Search Results for “acceleration” – 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 “acceleration” – 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
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.
]]>

10. Method of autonomous determination of the rocket’s reference attitude during pre-launch processing

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.

Full text (PDF) || Content 2024 (1)

Downloads: 14
Abstract views: 
808
Dynamics of article downloads
Dynamics of abstract views
Downloads geography
CountryCityDownloads
USA San Francisco; Clearwater; Chicago; Los Angeles; Buffalo; Los Angeles; Portland7
Germany Falkenstein; Falkenstein2
France1
Unknown1
China Shenzhen1
Singapore Singapore1
Ukraine Kremenchuk1
Downloads, views for all articles
Articles, downloads, views by all authors
Articles for all companies
Geography of downloads articles
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

Keywords cloud

Your browser doesn't support the HTML5 CANVAS tag.
]]> 12.1.2017 Static Performance Prediction of Hot-Gas Flapper-Nozzle Actuator https://journal.yuzhnoye.com/content_2017_1/annot_12_1_2017-en/ Fri, 22 Sep 2023 15:14:35 +0000 https://journal.yuzhnoye.com/?page_id=31702
Tutorial on the Theory of Electrohydraulic Servo Mechanism with Acceleration Control Operating in Switchover Mode.
]]>

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.

Full text (PDF) || Content 2017 (1)

Downloads: 33
Abstract views: 
829
Dynamics of article downloads
Dynamics of abstract views
Downloads geography
CountryCityDownloads
USA Boardman; Baltimore; Dublin; Ashburn; Columbus; Detroit; Phoenix; Phoenix; Phoenix; Monroe; Ashburn; Seattle; Ashburn; Seattle; Tappahannock; Portland; San Mateo; San Mateo; San Mateo; Des Moines; Boardman; Ashburn; Boardman23
Singapore Singapore; Singapore; Singapore; Singapore; Singapore; Singapore6
Ukraine Dnipro; Dnipro2
Germany Falkenstein1
Romania Voluntari1
Downloads, views for all articles
Articles, downloads, views by all authors
Articles for all companies
Geography of downloads articles
12.1.2017 Static Performance Prediction of Hot-Gas Flapper-Nozzle Actuator
12.1.2017 Static Performance Prediction of Hot-Gas Flapper-Nozzle Actuator
12.1.2017 Static Performance Prediction of Hot-Gas Flapper-Nozzle Actuator
]]> 23.2.2018 On the Role of Space in Origination of Inertia Force Field, Earth Gravity Force Field and Zero Gravity of Material Body https://journal.yuzhnoye.com/content_2018_2-en/annot_23_2_2018-en/ Thu, 07 Sep 2023 12:35:25 +0000 https://journal.yuzhnoye.com/?page_id=30813
Under the accelerated motion of the body reflection gains the acceleration vector dt d а   Value of the polarization vector equals the value of acceleration vector with negative sign. As a result metric lines of the configuration space under conditions of beam acceleration become polarized lines, generating vector information inertia field. And polarization vector is directed to the center of the Earth and equals acceleration vector of the free fall with the same sign.
]]>

23. On the Role of Space in Origination of Inertia Force Field, Earth Gravity Force Field and Zero Gravity of Material Body

Authors:

Muliar Yu. M., Fedorov V. M.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (2); 190-206

DOI: https://doi.org/10.33136/stma2018.02.190

Language: Russian

Annotation: Presented is the theoretical justification of the phenomenon of the inertia initiation under accelerated motion of the body, and gravity origin in the circumterrestrial space. There is no description of the physical nature of the inertia and gravity in the scientific publications. In the phenomenological approach under study, allowing for reflection properties of the space, earlier unknown interdependent information-physical link of the body and its mechanical particles with space under the accelerated motion was determined in the state of rest of the gravitation field as well as in the state of weightlessness. Alongside with the environment, eigenspace, i.e. configuration space of the body and corresponding metric lines of the space are considered. Idea of metric lines agrees with the concept of F. Wilczek, the American physicist, Nobel-Prize laureate, on the existence of the unobservable metric field in the real space. Solution of the problem rests on the example of the cantilever beam and mathematical model of the information reflection process, which for the first time takes into consideration previously unknown property of space reflection. Under the accelerated motion of the body reflection gains the acceleration vector dt d а     . In this case reflection manifests itself in the initiation of the beam of polarization vector under study   ~ in every point of the configuration space and is expressed as     ~ а . Value of the polarization vector equals the value of acceleration vector with negative sign. As a result metric lines of the configuration space under conditions of beam acceleration become polarized lines, generating vector information inertia field. Interaction of mechanical particles with the information inertia field in the configuration space generates physical inertia field of force, providing the real inertia under accelerated motion of the beam. (Relatively slow motion of bodies is studied as compared to the speed of light). According to the set forth unconventional approach the nature of the earth gravity is conditioned by the polarization of the radial metric lines of the circumterrestrial space. And polarization vector is directed to the center of the Earth and equals acceleration vector of the free fall with the same sign. Interaction of the body with specific mass with the vector information field of the Earth generates the physical force field of gravity. Article deals with the fundamental issues of theoretical physics and other fields of natural science. Materials of the conducted research are regarded as a potential scientific discovery.

