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

8.1.2020 Determining the main parameters of transport aircraft modifications considering the fuel efficiency

Вацлав Самусевич — Wed, 13 Sep 2023 10:34:58 +0000

8. Determining the main parameters of transport aircraft modifications considering the fuel efficiency

Authors:

Los’ O. V.

Organization:

Antоnov Company, Kyiv, Ukraine

Page: Kosm. teh. Raket. vooruž. 2020, (1); 85-89

DOI: https://doi.org/10.33136/stma2020.01.085

Language: Russian

Annotation: The main parameters are understood as: carrying capacity mг, range L and fuel efficiency qт, which largely determine the competitiveness of aircraft of this type, including military transport aircraft. The reason for the creation of modifications of transport category aircraft is the requirement for a constant increase in their flight performance by increasing the carrying capacity and range. Among the main goals of implementing such decisions there is an indispensable increase in the fuel efficiency of modifications, since the cost of fuel reaches 80 % of the cost of an airplane hour during operation. There are a number of models that make it possible to assess the influence of the weight and aerodynamic parameters of the airframe of the aircraft and the fuel performance of the power plant (specific engine consumption) on the integral indicator of the fuel efficiency of the modification at cruising mode and the average hourly fuel consumption at the certification stage, when all parameters of the airframe and engine are fixed and consideration of options is not possible. A new model is proposed for the stage of designing modifications, in which deep modification changes are made in the geometry of wing and in the power plant with various variants of their correlation and coordination. The parameters of new model: specific fuel efficiency – specific route productivity, in order to form the relative carrying capacity and relative range of action for the required specific fuel efficiency. An analysis of such dependencies showed: – with an increase in relative range L , fuel costs per flight also increase; – the adequacy of changes in route performance is observed only at L < 0.5. At L > 0.5 productivity is constantly decreasing, while the specific indicator of fuel consumption per unit of work increases exponentially; – if in the analysis we take into account the specific value of transport efficiency, that is, the characteristic “load – range” ( mп.н  f L ), it becomes obvious that the most favorable (from the point of view of fuel efficiency) are relative ranges of 0,3 < L < 0,5. In this range L , not only acceptable fuel efficiency values are realized, but also the maximum value of the route performance, that is the main parameters for which modifications are developed.

Key words: productivity, carrying capacity, fuel efficiency, parameter formation

Bibliography:

1. Balabuev P. V. Osnovy obshchego proektirovaniia samoletov s gazoturbinnymi dvigateliami. Kharkiv, 2003. Ch. 2. 389 s.

2. Yugov О. K. Soglasovanie kharakteristik samoleta i dvigatelia. 1975. 204 s.; 2-е izd., 1980. 200 s.

3. Korol’ V. N. Kontseptsiia sozdaniia mezhdunarodnogo konsortsiuma “Srednii transportnyi samolet”. Voprosy proektirovaniia i proizvodstva konstruktsii letalelnykh apparatov. Kharkiv, 2002. Vyp. 30(3). S. 6-27.

4. Global Market Forecast. Future Journeys 2013 – 2020 / AIRBUS S.A.S Blagnac Cedex: Art @ Caractere, 2013. 125 p. [electronic resource]. Access mode: http://www.airbus.com/company/market/forecast/elD=dam.

5. 747-400 Freighter Main deck cargo arrangements. Boeing, 2010 10 p. [electronic resource]. Access mode: http://www.boeing.com.

6. 6. ICAO. 3.2bn passengers used air transport in 2014. [electronic resource]. Access mode: http://www.aviatime.com/-en/airports/airports-news.

