combining the function of oxidizer neutralization unit and fuel neutralization unit in a single universal neutralization unit. The article substantiates the topicality and necessity of works to create the universal thermal neutralization unit from the viewpoint of economic and ecological aspects. The article presents a generalized description of technology and methodology of research tests of pilot samples of assemblies for high-temperature rocket propellants vapor and industrial wastewater supply into the neutralization unit. The assemblies for high-temperature rocket propellants vapor and industrial wastewater supply are considered as most critical components of the universal neutralization unit from the viewpoint of neutralized substance changing. The experiments were conducted on water solutions of rocket propellants that in this case simulated the contact of internal cavities of supply assemblies with aggressive toxic media. The conditions were created at which the probability existed of interaction of rocket propellants residues in stagnation zones at the moment of changing the supplied propellant component. In the frameworks of research tests of pilot samples, the obtained results were considered and analyzed. The findings are presented that confirm practical feasibility of using integrated supply assemblies.

Key words: neutralization unit, supply assemblies, alternate supply, rocket propellants interaction, universal thermal neutralization unit

Bibliography:
1. Kolesnikov S. V. Okislenie nesimmetrichnogo dimetilgidrazina (geptila) i identifikatsiia produktov ego prevrashcheniia pri prolivakh. Monografiia. NP “SibAK”, Novosibirsk, 2014.
2. Zhidkoe raketnoe toplivo v regione OBSE: obzor aspektov utilizatsii. FSC.DEL/443/07/Rev. 2. 23 okt. 2008 g.
3. Egorychev V. S., Kondrusev V. S. Topliva khimicheskikh raketnykh dvigatelei. Samara, 2007.
4. Kasimov А. М., Semenov V. Т., Shcherban’ N. H., Miasoedov V. V. Sovremennye problemy i resheniia v sisteme upravleniia opasnymi otkhodami. Kharkiv, 2008.

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20.1.2020 Studying the possibility of alternating delivery of rocket propellant wastes to a common thermal neutralization facility
20.1.2020 Studying the possibility of alternating delivery of rocket propellant wastes to a common thermal neutralization facility
20.1.2020 Studying the possibility of alternating delivery of rocket propellant wastes to a common thermal neutralization facility

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