Key words: configuration space, modified method of sections, information and vacuum environment, metric lines, property of space reflection, polarization, scalar information field, vector information field

Bibliography:
1. Vilchek F. Fine Physics. Mass, Ester and Unification of World Forces. Collection of publications, 2018. 336 p.
2. Sivukhin D. V. General Course of Physics. Vol. 1. М., 1989. 576 p.
3. Logunov А. А. Lectures on Relativity Theory and Gravitation. Modern Analysis of Problem. М., 1987. 272 p.
4. Feinman R., Layton R., Sands M. Feinman Lectures in Physics. Vol. 1. Modern Natural Science. The Laws of Mechanics. Vol. 2. Space. Time. Motion / Translation from English. М., 1976. 439 p.
5. Mulyar Y. M. On Stability of Compressed Rod. Technical mechanics. Dnepropetrovsk, 2000. No. 2. P. 51-57.
6. Mulyar Y. M., Perlik V. I. On Mathematical Model Representation of Information Field in Loaded Deformed System. Information and Telecommunication Technologies. М., 2012. No. 15. P. 61-74.
7. Vernadsky V. I. Reflections of Natural Scientist. Space and Time in Inanimate and Animate Nature. М., 1975. 173 p.
8. Ursul A. D. Reflection and Information. М., 1973. 231 p.
9. Vladimirov Y. S. Metaphysics. М., 2002. 550 p.
10. Author’s Certificate 181066 USSR. Energy Absorber / А. М. Buyanovsky, Y. М. Mulyar. Discoveries. Inventions. 1993. No. 15. P. 101.
11. Cacku M. Physics of Impossible / Translation from English. М., 2016. 456 p.
12. Proceedings of the International Scientific Conference “Problems of Ideality in Science”. М., 2001. 352 p.
13. Mulyar Y. M., Fyodorov V. M., Tryasuchev L. M. On the Impact of Initial Imperfections on Rod Stability Loss in Conditions of Axial Compression. Space Technology. Missile Armaments: Collection of scientific-technical articles. 2017. Issue 1 (113). P. 48-58.
14. Dyomin A.I. Paradigm of Dualism. Space – Time, information – energy. М., 2007. 320 p.
15. Lisin A.I. Paradigm of Dualism. Ide: Reality of ideality. Part 1. М., 1999. 382 p.

Full text (PDF) || Content 2018 (2)

Downloads: 39
Abstract views: 
1300
Dynamics of article downloads
Dynamics of abstract views
Downloads geography
CountryCityDownloads
USA Boardman; Matawan; Baltimore; Boydton; Plano; Miami; Phoenix; Phoenix; Monroe; Ashburn; Seattle; Seattle; Columbus; Columbus; Ashburn; Seattle; Seattle; Portland; San Mateo; Des Moines; Boardman; Ashburn; Seattle23
Singapore Singapore; Singapore; Singapore; Singapore; Singapore; Singapore6
Unknown;2
India1
Finland Helsinki1
France1
Canada Monreale1
Germany Falkenstein1
Romania Voluntari1
Netherlands Amsterdam1
Ukraine Dnipro1
Downloads, views for all articles
Articles, downloads, views by all authors
Articles for all companies
Geography of downloads articles
23.2.2018 On the Role of Space in Origination of Inertia Force Field, Earth Gravity Force Field and Zero Gravity of Material Body
23.2.2018 On the Role of Space in Origination of Inertia Force Field, Earth Gravity Force Field and Zero Gravity of Material Body
23.2.2018 On the Role of Space in Origination of Inertia Force Field, Earth Gravity Force Field and Zero Gravity of Material Body

