Search Results for “spring” – Collected book of scientific-technical articles https://journal.yuzhnoye.com Space technology. Missile armaments Tue, 05 Nov 2024 20:24:28 +0000 en-GB hourly 1 https://journal.yuzhnoye.com/wp-content/uploads/2020/11/logo_1.svg Search Results for “spring” – Collected book of scientific-technical articles https://journal.yuzhnoye.com 32 32 7.1.2024 Selection of the functional units for the Cyclone-4M ILV separation system https://journal.yuzhnoye.com/content_2024_1-en/annot_7_1_2024-en/ Fri, 14 Jun 2024 11:36:31 +0000 https://journal.yuzhnoye.com/?page_id=34957
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. pneumatic pusher , spring pusher , SPRE , gas-reactive nozzles , Zenit LV , Dnepr LV , Falcon 9 rocket , Cyclone-4М LV. pneumatic pusher , spring pusher , SPRE , gas-reactive nozzles , Zenit LV , Dnepr LV , Falcon 9 rocket , Cyclone-4М LV.
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7. Selection of the functional units for the Cyclone-4M ILV separation system

Authors:

Logvinenko A. I., Makarenko A. O., Khomyak V. O., Olesiyuk A. A.

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:
  1. Pankratov Yu. , Novikov A. V., Tatarevsky K. E., Azanov I. B. Dynamika perekhodnykh processov. 2014.
  2. Sinyukov A. M., Morozov N. I. Konstruktsia upravlyaemykh ballisticheskykh raket. 1969.
  3. 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).
  4. Kolesnikov K. S., Kozlov V. V., Kokushkin V. V. Dynamika razdeleniya stupeney letatelnykh apparatov. 1977.
  5. 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).
  6. Falcon 9 – pexels: website. URL: https://www. pexels.com/Falcon 9 (data zvernennya 31.10.2023).
  7. Kolesnikov K. , Kokushkin V. V., Borzykh S. V., Pankova N. V. Raschet i proektirovanie system razdeleniya stupeney raket. 2006.
  8. Cyclone-4M – website URL: https://www.yuzhnote.com (data zvernennya 31.10.2023)
  9. Logvinenko A. Sozdanie gasoreaktivnykh system otdeleniya i uvoda otrabotavshykh stupeney – noviy shag v RKT. Kosmicheskaya tekhnika. Raketnoe vooruzhenie, KBU, NKAU, vyp. 1, 2001.
  10. 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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7.1.2024 Selection of the functional units for the Cyclone-4M ILV separation system
7.1.2024 Selection of the functional units for the Cyclone-4M ILV separation system
7.1.2024 Selection of the functional units for the Cyclone-4M ILV separation system

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]]> 13.1.2019 Prediction of Solid Propellant Burnout Time in Launch Vehicle Propulsion System in Flight https://journal.yuzhnoye.com/content_2019_1-en/annot_13_1_2019-en/ Wed, 24 May 2023 16:00:19 +0000 https://journal.yuzhnoye.com/?page_id=27718
– New York: Springer-Verlag New York, Inc., 2004.
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13. Prediction of Solid Propellant Burnout Time in Launch Vehicle Propulsion System in Flight

Authors:

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

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

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

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

Language: Russian

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

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

Bibliography:

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

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

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]]> 6.2.2019 Stabilization of gas reducers adjustment https://journal.yuzhnoye.com/content_2019_2-en/annot_6_2_2019-en/ Mon, 15 May 2023 15:45:44 +0000 https://journal.yuzhnoye.com/?page_id=27208
The brief review of the designs of liquid and bimetal thermal compensators is presented, their advantages and disadvantages are described and the experience of reducers testing with regulating springs made of elinvar is analyzed. Special attention is given to the properties of regulating spring of the reducer because of change of elasticity modulus coefficient at different temperatures, the expected pressure scatter at reducer output is evaluated and the necessity of measures to reduce this error is explained. Key words: parametric characteristic , spring , elasticity modulus , thermal compensator , pneumocorrection Bibliography: 1. parametric characteristic , spring , elasticity modulus , thermal compensator , pneumocorrection .
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6. Stabilization of gas reducers adjustment

Authors:

Nazarenko O. P., Reuta V. I., Makarov O. D.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (2); 42-49

DOI: https://doi.org/10.33136/stma2019.02.042

Language: Russian

Annotation: The general information on gas pressure reducers, on their purpose in launch vehicles and spacecraft pneumohydraulic systems is set forth. The impact of different operating conditions on physical characteristics of these devices is considered. The main and auxiliary parametric characteristics of the reducer are presented and the physical process of gas pressure reduction in it is explained. The error of output pressure regulation is evaluated using full differential of function, whose arguments (input pressure, flow rate, temperature) have scatter. The reducer temperature curve is shown and the impact of structural temperature on the value of dynamic (with flow rate) and static (without flow rate) pressure in reducer output cavity is explained. The difference between the excess pressure reducer and absolute pressure reducer is shown. The brief review of the designs of liquid and bimetal thermal compensators is presented, their advantages and disadvantages are described and the experience of reducers testing with regulating springs made of elinvar is analyzed. Attention is focused on operating temperature and its impact on stability of reducer adjustment. The formulas that describe thermodynamic processes occurring in the reducer are presented. Special attention is given to the properties of regulating spring of the reducer because of change of elasticity modulus coefficient at different temperatures, the expected pressure scatter at reducer output is evaluated and the necessity of measures to reduce this error is explained. To compensate for temperature disturbance, the formula of gas pressure in closed volume of sensitive element is derived. The essence of original technique of pneumocorrection of initial pressure in sensitive element cavity that was proposed and introduced on Yuzhnoye SDO-developed reducers is set forth.

Key words: parametric characteristic, spring, elasticity modulus, thermal compensator, pneumocorrection

Bibliography:
1. Nazarova L. M., Utkin V. F., Titov S. M., Liseenko Y. I., Prisnyakov V. F., Gorbachev A. D. Klapany bortovykh system strategicheskykh raket i kosmicheskykh apparatov/ pod red. acad. M. K. Yangelya. M., 1969. 358 s.
2. Yermilov V. A., Nesterenko Y. V., Nikolaev V. G. Gazovye reduktory. L., 1981. 176 s.
3. Vygodskiy M. Y. Spravochnik po vyshey matematike. M., 1958. 783 s.
4. Golubev M. D. Gazovye regulyatory davleniya / pod red. prof. G. I. Voronina. M., 1964. 152 s.
5. Edelman A. I. Reduktory davleniya gaza. M., 1980. 167 s. https://doi.org/10.1097/00000542-198002000-00014
6. Khomyakov A. N., Trashutin A. I., Naidenova L. P. Analiz tipov (skhemnykh resheniy) reduktorov davleniya: techn. otchet №711-222/76 / KBU. Dnepropetrovsk, 1976. 50 s.

 

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6.2.2019 Stabilization of gas reducers adjustment
6.2.2019 Stabilization of gas reducers adjustment
6.2.2019 Stabilization of gas reducers adjustment

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