Parameters liable to be defined while a multi-dome parachute system flight-testing for its efficiency estimation

Aeronautical and Space-Rocket Engineering

Aerodynamics and heat-exchange processes in flying vehicles


DOI: 10.34759/vst-2020-3-49-59

Аuthors

Ivanov P. I.*, Kurinnyi S. M.**, Krivorotov M. M.***

Research Institute of Aeroelastic Systems, 85, Garnaeva str, Feodosia, Crimea Republic, 298112, Russia

*e-mail: Ivanovpetr@rambler.ru
**e-mail: Kurinniys@yandex.ru
***e-mail: Krivorotovmm@mail.ru

Abstract

It is customary to assume that a multi-dome parachute system is a system with the number of domes in the bundle of two and more [1–20]. Efficiency of the multi-dome parachute system is understood in this work as the ability of the object – multi-dome parachute system ability to perform its functions within the framework of the specified values of its critical (most important parameters).

The presented work considers some critical parameters liable to be determined while the flight-testing of the system, comprising an air drop object and multi-dome parachute system, such as landing speed and non-simultaneity of the domes filling process.

The article presents the dependence of the vertical component of the landing speed, being determined while the multi-dome parachute system design computations, which is assumed as an average valued (mathematical expectation) of the real value of the vertical component of the landing speed, as it is a random value in reality. The most probable random error of the landing speed function was determined with account for inaccuracy of measurements of all arguments included in the function structure, which allows evaluating contribution of each error component to the speed determining error, as well as find the largest one and minimize it.

Further, alongside with accounting for the atmospheric parameters, the possible active impact of near-Earth atmospheric turbulence on the value of real vertical component of the landing speed was being reckoned in.

The experimental results on determining the average value of real vertical component of the landing speed, reduce to the standard atmospheric conditions at the sea level and regular weight according to the data of a series of flight-testing, are presented.

The article presents the dependence of distribution density and probability of not exceedance of assigned value of landing speed’s vertical component for a special case.

The authors marked the possibility of appearance of insignificant number of “jumping-out” measurements under the impact of intensive, powerful surface atmospheric turbulence on the multi-dome system.

The article presents the detailed analysis of the phenomenon of non-simultaneity of the domes filling process in the bundle. Substantiation of the non-uniformity parameter importance for the multi-dome parachute system operation effectiveness is being brought forward.

The authors introduced a parameter named the coefficient of domes in the bundle filling simultaneity. The notions of leaders and outsiders for the domes in the bundle were introduced as well. The analysis of their role in the domes filling in the bundle was performed. The article presents physical explanation of the domes filling non-uniformity phenomenon. Some important effects, associated with the non-uniformity phenomenon, as well as factors affecting the non-uniformity of the domes filling in the bundle were considered.

Certain experimental data on the non-simultaneity of domes filling in the bundle is presented for the possible theoretical studies in the future of the non-simultaneity of domes filling phenomenon. The article presents the experimental data by the time intervals of the domes filling process in the three-domed corrugated parachute system with the area of the single dome of FS = 600 m2, while the airdrop of the object of m ≈ 3 tons in a wide range of ram air of the system implementation according to the data of forty four flight experiments. The experimental data on the time intervals of the four-dome parachute system with the area of the single dome of FS = 760 m2, while the airdrop of the object of m ≈ 6 tons according to the data of eleven flight experiments.

The above-mentioned data can be used effectively for checking the adequacy of the mathematical models under development of simultaneity (non-simultaneity) of the four-dome parachute systems filling.

The above data may be effectively used for the test for goodness of developed mathematical models of simultaneity (or non-simultaneity) of canopies filling in the four-dome parachute system.

Keywords:

multi-domed parachute system, critical (sensitive) parameters, landing speed, non-simultaneity of the dome bundle filling

References

  1. Lobanov N.A. Osnovy rascheta i konstruirovaniya parashyutov (Basics of calculation and design of parachutes), Moscow, Mashinostroenie, 1965, 363 p.

  2. Lyalin V.V., Morozov V.I., Ponomarev A.T. Parashyutnye sistemy. Problemy i metody ikh resheniya (Parachute system. Problems and methods of their solution), Moscow, Fizmatlit, 2009, 576 p.