Keywords cloud

Your browser doesn't support the HTML5 CANVAS tag.
]]> 4.1.2018 Determination of Angular Acceleration of Rotary Elements of Rocket Systems during Ground Tests https://journal.yuzhnoye.com/content_2018_1-en/annot_4_1_2018-en/ Mon, 04 Sep 2023 13:20:27 +0000 https://journal.yuzhnoye.com/?page_id=30411
Determination of Angular Acceleration of Rotary Elements of Rocket Systems during Ground Tests Authors: Zavialov P. 2018 (1); 20-26 DOI: https://doi.org/10.33136/stma2018.01.020 Language: Russian Annotation: The paper considers the task of determination of angular acceleration of rotary elements of rocket systems during ground tests, which, at the composition of meters ensuring simple enough measurement system embodiment, is poorly conditioned. (2018) "Determination of Angular Acceleration of Rotary Elements of Rocket Systems during Ground Tests" Космическая техника. "Determination of Angular Acceleration of Rotary Elements of Rocket Systems during Ground Tests" Космическая техника. quot;Determination of Angular Acceleration of Rotary Elements of Rocket Systems during Ground Tests", Космическая техника. Determination of Angular Acceleration of Rotary Elements of Rocket Systems during Ground Tests Автори: Zavialov P.
]]>

4. Determination of Angular Acceleration of Rotary Elements of Rocket Systems during Ground Tests

Authors:

Zavialov P. P., Shatov O. А.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (1); 20-26

DOI: https://doi.org/10.33136/stma2018.01.020

Language: Russian

Annotation: The paper considers the task of determination of angular acceleration of rotary elements of rocket systems during ground tests, which, at the composition of meters ensuring simple enough measurement system embodiment, is poorly conditioned. The technique of its solution is presented.

Key words:

Bibliography:
1. Amosov А. А., Dubinsky Y. A., Kopchenova N. V. Computational Methods for Engineers: Tutorial. М., 1994. 554 p.
2. Tikhonov A. N., Arsenin V. Y. Methods to Solve Incorrect Problems. М., 1979.

Full text (PDF) || Content 2018 (1)

Downloads: 40
Abstract views: 
465
Dynamics of article downloads
Dynamics of abstract views
Downloads geography
CountryCityDownloads
USA Boardman; Matawan; Baltimore; Plano; Columbus; Phoenix; Los Angeles; Monroe; Ashburn; Seattle; Seattle; Ashburn; Boardman; Seattle; Seattle; Tappahannock; Portland; San Mateo; San Mateo; San Mateo; Des Moines; Boardman; Ashburn; Boardman24
Singapore Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore7
Finland Helsinki1
Unknown1
Canada Monreale1
Pakistan Karachi1
Germany Falkenstein1
Romania Voluntari1
Netherlands Amsterdam1
Russia Moscow1
Ukraine Dnipro1
Downloads, views for all articles
Articles, downloads, views by all authors
Articles for all companies
Geography of downloads articles
4.1.2018 Determination of Angular Acceleration of Rotary Elements of Rocket Systems during Ground Tests
4.1.2018 Determination of Angular Acceleration of Rotary Elements of Rocket Systems during Ground Tests
4.1.2018 Determination of Angular Acceleration of Rotary Elements of Rocket Systems during Ground Tests
]]> 9.2.2016 Metrological Support of Kinematic Model Testing on Zero-Gravity Test Stands https://journal.yuzhnoye.com/content_2016_2-en/annot_9_2_2016-en/ Tue, 06 Jun 2023 11:56:39 +0000 https://journal.yuzhnoye.com/?page_id=28319
2016 (2); 60-64 Language: Russian Annotation: Example of the estimate of the measurement error of the linear accelerations during the free fall of the kinematic model is considered.
]]>

9. Metrological Support of Kinematic Model Testing on Zero-Gravity Test Stands

Authors:

Bondar’ М. А., Yeres L. O., Kurako I. М., Petrenko Y. M., Goltsev O. S.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2016 (2); 60-64

Language: Russian

Annotation: Example of the estimate of the measurement error of the linear accelerations during the free fall of the kinematic model is considered. It was concluded that experiments on error measurements can be replaced with calculations for those parameters which have sufficient initial data on metrological performance of the applied instrumentation.

