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

10.2.2019 Dynamic performance of the gas drive with jet motor

Вацлав Самусевич — Tue, 03 Oct 2023 11:52:15 +0000

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

manager — Tue, 03 Oct 2023 11:48:27 +0000

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

manager — Fri, 29 Sep 2023 18:22:49 +0000

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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2.1.2020 Analysis of development trends of design parameters and basic characteristics of missiles for the advanced multiple launch rocket systems

Вацлав Самусевич — Fri, 29 Sep 2023 18:16:07 +0000

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:

1. Degtyarev A. V. Raketnaia tekhnika. Problemy i perspektivy: izbrannye nauchno-tekhnicheskie publikatsii. Dnepropetrovsk, 2014. 420 s.

2. Pro zatverdzhennia Poriadku zdiisnennia derzhavnoho kontriliu za mizhnarodnymy peredachamy tovariv podviinoho vykorystannia:Postanova Kabinetu Ministriv Ukrainy vid 28 sichnia 2004 r. № 86. Date: 29.11.2018. URL: https://zakon.rada.gov.ua/laws/show/86-2004-%D0%BF (Access date 01.09.2019).

3. Catalogue China Aerospase Long-march International. February, 2017. 136 p.

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).

13. Effectivnost slozhnykh system. Dinamicheskie modeli / V. А. Vinogradov, V. А. Hrushchansky, S. S. Dovhodush i dr. М., 1989. 285 s.

14. Ilichev А. V., Volkov V. D., Hrushchansky V. А. Effectivnost proektiruemykh elementov slozhnykh system: ucheb. posobie. М., 1982. 280 s.

15. Krotov V. F., Gurman V. I. Metody I zadachi optimalnogo upravleniia. М., 1973. 446 s.

16. Pontriagin L. S., Boltiansky V. G., Gamkrelidze R. V., Mishchenko Е. F. Matematicheskaia teoriia optimalnykh protsesov. М., 1969. 385 s.

17. Tarasov Е. V. Algoritm optimalnogo proektirovaniia letatelnogo apparata. М., 1970. 364 s.

18. Shcheverov D. N. Proektirovanie bespilotnykh letatelnykh apparatov. М., 1978. 264 s.

19. Siniukov А. М., Volkov L. I., Lvov А. I., Shishkevich А. М. Ballisticheskaia raketa na tverdom toplive / pod red. А. М. Siniukova. М., 1972. 511 s.

20. Burov М. А., Varfolomeev V. I., Volkov L. I. Proektirovanie i ispytanie ballisticheskikh raket / pod red. V. I. Varfolomeeva, М. I. Kopytova. М., 1970. 392 s.

21. Siutkina-Doronina S. V. K voprosu optimizatsii proektnykh parametrov i programm upravleniia raketnogo ob’ekta s raketnym dvigatelem na tverdom toplive. Aviatsionno-kosmicheskaia tekhnika i tekhnologiia. 2017. № 2 (137). S. 44–59.

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

23. Metodicheskoe obespechenie dlia optimizatsii na nachalnom etape proektirovaniia proektnykh parametrov, programm upravleniia, ballisticheskikh, energeticheskikh i gabaritno-massovykh kharakteristik upravliaemykh raketnykh ob’ektov, osushchestvliaiushchikh dvizhenie po aeroballisticheskoi traektorii: otchet po NIR / ITM NANU i GKAU, GP “KB “Yuzhnoye”. Dnepropetrovsk, 2017. 159 S.

24. Senkin V. S. K Vyboru programm upravleniia dvizheniem raketnogo ob’ekta po ballisticheskoi traektorii. Tekhnicheskaia mekhanika. 2018. № 1. S. 48–59.

25. Alpatov A. P., Senkin V. S. Metodicheskoe obespechenie dlia vybora oblika, optimizatsii proektnykh parametrov i programm upravleniia poletom rakety-nositelia. Tekhnicheskaia mekhanika. 2013. № 4. S. 146–161.