7. An-188. Srednii voenno-ttansportnyi samolet ukorochennogo vzleta i posadki. Kyiv, 2018. S. 118.

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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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16.1.2018 Some Correlation Dependences in Families of Aton and Apollo and Rendezvous Frequency in Main Asteroid Belt

Вацлав Самусевич — Tue, 05 Sep 2023 07:10:09 +0000

16. Some Correlation Dependences in Families of Aton and Apollo and Rendezvous Frequency in Main Asteroid Belt

Authors:

Usichenko V. I., Zavraisky D. V.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (1); 101-117

DOI: https://doi.org/10.33136/stma2018.01.101

Language: Russian

Annotation: The paper presents the a priori probabilities of collision with the Earth for asteroids of Aten and Apollo groups according to Epic and the minimal distances between the orbits of those asteroids and the Earth orbit. The respective regression equations have been derived. For the first thousand of asteroids of the main belt, a number of conclusions are presented concerning genetic relationship between some of them and possibility in principle of close approach (crossing) of their orbits. Some peculiarities are noted of organization and making mass calculations by Halle’s method. The incompleteness of the results obtained is noted.

Key words:

Bibliography:

1. Degtyarev A. V. Rocket Technology. Problems and Prospects: Selected Scientific-Technical Publications. Dnepropetrovsk, 2014. P. 314-322.

2. Catler E. H. On Feasibility of Practical Use of Asteroids that are Near the Earth. Astronomical Bulletin. Vol. 26, No. 4. 1992.

3. Cramer E. N. Comet Radiants and Connection of Meteorite Flows with Comets / News of OGU Astronomical Observatory. К., 1953.

4. Usichenko V. I., Kryukov A. V. On the Problem of Distances between Pairs of Elliptical Orbits / News of Dnipropetrovsk University. Series: Space Rocket Technology. Vol. 22, Issue 17. No. 4. 2014.

5. Shestaka I. S. Origin, Evolution and Genetic Links of Solar System Small Bodies and their Complexes: Dissertation of Doctor of Physics and Mathematics. K., 1993.

6. Usichenko V. I. Selestial-Mechnical Analysis of Unexplained Observations of Years 1768-1865. Dnipropetrovsk, 2011.

7. Litrov I. I. Mysteries of Sky. Saint Petersburg, 1904.

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

manager — Wed, 24 May 2023 16:00:19 +0000

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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9.1.2023 Methodology for selecting design parameters of solid-propellant sustainer engines. Mathematical support and software

manager — Fri, 12 May 2023 16:11:14 +0000

9. Methodology for selecting design parameters of solid-propellant sustainer engines. Mathematical support and software

Authors:

Yenotov V. H., Kushnir B. I., Pustovharova O. V., Chubarov A. M.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2023 (1); 77-87

DOI: https://doi.org/10.33136/stma2023.01.077

Language: Ukrainian

Annotation: Substantiation of the research tools has been performed as a part of methodology development for the air and missile defense system. The problem under consideration is very complex due to the multifactorial nature of the research object, its qualitative variety and manifold structure, incomplete definition of the problem statement. Furthermore, the ability of modern technologies to produce different arms systems, which are capable of carrying out same class tasks, considerably increases the risk of making not the best decisions. Based on this, as well as taking into account the sharp increase in the cost of weaponry, the considered problem is classified as an optimization one that should be solved through the theory of operations research. In this theory, such task is viewed as a mathematical problem, and mathematical simulation is the basic method of research. The main types of mathematical models, their areas of application have been considered as a part of the analysis. The classification of mathematical models has been indicated according to the scale of reproduced operations, purpose, and goal orientation. Quantitative and qualitative correlation of forces has been accepted as the efficiency criterion, which determines a goal orientation of the model. The problems related to this have been shown. In particular, searching for the compromise between simplicity of the mathematical model and its adequacy to the research object is among these problems. Two of the basic approaches to principles of the military operation model construction and its assessment have been considered. The first is implemented through modeling of the combat operations. The second approach is based on the assumption that different armament types can be compared based on their contribution to the outcome of the operation, and on the possibility to assign «a weighting coefficient» named as a combat potential to each of these types. The modern level of problem solving related to this method has been shown. The reasonability of its application in the considered task, including the definition of forces correlation of the opposing parties, has been substantiated. The basic regulations of the construction concept of the required mathematical model and tools for its research have been formulated based on the analysis results: the assigned problem should be solved by analytical methods through the theory of operations research; the analytical model is the most acceptable conception of the analyzed level of the military operation; the synthesis of the model should be based on the idea of a combat potential. At the same time, it should be taken into account that the known approach to the definition of forces correlation, which uses the combat potential method, has a number of essential limitations, including the methodological ones. Therefore, within the bounds of further research, this approach requires the development both in terms of improving the reliability of the single assessment and in terms of giving the system qualities to the synthesized mathematical model.