Key words:

Bibliography:

Full text (PDF) || Content 2016 (2)

Downloads: 42
Abstract views: 
448
Dynamics of article downloads
Dynamics of abstract views
Downloads geography
CountryCityDownloads
USA Boardman; Matawan; Baltimore; Plano; Phoenix; Monroe; Ashburn; Seattle; Seattle; Columbus; Ashburn; Boardman; Seattle; Seattle; Tappahannock; Portland; San Mateo; Des Moines; Des Moines; Boardman; Boardman; Ashburn; Ashburn23
Singapore Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore9
Germany; Falkenstein2
Ukraine Dnipro; Dnipro2
Finland Helsinki1
Unknown1
France1
Mongolia1
Canada Monreale1
Romania Voluntari1
Downloads, views for all articles
Articles, downloads, views by all authors
Articles for all companies
Geography of downloads articles
9.2.2016 Metrological Support of Kinematic Model Testing on Zero-Gravity Test Stands
9.2.2016 Metrological Support of Kinematic Model Testing on Zero-Gravity Test Stands
9.2.2016 Metrological Support of Kinematic Model Testing on Zero-Gravity Test Stands
]]> 22.1.2019 Calculation of Uncertainty of Represented Values of Linear Accelerations during Centrifugal Machines Certification https://journal.yuzhnoye.com/content_2019_1-en/annot_22_1_2019-en/ Wed, 24 May 2023 16:00:54 +0000 https://journal.yuzhnoye.com/?page_id=27727
Calculation of Uncertainty of Represented Values of Linear Accelerations during Centrifugal Machines Certification Authors: Bondar’ М. This article offers the methodology for uncertainty calculation when certificating a centrifugal machine that is used to reproduce precisely the given value of linear acceleration that permanently acts on a tested unit spinning together with a rotor. The offered methodology for uncertainty calculation is applicable to centrifugal machines, for which numerical values of reproducible linear acceleration are determined by results of calculations of the centrifugal machine’s rotor angular velocity and radial distance from rotor’s longitudinal axis to the given point of the tested unit. The calculation given in the article estimates the limit of linear accelerations that can be attributed with established probability to the given value of linear acceleration reproduced when certificating the centrifugal machine.
]]>

22. Calculation of Uncertainty of Represented Values of Linear Accelerations during Centrifugal Machines Certification

Authors:

Bondar’ М. А., Voloshina M. O., Yeres L. O., Kurako I. М., Morozov O. D.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (1); 149-153

DOI: https://doi.org/10.33136/stma2019.01.149

Language: Russian

Annotation: Applicable documents on metrological assurance regulate the estimation of measurement uncertainty. In Ukraine there is no regulative methodology for uncertainty calculation when certificating test equipment that causes the necessity of its definition. This article offers the methodology for uncertainty calculation when certificating a centrifugal machine that is used to reproduce precisely the given value of linear acceleration that permanently acts on a tested unit spinning together with a rotor. The offered methodology for uncertainty calculation is applicable to centrifugal machines, for which numerical values of reproducible linear acceleration are determined by results of calculations of the centrifugal machine’s rotor angular velocity and radial distance from rotor’s longitudinal axis to the given point of the tested unit. Initial data used were results of observation obtained after multiple reproductions of the given values of linear acceleration as well as numerical values of errors and measurement uncertainties of measuring equipment that was used when monitoring the rotary angular velocity and radial distance considering the contribution of each measurable parameter to a certain value of linear acceleration. The calculation given in the article estimates the limit of linear accelerations that can be attributed with established probability to the given value of linear acceleration reproduced when certificating the centrifugal machine. The design formulae are given to estimate the uncertainty components of the reproducible values of linear accelerations and the recommendations are given to present the uncertainty budget.