26. Alpatov A. P., Senkin V. S. Kompleksnaia zadacha optimizatsii osnovnykh proektnykh parametrov i programm upravleniia dvizheniem raket kosmicheskogo naznacheniia. Tekhnicheskaia mekhanika. 2011. № 4. S. 98–113.

27. Senkin V. S. Optimizatsiia proektnykh parametrov rakety-nositelia sverkhlegkogo klassa. Tekhnicheskaia mekhanika. 2009. № 1. S. 80–88.

28. Lebedev А. А., Gerasiuta N. F. Ballistika raket. М., 1970. 244 s.

29. Razumev V. F., Kovalev B. K. Osnovy proektirovaniia ballisticheskikh raket na tverdom toplive: ucheb. posobie dlia vuzov. М., 1976. 356 s.

30. Erokhin B. Т. Teoreticheskie osnovy oroektirovaniia RDTT. М., 1982. 206 s.

31. Abugov D. I., Bobylev V. М. Teoriia i raschet raketnykh dvigatelei tverdogo topliva: uchebnik dlia mashinostroitelnykh vuzov. М., 1987. 272 s.

32. Shishkov А. А. Gasodinamika porokhovykh raketnykh dvigatelei: inzhenernye metody rascheta. М., 1974. 156 s.

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12.1.2017 Static Performance Prediction of Hot-Gas Flapper-Nozzle Actuator

manager — Fri, 22 Sep 2023 15:14:35 +0000

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

Вацлав Самусевич — Wed, 13 Sep 2023 12:02:02 +0000

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

Authors:

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

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

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

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

Language: Russian

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

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

Bibliography:

1. Mashinostroenie. Entsiklopediia / А. P. Adzhian i dr.; pod red. V. P. Legostaeva. М., 2012. Т. IV-22. V 2-kh kn. Kn. 1. 925 s.

2. Bement L. J., Schimmel M. L. A Manual for Pyrotechnic Design, Development and Qualification: NASA Technical Memorandum 110172. 1995.

3. Yumashev L. P. Ustroistvo raket-nositelei (vspomagatelnye sistemy): ucheb. posob. Samara, 1999. 190 s.

4. Lee J., Han J.-H., Lee Y., Lee H. Separation characteristics study of ridge-cut explosive bolts. Aerospace Science and Technology. 2014. Vol. 39. Р. 153-168. https://doi.org/10.1016/j.ast.2014.08.016

5. Yanhua L., Jingcheng W., Shihui X., Li C., Yuquan W., Zhiliang L. Numerical Study of Separation Characteristics of Piston-Type Explosive Bolt. Shock and Vibration. https://doi.org/10.1155/2019/2092796

6. Yanhua L., Yuan L., Xiaogan L., Yuquan W., Huina M., Zhiliang L. Identification of Pyrotechnic Shock Sources for Shear Type Explosive Bolt. Shock and Vibration. https://doi.org/10.1155/2017/3846236

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16.1.2020 Parameters of the supersonic jet of a block propulsion system, flowing into a gas duct, considering chemical kinetics of gas-cycle transformations

Вацлав Самусевич — Wed, 13 Sep 2023 11:18:27 +0000

16. Parameters of the supersonic jet of a block propulsion system, flowing into a gas duct, considering chemical kinetics of gas-cycle transformations

Authors:

Furkalo S. A., Stelmakh K. L., Lazarev T. V.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2020, (1); 149-154

