Search Results for “navigation system” – Collected book of scientific-technical articles https://journal.yuzhnoye.com Space technology. Missile armaments Tue, 30 Jun 2026 12:57:39 +0000 en-GB hourly 1 https://journal.yuzhnoye.com/wp-content/uploads/2020/11/logo_1.svg Search Results for “navigation system” – Collected book of scientific-technical articles https://journal.yuzhnoye.com 32 32 10.1.2024 METHOD OF AUTONOMOUS DETERMINATION OF THE ROCKET’S REFERENCE ATTITUDE DURING PRE-LAUNCH PROCESSING https://journal.yuzhnoye.com/content_2024_1-en/annot_10_1_2024-en/ Mon, 17 Jun 2024 08:44:04 +0000 https://journal.yuzhnoye.com/?page_id=35018
Gimballess inertial navigation system, built on the basis of inertial MEMS-sensors of Industry class (three angular velocity sensors and three accelerometers), is taken as the navigation device. In the classical version, the integration of data from angular velocity sensors and from accelerometers is the basis of gimballess inertial navigation system operation. Initial data, received from the gimballess inertial navigation system, is used as the output data. Key words: navigation system , mems-sensors , accelerometers , angular velocity sensors , reference attitude Bibliography: Meleshko V.V., Nesterenko O.I. navigation system , mems-sensors , accelerometers , angular velocity sensors , reference attitude .
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10. Method of autonomous determination of the rocket’s reference attitude during pre-launch processing

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Borscheva O. V., Khorolskiy P. G.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2024, (1); 85-92

DOI: https://doi.org/10.33136/stma2024.01.085

Language: Ukrainian

Annotation: To solve the navigation tasks (determination of the apparent accelerations and angular velocities and calculation of rocket orientation angles) in the rocket engineering, the data from the sensing elements (angular velocity sensors and accelerometers) is used. Accuracy of reference attitude determination of the rocket in the steady mode (at lift-off) has great influence on accuracy of the received navigation data during the flight. Gimballess inertial navigation system, built on the basis of inertial MEMS-sensors of Industry class (three angular velocity sensors and three accelerometers), is taken as the navigation device. In the classical version, the integration of data from angular velocity sensors and from accelerometers is the basis of gimballess inertial navigation system operation. It results in accumulation of errors when solving the navigation task (in particular due to the integration of data from angular velocity sensors). Taking it into consideration, the alternative method of rocket’s reference attitude determination during the pre-launch processing is offered. This method does not use mathematical operations of integration and is autonomous. Initial data, received from the gimballess inertial navigation system, is used as the output data. This data is used to determine the rocket’s reference attitude (orientation of object-centered coordinates in the geographical reference system) in the steady mode. Orientation angles are determined without the integration of data picked up from the angular velocity sensors. The comparative analysis to define the processing efficiency of the navigation device initial data was held during the determination of the rocket’s orientation angles in the steady mode, using the proposed method and Runge-Kutta method. The received results showed that accuracy of the reference attitude determination with the proposed method is higher. Thus, the proposed method will help reduce the errors in determination of the rocket’s reference attitude in the steady mode that in the future will improve the accuracy in determination of navigational parameters during the rocket’s flight.

Key words: navigation system, mems-sensors, accelerometers, angular velocity sensors, reference attitude