Key words: extended uncertainty, standard uncertainty, sensitivity coefficient, measurement uncertainty contribution, frequency meter

Bibliography:
1. GOST 24555. Poryadok attestatsii ispytatelnogo oborudovania. Osnovnye polozheniya. Vved. 27.01.81. M.: Gosstandart, 1982. 12 p.
2. https://www.twirpx.com/file/1791976.
3. Guide to the Expression of Uncertainty in Measurement: ISO. Geneva, 1993. 101 p.
4. Zakon Ukrainy «Pro metrologiu ta metrologychnu diyalnist’»// Vidom. Verkhovnoi Rady (VVR). 2014. № 30. P.1008.
5. Duplischeva O. M. i dr. Experimentalnaya otrabotka agregatov avtomatiki I system letatelnykh apparatov/ Pod obsch. red. d. t. n. A. V. Degtyareva. Dnepropetrovsk: GP KB «Yuzhnoye» im. M. K. Yangelya», 2013. 208 p.
6. Bondar’ M. A. i dr. Metodologia otsenivania neopredelennosti izmerenniy pri provedenii attestatsii sredstv izmeritelnoi techniki//Kosmicheskaya technika. Raketnoe vooruzhenie: Sb. nauch. – techn. st. 2017. Vyp. 1. P. 3–7.

Full text (PDF) || Content 2019 (1)

Downloads: 33
Abstract views: 
614
Dynamics of article downloads
Dynamics of abstract views
Downloads geography
CountryCityDownloads
USA Boardman; Ashburn; Baltimore;; Los Angeles; Plano; Monroe; Seattle; Columbus; Ashburn; Seattle; Seattle; Tappahannock; Portland; San Mateo; Des Moines; Boardman; Boardman; Ashburn; Boardman20
Singapore Singapore; Singapore; Singapore; Singapore; Singapore; Singapore6
Belgium Brussels; Brussels2
Philippines Olongapo City1
Germany Falkenstein1
Romania Voluntari1
Netherlands Amsterdam1
Ukraine Dnipro1
Downloads, views for all articles
Articles, downloads, views by all authors
Articles for all companies
Geography of downloads articles
22.1.2019 Calculation of Uncertainty of Represented Values of Linear Accelerations during Centrifugal Machines Certification
22.1.2019 Calculation of Uncertainty of Represented Values of Linear Accelerations during Centrifugal Machines Certification
22.1.2019 Calculation of Uncertainty of Represented Values of Linear Accelerations during Centrifugal Machines Certification

Keywords cloud

Your browser doesn't support the HTML5 CANVAS tag.
]]> 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. 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. 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.
]]>

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

Full text (PDF) || Content 2019 (1)

Downloads: 40
Abstract views: 
691
Dynamics of article downloads
Dynamics of abstract views
Downloads geography
CountryCityDownloads
USA Boardman; Matawan; North Bergen; Plano; Columbus; Phoenix; Phoenix; Phoenix; Monroe; Ashburn; Seattle; Ashburn; Ashburn; Seattle; Tappahannock; Portland; San Mateo; San Mateo; Des Moines; Boardman; Ashburn21
Singapore Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore9
Great Britain London; London2
Finland Helsinki1
Ethiopia Addis Ababa1
Mongolia1
Canada Monreale1
Germany Falkenstein1
Romania Voluntari1
Netherlands Amsterdam1
Ukraine Dnipro1
Downloads, views for all articles
Articles, downloads, views by all authors
Articles for all companies
Geography of downloads articles
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

Keywords cloud

Your browser doesn't support the HTML5 CANVAS tag.
]]> 12.1.2019 Monitoring of Launch Platform Drift Parameters during Zenit-3SL Integrated Launch Vehicle Prelauch Processing https://journal.yuzhnoye.com/content_2019_1-en/annot_12_1_2019-en/ Wed, 24 May 2023 16:00:15 +0000 https://journal.yuzhnoye.com/?page_id=27717
maximum acceleration of platform drift – no more than ±0,05 m/s2; •  The article includes the computation algorithm of the platform drift parametres to calculate velocity and acceleration of the drift, as well as distance from the design launch point to the actual point of the platform location. Key words: Sea Launch , latitude , longitude , algorithm , velocity , acceleration Bibliography: Full text (PDF) || Sea Launch , latitude , longitude , algorithm , velocity , acceleration .
]]>

12. Monitoring of Launch Platform Drift Parameters during Zenit-3SL Integrated Launch Vehicle Prelauch Processing

Authors:

Stetsenko V. Y., Davydenko S. O.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (1); 81-86