DOI: https://doi.org/10.33136/stma2020.01.149

Language: Russian

Annotation: Launch vehicle lift-off is one of the most critical phases of the whole mission requiring special technical solutions to ensure trouble-free and reliable launch. A source of increased risk is the intense thermal and pressure impact of rocket propulsion jet on launch complex elements and on rocket itself. The most accurate parameters of this impact can be obtained during bench tests, which are necessary to confirm the operability of the structure, as well as to clarify the parameters and configuration of the equipment and systems of complex. However, full-scale testing is expensive and significantly increases the development time of the complex. Therefore, a numerical simulation of processes is quite helpful in the design of launch complexes. The presented work contains simulation of liquid rocket engine combustion products jet flowing into the gas duct at the rocket lift-off, taking into account the following input data: the parameters of propulsion system, geometric parameters of launch complex elements, propulsion systems nozzles and gas duct. A three-dimensional geometric model of the launch complex, including rocket and gasduct, was constructed. The thermodynamic parameters of gas in the engine nozzle were verified using NASA CEA code and ANSYS Fluent. When simulating a multicomponent jet, the equations of conservation of mass, energy, and motion were solved taking into account chemical kinetics. The three-dimensional problem was solved in ANSYS Fluent in steady-state approach, using Pressure-based solver and RANS k-omega SST turbulence model. The calculation results are the gas-dynamic and thermodynamic parameters of jets, as well as distribution of gas-dynamic parameters at nozzle exit, in flow and in boundary layer at gas duct surface. The methodology applied in this work makes it possible to qualitatively evaluate the gas-dynamic effect of combustion products jets on gas duct for subsequent optimization of its design.

Key words: liquid rocket engine, combustion products, multicomponent flow, ANSYS Fluent

Bibliography:

1. Bonnie J. McBride, Sanford Gordon. Computer Program for Calculation of Complex Chemical Equilibrium Compositions and Applications. II. Users Manual and Program Descriptions: NASA Reference Publication 1311. 1996.

2. Ten-See Wang. Thermophysics Characterization of Kerosene Combustion. Journal of Thermophysics and Heat Transfer. 2001. № 2, Vol. 15. P. 140–147. https://doi.org/10.2514/2.6602

3. Maas U., Warnatz J. Ignition Processes in Carbon-Monoxide-Hydrogen-Oxygen Mixtures: Twenty-Second Symposium (International) on Combustion. The Combustion Institute, 1988. P. 1695–1704. https://doi.org/10.1016/S0082-0784(89)80182-1

4. Timoshenko V. I. Teoreticheskiie osnovy tekhnicheskoj gazovoj dinamiki. Kiev, 2013. S. 154–155.

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10.1.2020 Calculation and selection of parameters for a propellant consumption diagram of dual-thrust main SRM

Вацлав Самусевич — Wed, 13 Sep 2023 10:47:53 +0000

10. Calculation and selection of parameters for a propellant consumption diagram of dual-thrust main SRM

Authors:

Yenotov V. H., Pustovharova O. V.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2020, (1); 99-106

DOI: https://doi.org/10.33136/stma2020.01.099

Language: Russian

Annotation: The main solid rocket motors of surface-to-air missiles and some short-range missiles have, as a rule, two operation modes – starting (augmented rating) and cruise (with decreased propellant consumption level). The methods to calculate intraballistic characteristics of such motors have a number of peculiarities, which set them apart from the methods of determining the characteristics of motors with constant propellant consumption level. The purpose of this article is to analyze such peculiarities, design methods, to find interrelation between the parameters of propellant consumption diagram, to determine the impact on the latter of motor design features and propellant characteristics. To achieve this goal, the method of analytical dependencies was developed. The equations obtained show that the required parameters of diagrams (including consumption-thrust characteristics difference between the starting and cruise modes) can be ensured due to varying either case diameter or propellant combustion rate or due to combined variation of these values. In practice, the cases are possible when for some reasons it does not seem possible to vary the case diameter or propellant combustion rate and the requirements to consumption diagram cannot be satisfied to the full extent. The task of motor developer in that case consists in determination of acceptable (alternative) propellant consumption diagrams that would be closest to required. The proposed method is based on calculation and construction of nomograms of dependencies of relative propellant consumption in cruse mode on relative time of starting leg at different propellant combustion rates and constant (required) case diameter and vice versa, at different values of case diameter and constant (available) propellant combustion rate. Using these nomograms, the rocket developer can determine the propellant consumption diagram acceptable for the rocket. In a number of cases, design limitations for separate main motor assemblies are imposed on consumption characteristic diagram that have an impact on its required parameters. The presented materials allow evaluating that impact and contain the proposals to remove it. The presented method allows quickly determining the conditions needed to fulfill required propellant combustion products consumption diagrams and in case of nonfulfillment of these conditions – allow presenting alternative options for selection of most acceptable one.