  3. Rysev O.V., Ponomarev A.T., Vasil’ev M.I., Vishnyak A.A., Dneprov I.V., Moseev Yu.V. Parashyutnye sistemy (Parachute system), Moscow, Nauka. Fizmatgiz, 1996, 288 p.

  4. Zaidel’ A.N. Elementarnye otsenki oshibok izmerenii (Elementary estimates of measurement errors), Leningrad, Nauka, 1965, 80 p.

  5. Rego K.G. Metrologicheskaya obrabotka rezul’tatov tekhnicheskikh izmerenii. Spravochnik (Metrological processing of technical measurements results), Kiev, Tekhnika, 1987, 128 p.

  6. Sobol’ I.M. Metod Monte-Karlo (Monte-Carlo method), Moscow, Nauka, 1985, 80 p.

  7. Ivanov P.I., Berislavskii N.Y. Problematic issues of functioning of multi-dome parachute systems. Aerospace MAI Journal, 2020, vol. 27, no. 1, pp. 43-52. DOI: 10.34759/vst-2020-1-43-52

  8. Ivanov P.I., Kurinnyi S.M., Krivorotov M.M. Asymmetry in the parachute canopy filling process. Aerospace MAI Journal, 2019, vol. 26, no. 3, pp. 7-16.

  9. Ivanov P.I. Materialy X Mezhdunarodnoi nauchno-tekhnicheskoi konferentsii uchenykh Ukrainy, Rossii, Belorussii “Prikladnye problemy mekhaniki zhidkosti I gaza”, Sevastopol, SevNTU, 2001, pp. 97-101.

  10. Ivanov P.I. Dinamicheskie sistemy, 2001, no. 17, pp. 41-46.

  11. Gromov Yu.Yu., Zemskoi N.A., Lagutin A.V. et al. Sistemnyi analiz v informatsionnykh tekhnologiyakh (System analysis in information technologies), Tambov, TGTU, 2007, 176 p.

  12. Sistema gosudarstvennykh ispytanii produktsii. Ispytaniya i kontrol’ kachestva produktsii. Osnovnye terminy I opredeleniya. GOST 16504-81 (The state system of products testing. Product test and quality inspection. General terms and definitions, State Standard 16504-81), Moscow, Standartinform, 2011, 24 p.

  13. Ivanov P.I. Aerodinamicheskie kharakteristiki parashyutov bol’shikh ploshchadei s konstruktivnoi pronitsaemost’yu (Aerodynamic characteristics of large area parachutes with structural permeability), Doctor’s thesis, Moscow, NII AU, 1986, 202 p.

  14. Ivanov P.I. Letnye ispytaniya parashyutnykh system (Flight testing of parachute systems), Feodosiya, Grand–S, 2001, 332 p.

  15. Morozov V.I., Ponomarev A.T., Rysev O.V. Matematicheskoe modelirovanie slozhnykh aerouprugikh system (Mathematical modeling of complex aeroelastic systems), Moscow, Fizmatlit, 1995, 736 p.

  16. Antonenko A.I., Rysev O.V., Fatykhov F.F, Churkin V.M., Yurtsev Yu.N. Dinamika dvizheniya parashyutnykh sistem (Dynamics of parachute systems movement), Moscow, Mashinostroenie, 1982, 152 p.

  17. Ivanov P.I., Berislavskii N.Yu. Nauka i tekhnika vozdushnykh sil vooruzhennykh sil Ukrainy, 2014, no. 2(15), pp. 58-66.

  18. Ivanov P.I. Vestnik Khersonskogo natsional’nogo tekhnicheskogo universiteta, 2008, no. 2(31), pp. 189-194.

  19. Churkin V.M. Ustoichivost’ i kolebaniya parashyutnykh system (Stability and oscillations of parachute systems), Moscow, URSS, 2017, 232 p.

  20. Churkin V.M., Serpicheva E.V., Silant’ev V.M. Trudy MAI, 2003, no. 12. URL: http://trudymai.ru/eng/published.php?ID=34455

mai.ru — informational site of MAI

Copyright © 1994-2024 by MAI