Bibliography:
  1. Meleshko V.V., Nesterenko O.I. Besplatformennye inertsialnye navigatsionnye systemy. Ucheb. posobie. Kirovograd: POLIMED – Service, 2011. 164 s.
  2. Vlasik S.N., Gerasimov S.V., Zhuravlyov A.A. Matematicheskaya model besplatformennoy inertsialnoy navigatsionnoy systemy i apparatury potrebitelya sputnikovoi navigatsionnoy systemy aeroballisticheskogo apparata. Nauka i technika Povitryannykh Sil Zbroinykh Sil Ukrainy. 2013. № 2(11). s. 166-169.
  3. Waldenmayer G.G. Protsedura pochatkovoi vystavki besplatformennoy inertsialnoy navigatsionoy systemy z vykorystannyam magnitometra ta rozshirennogo filtra Kalmana. Aeronavigatsini systemy. 2012. s. 8.
  4. Korolyov V.M., Luchuk Ye.V., Zaets Ya.G., Korolyova O.I., Miroshnichenko Yu.V. Analiz svitovykh tendentsiy rozvytku system navigatsii dlya sukhoputnykh viysk. Rozroblennya ta modernizatsia OVT. 2011. №1(4). s.19-29. https://doi.org/10.33577/2312-4458.4.2011.19-29
  5. Avrutov V.V., Ryzhkov L.M. Pro alternativniy metod avtonomnogo vyznachennya shyroty i dovgoty rukhomykh obiektiv. Mekhanika gyroskopichnykh system. 2021. №41. s.  122-131. https://doi.org/10.20535/0203-3771412021269255
  6. Bugayov D.V., Avrutov V.V., Nesterenko O.I. Experimentalne porivnyannya algoritmiv vyznachennya orientatsii na bazi complimentarnogo filtru ta filtru Madjvika. Avtomatizatsiya technologichnykh i biznes-protsesiv. 2020. T. 12, №3. s. 10-19.
  7. Chernyak M.G., Kolesnik V.O. Zmenshennya chasovykh pokhibok inertsialnogo vymiryuvalnogo modulya shlyakhom realizatsii yogo strukturnoi nadlyshkovosti na bazi tryvisnykh micromekhanichnykh vymiruvachiv. Mekhanika giroskopichnykh system. 2020. №39. s. 66-80. https://doi.org/10.20535/0203-3771392020229096
  8. Rudik A.V. Matematichna model pokhibok accelerometriv bezplatformenoi inertsialnoi navigatsinoi systemy. Visnyk Vynnitskogo politechnychnogo institutu. 2017. №2. s. 7-13.
  9. Naiko D.A., Shevchuk O.F. Teoriya iomovirnostey ta matematychna statistika: navch. posib. Vinnytsya: VNAU. 2020. 382 s.
  10. Matveev V.V., Raspopov V.Ya. Osnovy postroeniya bezplatformennykh inertsialnykh navigatsionnykh system. SPb.: GNTs RF OAO «Kontsern «TsNII «Electropribor». 2009. 280 s.
  11. Novatorskiy M.A. Algoritmy ta metody obchislen’ [Electronniy resurs]: navch. posib. dlya stud. KPI im. Igorya Sikorskogo. Kiyv: KPI im. Igorya Sikorskogo. 2019. 407 s.

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]]> 1.2.2019 Optimization of the trajectory of the antiaircraft guided missile https://journal.yuzhnoye.com/content_2019_2-en/annot_1_2_2019-en/ Sat, 16 Sep 2023 21:19:15 +0000 https://journal.yuzhnoye.com/?page_id=28723
Systemy obrobky informatsii. Systemy ozbroyennya i viyskova tekhnika. Optimal Planar Evasive Aircraft Maneuvers Against Proportional Navigation Missiles. Systemy samonavedeniya.
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1. Optimization of the trajectory of the antiaircraft guided missile

ISSN: 2617-5525

e-ISSN: 2617-5533

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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]]> 6.1.2018 On Building of Inertial Navigation System in the Condition of Presence of Considerable g-Load and Angular Velocity in Preferential Direction https://journal.yuzhnoye.com/content_2018_1-en/annot_6_1_2018-en/ Tue, 05 Sep 2023 06:19:12 +0000 https://journal.yuzhnoye.com/?page_id=30454
On Building of Inertial Navigation System in the Condition of Presence of Considerable g-Load and Angular Velocity in Preferential Direction ISSN: 2617-5525 e-ISSN: 2617-5533 Authors: Degtyareva O. quot;On Building of Inertial Navigation System in the Condition of Presence of Considerable g-Load and Angular Velocity in Preferential Direction," Космическая техника. On Building of Inertial Navigation System in the Condition of Presence of Considerable g-Load and Angular Velocity in Preferential Direction. (2018) On Building of Inertial Navigation System in the Condition of Presence of Considerable g-Load and Angular Velocity in Preferential Direction, Космическая техника. "On Building of Inertial Navigation System in the Condition of Presence of Considerable g-Load and Angular Velocity in Preferential Direction." Космическая техника. On Building of Inertial Navigation System in the Condition of Presence of Considerable g-Load and Angular Velocity in Preferential Direction.
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6. On Building of Inertial Navigation System in the Condition of Presence of Considerable g-Load and Angular Velocity in Preferential Direction

ISSN: 2617-5525

e-ISSN: 2617-5533

Authors:

Degtyareva O. А., Lapko O. M., Meleshko A. O., Chucha Y. V.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (1); 31-38

DOI: https://doi.org/10.33136/stma2018.01.031

Language: Russian

Annotation: The paper deals with the options of solving the task of constructing an inertial navigation system in the conditions of considerable g-load and angular velocity in identified direction by method of setting the sensitive elements at some angle to the identified direction, which allows making measurements in it without loss of measurement quality in the other directions. The paper describes the technique of calculating the angle of sensitive elements setting to the identified direction. The scheme of constructing an inertial navigation system with incomplete set of sensitive elements is considered for the cases when in entire operation leg, rotation around the identified direction is executed. The analysis is given of measurement vector error due to incompleteness of the sensitive elements set.