Key words: solid propellant charge mass, propellant combustion rate, combustion chamber pressure, operation time in starting and cruise modes, combustion chamber pressure difference

Bibliography:

1. K vyboru velichiny davliniia v kamere sgoraniia marshevykh RDTT: tekhn. otchet / GP “KB “Yuzhnoye”. Dnipro, 2017. 19 s.

2. Enotov V. G., Kushnir B. I., Pustovgarova Е. V. Avtomatizirovannaia proektnaia otsenka kharakteristik marshevykh dvigatelei na tverdom toplive s korpusom iz vysokoprochnykh metallicheskikh materialov takticheskikh i operativno-takticheskikh raket: ucheb.-metod. posobie / pod red. А. S. Kirichenko. Dnepropetrovsk, 2014. 72 s.

3. Sorkin R. Е. Gasotermodinamika raketnykh dvigatelei na tverdom toplive. М, 1967. 368 s.

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19.2.2018 Control of Validity and Assessment of Accuracy of Telemetry Results during Full-Scale Test of Launch Vehicles

Вацлав Самусевич — Thu, 07 Sep 2023 12:23:58 +0000

19. Control of Validity and Assessment of Accuracy of Telemetry Results during Full-Scale Test of Launch Vehicles

Authors:

Aksiuta О. А., Balyayev O. A., Konstantinov G. I., Sidoruk V. O.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (2); 157-172

DOI: https://doi.org/10.33136/stma2018.02.157

Language: Russian

Annotation: The measurement errors upon conducting flight tests for launch vehicles are evaluated by considering the interferences and uncertainties in the measurement system procedure. Formal use of this approach can lead to unpredictable consequences. More reliable evaluation of errors upon conducted measurements can be achieved if the measurement process is regarded as a procedure of successive activities for designing, manufacturing, and testing the measurement system and the rocket including measurements and their processing during the after-flight analysis of the received data. The sampling rates of the main controlled parameters are three to ten times higher than the frequency range of their changing. Therefore, it is possible to determine the characteristics of the random error components directly on the basis of registered data. The unrevealed systematic components create the basic uncertainty in the evaluation of the examined parameter’s total measurement error. To evaluate the precision and measurement accuracy of a particular launch, the article suggests specifying the preliminary data on measurement error components determined during prelaunch processing and launch. Basic structures of algorithms for evaluation of precision and measurement accuracy for certain mathematical models that form the measured parameters were considered along with the practical case when static correlation existed among the measured parameters.

Key words: flight tests, sensor, measurement error, mathematical model

Bibliography:

1. Novitsky P. V., Zograf I. A. Evaluation of Measurement Errors. L., 1985. 248 p.

2. Shmutzer E. Relativity Theory. Modern Conception. Way to Unity of Physics. М., 1981. 230 p.

3. Blekhman I. I., Myshkis A. D., Panovenko Y. G. Applied Mathematics: Subject, Logic, Peculiarities of Approaches. К., 1976. 270 p.

4. Moiseyev N. N. Mathematical Problems of System Analysis. М., 1981. 488 p.

5. Bryson A., Ho Yu-Shi. Applied Theory of Optimal Control. М., 1972. 544 p.

6. Yevlanov L. G. Monitoring of Dynamic Systems. М., 1972. 424 p.

7. Sergiyenko A. B. Digital Signal Processing: Collection of publications. 2011. 768 p.

8. Braslavsky D. A., Petrov V. V. Precision of Measuring Devices. М., 1976. 312 p.

9. Glinchenko A. S. Digital Signal Processing: Course of lectures. Krasnoyarsk, 2008. 242 p.

10. Garmanov A. V. Practice of Optimization of Signal-Noise Ratio at ACP Connection in Real Conditions. М., 2002. 9 p.

11. Denosenko V. V., Khalyavko A. N. Interference Protection of Sensors and Connecting Wires of Industrial Automation Systems. SТА. No. 1. 2001. P. 68-75.