Key words: multifunctional system, mathematical model, military unit, combat potential, correlation of forces, defensive sufficiency

Bibliography:

1. Pavlyuk Yu. S. Ballisticheskoe proektirovanie raket: ucheb.-metod, posobie dlya vuzov. UDK623.451.8. Izd-vo ChGTU, Chelyabinsk, 1996. 92 s.
2. Nikolaev Yu. M., Solomonov Yu. S. Inzhenernoe proektirovanie upravlyaemykh ballisticheskikh raket s RDTT. M., 1979. 240 s.
3. Enotov V. G., Kirichenko A. S., Pustovgarova Ye. V. Osobennosti rascheta i vybora raskhodnoy diagrammy dvukhrezhimnykh marshevykh RDTT: ucheb.-metod. posobie. Pod red. akadem. A. V. Degtyreva. Dnepr, 2019. 68 s.
4. Enotov V. G., Kushnir B. I., Pustovgarova Ye. V. Metodika-programma proektnoy otsenki characteristic marshevykh dvigateley na tverdom toplive s korpusami iz vysokoprochnykh metallicheskikh materialov, statsionarnymi soplami i postanovka ee na avtomatizirovanniy raschet: ucheb.-metod. posobie. Vtoroe izd., pererabot. i dop. Pod red. A. S. Kirichenko. Dnep, 2019. 91 s.
5. Enotov V. G., Kirichenko A. S., Kushnir B. I., Pustovgarova Ye. V. Metodika proektnoy otsenki characteristic marshevykh dvigatelnykh ustanovok na tverdom toplive s povorotnymi upravlyayuschimi soplami, plastikovymi tselnomotannymi korpusamy i postanovka ee na avtomatizirovanniy raschet: ucheb.-metod. posobie. Vtoroe izd., pererabot. i dop. Pod red. akadem. A. V. Degtyareva. Dnepr. 2019. 149 s.
6. Alemasov V. Ye., Dregalin A. F., Tishin A. P. Teoriya raketnykh dvigateley. M., 1980. 55 s.
7. Raschetnye materialy dlya podgotovki i vydachi iskhodnykh dannykh na razrabotku uzlov marshevykh dvigatelnykh ustanovok na tverdom toplive. Raschet ID metodom avtomatizirovannogo proektirovaniya operativno-takticheskikh raket: inzhenern. zapiska 553-376 IZ. GP «KB «Yuzhnoye». Dnepropetrovsk, 2017. 30 s.
8. Metodika avtomatizirovannogo proektirovaniya operativno-takticheskikh raket: nauch.-tekhn. Otchet 03-453/32 NTO. GP «KB «Yuzhnoye». Dnepropetrovsk, 2010. 127 s.

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1.1.2023 On the development of a methodology for building air and missile defense systems. Explanation of the investigation mechanism

manager — Thu, 11 May 2023 15:25:30 +0000

1. On the development of a methodology for building air and missile defense systems. Explanation of the investigation mechanism

Authors:

Perkov V. M., Herasimov A. P., Degtyarev O. V.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2023 (1); 3-13

DOI: https://doi.org/10.33136/stma2023.01.003

Language: Ukrainian

Key words: multifunctional system, mathematical model, military unit, combat potential, correlation of forces, defensive sufficiency

Bibliography:

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Katasonov Yu. V. SShA: voennoe programmirovanie. M., 1972. 228 s.
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Ponomarev O. K. O metodah kolichestvennoy i kachestvennoy otsenki sil storon. Voennaya mysl. № 4. S. 41-46.
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