Key words:

Bibliography:
1. Shunkov V. N. Encyclopedia of Rocket Artillery / Under the general editorship of A. E. Taras. Minsk, 2004. 544 p.
2. Shirokorad A. B. Encyclopedia of National Artillery / Under the general editorship of A. E. Taras. Minsk: Harvest, 2000. 1156 p.
3. Pugachyov V. S. et al. Rocket Control System and Flight Dynamics / V. S. Pugachyov, I. E. Kazakov, D. I. Gladkov, L. G. Yevlanov, A. F. Mishakov, V. D. Sedov. М., 1965. 610 p.
4. Branets V. N., Shmyglevsky I. P. Use of Quaternions in Solid Body Orientation Problems. М., 1973. 320 p.
5. Borisova A. Y., Smal’ A. V. Analysis of Developments of Gimballess Inertial Navigation Systems. Engineering News. N. E. Bauman MGTU. No. 05. 2017.

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

ISSN: 2617-5525

e-ISSN: 2617-5533

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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]]> Сollected book of scientific-technical articles https://journal.yuzhnoye.com/ Thu, 04 May 2023 07:56:30 +0000 https://enovathemes.com/samatex2/?page_id=41
The scope of the Collection covers the development and operation of state-of-the-art military missile and space launch systems, spacecraft, and satellite systems, as well as their components, including: Design and development of missile and ground-based systems. Problems of efficiency, reliability, safety, and economic feasibility of space launch systems. Other aspects that are directly related to the development and operation of space launch systems.
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The collection of scientific and technical articles Space Technology. Missile Armaments is a specialized professional publication that publishes new results of theoretical and experimental research and development in the field of aviation and space rocket technology.

The subject area of the Collection corresponds to the Mechanical Engineering and Machine-Building cluster (G8 Materials Science, G9 Applied Mechanics, G10 Metallurgy, G11 Industrial Engineering, and G12 Aviation, Rocket, and Space Technology).

The scope of the Collection covers the development and operation of state-of-the-art military missile and space launch systems, spacecraft, and satellite systems, as well as their components, including:

  • Design and development of missile and ground-based systems.
  • Design and development of components of space launch vehicles and combat missiles (liquid-propellant and solid-propellant rocket engines, propulsion systems, control systems, separation systems, payload equipment, etc.)
  • Design and development of components for ground-based systems (facilities, fueling systems, prelaunch processing systems, etc.)
  • Design and development of spacecraft and their components.
  • Problems of aerodynamics, heat and mass transfer, flight theory, loading, and structural strength.
  • Problems of efficiency, reliability, safety, and economic feasibility of space launch systems.
  • Other aspects that are directly related to the development and operation of space launch systems.
  • Other topics corresponding to the Mechanical Engineering and Manufacturing

 

The target audience is scientists, postgraduate students, and specialists whose scientific interests include achievements in aviation, rocket, and space technology (G12) and other specialties within the Mechanical Engineering and Machine-Building cluster (G8, G9, G10, and G11).

The Collection is included in the List of Scientific Professional Publications of Ukraine (category B) in accordance with Order No. 928 of the Ministry of Education and Science, dated June 11, 2026 (Appendix 5).

The Collection is registered in the unified open scientific identification system ROR (Research Organization Registry).

The collection of scientific and technical articles Space Technology. Missile Armaments has been published since April 1979. It is currently published in printed (ISSN 2617-5525) and identical in content, full-text electronic forms (e-ISSN 2617 5533).

Publications in the Collection are provided free of charge for both authors and users (Diamond Open Access). No fees are charged to authors for the processing, peer review, or publication of the articles in the Collection or on its website.

About the collected articles

ISSN 2617-5525 (Print); e-ISSN 2617-5533 (Online)

obl1

ISSN 2617-5525 (Print);
e-ISSN 2617-5533 (Online)

Publisher and founder: Yuzhnoye State Design Office, EDRPOU code 14308304.

Publication DOI: 10.33136/stma

Publication languages: Ukrainian, English.

Periodicity: twice a year.
In 2023-2024, taking into account the announcement of martial law in Ukraine, the Collection was issued once a year.
In 2025, the editorial and publication process was stabilized, and the Collection resumed publication every six months.

State registration of the printed media in the National Council of Ukraine on Television and Radio Broadcasting: media identifier – R30-01817 of 04.12.2023.

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Google Scholar - Yuzhnoye State Design Office publications


OpenAlex - Yuzhnoye State Design Office publications


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ROR - Yuzhnoye State Design Office organization ID


Open Archives - Validate Site


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