12. Garmanov A. V. Connection of Measuring Instruments. Solution of Electric Compatibility and Interference Protection Problems. М., 2003. 41 p.

13. TP ACS Encyclopedia. bookASUTR.ru.

14. Smolyak S. A., Titarenko B. P. Stable Estimation Methods. М., 1980. 208 p.

15. Fomin A. F. et al. Rejection of Abnormal Measurement Results. М., 1985. 200 p.

16. Medich J. Statistically Optimal Linear Estimations and Control. М., 1973. 440 p.

17. Sage E., Mells J. Estimation Theory and its Application in Communication and Control. М., 1976. 496 p.

18. Filtration and Stochastic Control in Dynamic Systems: Collection of articles / Under the editorship of K. T. Leondes. М., 1980. 408 p.

19. Krinetsky E. I. et al. Flight Tests of Rockets and Spacecraft. М., 1979. 464 p.

20. Viduyev N. G., Grigorenko A. G. Mathematical Processing of Geodesic Measurements. К., 1978. 376 p.

21. Aivazyan S. A., Yenyukov I. S., Meshalkin L. D. Applied Statistics. Investigation of Dependencies. М., 1985. 487 p.

22. Sirenko V. N., Il’yenko P. V., Semenenko P. V. Use of Statistic Approaches in Analysis of Gas Dynamic Parameters in LV Vented Bays. Space Technology. Missile Armaments: Collection of scientific-technical articles. Issue 1. P. 43-47.

23. Granovsky V. A., Siraya T. N. Methods of Experimental Data Processing at Measurements. L., 1990. 288 p.

24. Zhovinsky A. N., Zhovinsky V. N. Engineering Express Analysis of Random Processes. М., 1979. 112 p.

25. Anishchenko V. A. Control of Authenticity of Duplicated Measurements in Uncertainty Conditions. University News. Minsk, 2010. No. 2. P. 11-18.

26. Anishchenko V. A. Reliability and Accuracy of Triple Measurements of Analog Technological Variables. University News. Minsk, 2017. No. 2. P. 108-117.

27. Shenk H. Theory of Engineering Experiment. М., 1972. 381 p.

28. Bessonov А. А., Sverdlov L. Z. Methods of Statistic Analysis of Automatic Devices Errors. L., 1974. 144 p.

29. Pugachyov V. N. Combined Methods to Determine Probabilistic Characteristics. М., 1973. 256 p. https://doi.org/10.21122/1029-7448-2017-60-2-108-117

30. Gandin L. S., Kagan R. L. Statistic Methods of Meteorological Data Interpretation. L., 1976. 360 p.

31. Zheleznov I. G., Semyonov G. P. Combined Estimation of Complex Systems Characteristics. М., 1976. 52 p.

32. Vt222М Absolute Pressure Sensor: ТU Vt2.832.075TU. Penza, 1983.

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12.2.2018 Methodological Support for Initial Phase Optimization of Projecting Design, Trajectory Parameters and Rocket Object Motion Control Programs

Вацлав Самусевич — Thu, 07 Sep 2023 11:38:27 +0000

12. Methodological Support for Initial Phase Optimization of Projecting Design, Trajectory Parameters and Rocket Object Motion Control Programs

Authors:

Aksyonenko A. V.¹, Baranov E. Y.¹, Hurskyi O. I.¹, Klochkov A. S.¹, Morozov A. S.¹, Alpatov A. P.², 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. 2018 (2); 101-116

DOI: https://doi.org/10.33136/stma2018.02.101

Language: Russian

Annotation: The main scientific and methodological propositions for designing single-stage guided missiles with main solid rocket motors that are intended for delivering payload to the given spatial point with required and specified kinematic motion parameters are defined. The aim of the article is to develop methodology for the early design phase to improve the basic characteristics of guided missiles, including formalization of complex problem to optimize design parameters, trajectory parameters and motion control programs for guided missiles capable of flying along the ballistic, aeroballistic or combined trajectories. The task is defined as a problem of the optimal control theory with limitations in form of equality, inequality and differential constraints. 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 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 criterion functional that was used for optimization of design parameters, control programs and basic characteristics of the guided missile. The mathematical model of the guided missile provides adequate accuracy for design study to determine: overall dimensions and mass characteristics of the guided missile in general and its structural components and subsystems; power, thrust and consumption characteristics of the main engine; aerodynamic and ballistic characteristics of the guided missile. The developed methodology was tested by solving design problems. Applications of the developed program were studied to present the research results in a user-friendly form.

