Search Results for “Ryzhko O. V.” – Collected book of scientific-technical articles https://journal.yuzhnoye.com Space technology. Missile armaments Tue, 05 Nov 2024 21:17:59 +0000 en-GB hourly 1 https://journal.yuzhnoye.com/wp-content/uploads/2020/11/logo_1.svg Search Results for “Ryzhko O. V.” – 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
https://doi.org/10.33577/2312-4458.4.2011.19-29 Avrutov V.V., Ryzhkov L.M.
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10. Method of autonomous determination of the rocket’s reference attitude during pre-launch processing

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

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

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

Language: Ukrainian

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

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

Bibliography:
  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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10.1.2024 METHOD OF AUTONOMOUS DETERMINATION OF THE ROCKET’S REFERENCE ATTITUDE DURING PRE-LAUNCH PROCESSING
10.1.2024 METHOD OF AUTONOMOUS DETERMINATION OF THE ROCKET’S REFERENCE ATTITUDE DURING PRE-LAUNCH PROCESSING
10.1.2024 METHOD OF AUTONOMOUS DETERMINATION OF THE ROCKET’S REFERENCE ATTITUDE DURING PRE-LAUNCH PROCESSING

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11.2.2018 Some Peculiarities of Ensuring LRE Guarantied Service Life in the Conditions of Replacement of Components of Interindustry Application https://journal.yuzhnoye.com/content_2018_2-en/annot_11_2_2018-en/ Thu, 07 Sep 2023 11:32:42 +0000 https://journal.yuzhnoye.com/?page_id=30768
, Ryzhko O. vooruž. The content of works is considered to seek for and introduce new components of inter-industry application, in particular, replacing materials for rubber mixtures during production of rubber technical goods, polymer materials (fluoroplastics, polyamides), isotropic pyrographite, ozone friendly means for degreasing liquid rocket engine assemblies being in contact with propellant componentoxygen and to seek for alternative bearings. Shaposhnikov V. A., Ryzhko O. A., Ryzhko O. Missile armaments, vol. A., Ryzhko O. A., Ryzhko O. A., Ryzhko O. A., Ryzhko O. isotropic pyrographite , accelerated environmental tests , fluoroplastic , equivalent storage temperature , activation energy .
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11. Some Peculiarities of Ensuring LRE Guarantied Service Life in the Conditions of Replacement of Components of Interindustry Application

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (2); 94-100

DOI: https://doi.org/10.33136/stma2018.02.094

Language: Russian

Annotation: The article considers the present-day aspects of predicting and establishing the guaranteed service life of liquid rocket engines. The phases and sequence of works to specify the guarantee periods are presented. The physical ground for determining thermal ageing test modes and increased humidity test modes is set forth. The mathematical dependencies are given to determine the time of testing at increased temperature, increased relative humidity, equivalent article storage temperature. The generalized list and sequence of tests to establish a guarantee period are set forth. The content of works is considered to seek for and introduce new components of inter-industry application, in particular, replacing materials for rubber mixtures during production of rubber technical goods, polymer materials (fluoroplastics, polyamides), isotropic pyrographite, ozone friendly means for degreasing liquid rocket engine assemblies being in contact with propellant component – oxygen and to seek for alternative bearings.

Key words: isotropic pyrographite, accelerated environmental tests, fluoroplastic, equivalent storage temperature, activation energy

Bibliography:
1. Vasilina V. G. et al. Autonomous Development Testing of LRPS Pneumohydraulic Supply Systems and Units. Kharkiv, 2005. 113 p.
2. Shaposhnikov V. A., Utkin V. F., Belyayev N. M. Evaluation of Rockets Guaranteed Service Life. М., 1967. 164 p.
3. GOST 9.707-81. Unified System of Corrosion and Ageing Protection. Polymer Materials. Methods of Accelerated Climatic Ageing Tests. М., 1990. 79 p.
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11.2.2018 Some Peculiarities of Ensuring LRE Guarantied Service Life in the Conditions of Replacement of Components of Interindustry Application
11.2.2018 Some Peculiarities of Ensuring LRE Guarantied Service Life in the Conditions of Replacement of Components of Interindustry Application
11.2.2018 Some Peculiarities of Ensuring LRE Guarantied Service Life in the Conditions of Replacement of Components of Interindustry Application

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