DOI: https://doi.org/10.33136/stma2019.01.082

Language: Russian

Annotation: Under the Sea Launch program when developer of the Zenit-3SL ILV control system issued the permission to launch in the conditions of drift from the design launch point of the Odyssey launch platform, the problem of drift parameters monitoring at the Sea Launch Commander ACS appeared. To ensure the payload orbiting accuracy the following maximum permissible values of platform drift parametres were determined: • maximum velocity of platform drift – no more than 0,32 m/s; • maximum acceleration of platform drift – no more than ±0,05 m/s2; • maximum distance of platform drift from design launch point – no more than 1950 m. The article includes the computation algorithm of the platform drift parametres to calculate velocity and acceleration of the drift, as well as distance from the design launch point to the actual point of the platform location. Geographical coordinates – latitude and longitude of the platform according to the GPS sensor, installed on the platform are used for calculations. These values during prelaunch processing of the ILV are transmitted to the assembly and command ship’s workstation for calculation of loads in the ILV root section at the rate of once in a second. During one of the Sea Launch missions, C++ program was developed and installed on the loads calculation workstation, realizing the computation algorithm offered by the authors of this article. This program displayed in real time the monitored parametres of the platform drift, and monitored the tolerable limits. During the same mission, the correctness of the developed algorithm and program were confirmed during the special experiment on the launch platform drift in the launch point. In future, they were used during the subsequent missions of the Sea Launch program.

Key words: Sea Launch, latitude, longitude, algorithm, velocity, acceleration

Bibliography:

Full text (PDF) || Content 2019 (1)

Downloads: 39
Abstract views: 
738
Dynamics of article downloads
Dynamics of abstract views
Downloads geography
CountryCityDownloads
USA Ashburn; Springfield; Baltimore; Plano; Phoenix;; Monroe; Ashburn; Seattle; Seattle; Seattle; Ashburn; Ashburn; Seattle; Tappahannock; Portland; San Mateo; San Mateo; San Mateo; Des Moines; Boardman; Boardman; Ashburn; Boardman24
Singapore Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore8
Unknown; Hong Kong2
Belgium Brussels1
Germany Falkenstein1
Romania Voluntari1
Netherlands Amsterdam1
Ukraine Dnipro1
Downloads, views for all articles
Articles, downloads, views by all authors
Articles for all companies
Geography of downloads articles
12.1.2019 Monitoring of Launch Platform Drift Parameters during Zenit-3SL Integrated Launch Vehicle Prelauch Processing
12.1.2019 Monitoring of Launch Platform Drift Parameters during Zenit-3SL Integrated Launch Vehicle Prelauch Processing
12.1.2019 Monitoring of Launch Platform Drift Parameters during Zenit-3SL Integrated Launch Vehicle Prelauch Processing

Keywords cloud

Your browser doesn't support the HTML5 CANVAS tag.
]]> 5.2.2019 Features of the development testing of the propellants deposition inside the tanks of launch vehicles https://journal.yuzhnoye.com/content_2019_2-en/annot_5_2_2019-en/ Mon, 15 May 2023 15:45:40 +0000 https://journal.yuzhnoye.com/?page_id=27207
The propellant is moved to the supply lines by way of creating longitudinal acceleration which is done using inertial continuity ensuring means (thrusters). Motion of liquid-vapor interface in response to imposed acceleration.
]]>

5. Features of the development testing of the propellants deposition inside the tanks of launch vehicles

Authors:

Sedykh I. V., Nazarenko D. S., Smolenskyi D. E.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (2); 35-41

DOI: https://doi.org/10.33136/stma2019.02.035

Language: Russian

Annotation: When accomplishing the task of spacecraft orbital injection, the necessity arises of main engine multiple ignitions and consequently, long pauses between the ignitions are possible. As the propellant during pauses between ignitions is in the conditions of practically full absence of gravitation and can freely move over entire tank volume taking practically any spatial position, to ensure main engine guaranteed ignition the necessity arises to move the propellant into pre-start position. The propellant is moved to the supply lines by way of creating longitudinal acceleration which is done using inertial continuity ensuring means (thrusters). The time of full liquid displacement from one position into another is the most important parameter having an impact on propellant amount in the tanks and accordingly, on power characteristics of a stage. The theoretical calculations of hydrodynamic processes are connected with considerable mathematical difficulties caused by complexity of solving hydrodynamic problems of determination of liquid flowing with free surface taking into account surface tension of the liquid and many other geometrical, kinematic, and dynamic factors. Therefore, the most reliable data from solving these problems are currently obtained only on model hydrodynamic stands where it is possible to model liquid behavior in tanks in the conditions of variable gravitation. The paper presents the authors-developed procedure of calculating the full time required for propellant components deposition during rocket’s apogee stage flight and the procedure of selecting the modeling parameters (scale, time, and acсeleration) to ensure development testing in the conditions of limited test stand base. The use of the proposed procedure allows (in initial phase of launch vehicle development) determining the full time required to perform deposition with sufficient accuracy and thus optimizing the propellant mass required for operation of inertial continuity ensuring system, which in its turn, will allow increasing the payload mass to be injected.