Key words: 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 object

Bibliography:

1. Degtyarev A. V. Rocket Engineering: Problems and Prospects. Selected scientific-technical publications. Dnepropetrovsk, 2014. 420 p.

2. Shcheverov D. N. Designing of Unmanned Aerial Vehicles. М., 1978. 264 p.

3. Sinyukov А. М. et al. Ballistic Solid-Propellant Rocket / Under the editorship of A. M. Sinyukov. М., 1972. 511 p.

4. Varfolomeyev V. I. Designing and Testing of Ballistic Rockets / Under the editorship of V. I. Varfolomeyev, M. I. Kopytov. М., 1970. 392 p.

5. Vinogradov V. A., Grushchansky V. A., Dovgodush S. I. et al. Effectiveness of Complex Systems. Dynamic Models. М., 1989. 285 p.

6. Il’ichyov A. V., Volkov V. D., Grushchansky V. A. Effectiveness of Designed Complex Systems’ Elements. М., 1982. 280 p.

7. Krotov V. F., Gurman V. I. Methods and Problems of Optimal Control. М., 1973. 446 p.

8. Pontryagin L. S. et al. Mathematical Theory of Optimal Processes. М., 1969. 385 p.

9. Tarasov E. V. Algorithms of Flying Vehicles Optimal Designing. М., 1970. 364 p.

10. Alpatov A. P., Sen’kin V. S. Complex Task of Optimization of Space Rocket Basic Design Parameters and Motion Control Programs. Technical Mechanics. 2011. No. 4. P. 98-113.

11. Alpatov A. P., Sen’kin V. S. Methodological Support for Selection of Launch Vehicle Configuration, Optimization of Design Parameters and Flight Control Programs. Technical Mechanics. 2013. No. 4. P. 146-161.

12. Sen’kin V. S. Optimization of Super-Light Launch Vehicle Design Parameters. Technical Mechanics. 2009. No. 1. P. 80-88.

13. Sen’kin V. S. Flight Control Optimization and Thrust Optimization of Controllable Rocket Object Main Propulsion System. Technical Mechanics. 2000. No. 1. P. 46-50.

14. Syutkina-Doronina S. V. On Problem of Optimization of Design Parameters and Control programs of a Rocket Object With Solid Rocket Motor. Aerospace Engineering and Technology. 2017. No. 2 (137). P. 44-59.

15. Lebedev А. А., Gerasyuta N. F. Rocket Ballistics. М., 1970. 244 p.

16. Razumov V. F., Kovalyov B. K. Design Basis of Solid-Propellant Ballistic Missiles. М., 1976. 356 p.

17. Yerokhin B. T. SRM Theoretical Design Basis. М., 1982. 206 p.

18. Abugov D. I., Bobylyov V. M. Theory and Calculation of Solid Rocket Motors. М., 1987. 272 p.

19. Shishkov А. А. Gas Dynamics of Powder Rocket Motors. М., 1974. 156 p.

20. Sen’kin V. S. Complex Task of Optimization of Super-Light Solid-Propellant Launch Vehicle Design Parameters and Control Programs. Technical Mechanics. 2012. No. 2. P. 106-121.

21. Methodological Support to Determine in Initial Designing Phase the Design Parameters, Control Programs, Ballistic, Power, and Mass-Dimensional Characteristics of Controllable Rocket Objects Moving In Aeroballistic Trajectory: R&D Report. ITM of NASU and SSAU, Yuzhnoye SDO. Inv. No. 40-09/2017. 2017. 159 p.

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