Key words: propellant deposition, zero-gravity stand, hydrodynamic similarity, damping and separation

Bibliography:
1. Masica W. J., Petrash D. A. Motion of liquid-vapor interface in response to imposed acceleration. Lewis Research Center. NASA TN D-3005. 1965. 24 р.
2. Masica W. J., Petrash D. A., Otto E. W. Hydrostatic stability of liquid-vapor interface in the gravitational field. Lewis Research Center. NASA TN D-2267. 1964. 18 р.
3. Glyuk D. F., Jill D. P. Hydromechanika podachi topliva v dvigatelnoy systeme kosmicheskogo korablya v sostoyanii nevesomosti. Konstruirovanie i technologiya machinostroeniya. 1965. T. 87. S. 1–10.
4. Birdge G. V., Blackmon J. B. et al. Analiticheskiy podkhod k proektirovaniyusystem povtornoy zapravke na orbite. Sbornik perevodov. GONTI-4. 1970. S. 56–111.
5. Woss D. E., Hattis P. D. Problema upravleniya istecheniem v processe zapravki bakov Space Shuttle zhidkimi komponentami na okolozemnoy orbite. Astronavtika i raketodynamika. 1986. № 7. S. 8–19.
6. Sedykh I. V., Smolenskiy D. E. Eksperimentalnoe podtverzhdenie rabotosposobnosti capillyrnogo zabornogo ustroistva pri otdelenii kosmicheskogo apparata. Mekhanika gyroskopicheskikh system. 2017. № 33. S. 105–114.
7. Sedykh I. V., Smolenskiy D. E., Nazarenko D. S. Eksperimentalnoe podtverzhdenie rabotosposobnosti capillyrnogo zabornogo ustroistva (setchatogo razdelitelya) pri programmnom razvorote. Visn. Dnipr. un-tu. Ser.: Raketno-kosmichna tekhnika. 2018. Vyp. 21. T. 26. S. 112–119.
8. Garkusha V. A., Shevchenko B. A., Rada N. A., Prilukova L. V. Eksperimentalnaya otrabotka sredstv obespecheniya sploshnosti komponentov topliva kosmicheskykh letatelnykh apparatov: Obzor po materialam otkrytoy zarubezhnoy pechati za 1963–1983. Seria UP. № 235. GONTI-3. 1984. 38 s.

Full text (PDF) || Content 2019 (2)

Downloads: 43
Abstract views: 
638
Dynamics of article downloads
Dynamics of abstract views
Downloads geography
CountryCityDownloads
USA Boardman; Matawan; Baltimore; Plano; Dublin; Ashburn; Detroit; Phoenix; Phoenix; Phoenix; Monroe; Ashburn; Seattle; Seattle; Ashburn; Boardman; Seattle; Tappahannock; San Mateo; San Mateo; San Mateo; Des Moines; Boardman; Boardman; Ashburn25
Singapore Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore; Singapore9
Ukraine Dnipro; Dnipro2
Philippines1
Finland Helsinki1
Canada Monreale1
France Strasbourg1
Germany Falkenstein1
Romania Voluntari1
Netherlands Amsterdam1
Downloads, views for all articles
Articles, downloads, views by all authors
Articles for all companies
Geography of downloads articles
5.2.2019 Features of the development testing of the propellants deposition inside the tanks of launch vehicles
5.2.2019 Features of the development testing of the propellants deposition inside the tanks of launch vehicles
5.2.2019 Features of the development testing of the propellants deposition inside the tanks of launch vehicles

Keywords cloud

Your browser doesn't support the HTML5 CANVAS tag.
]]>