Персона:
Аксенов, Виктор Серафимович

Организационные подразделения

Организационная единица

Институт лазерных и плазменных технологий

Стратегическая цель Института ЛаПлаз – стать ведущей научной школой и ядром развития инноваций по лазерным, плазменным, радиационным и ускорительным технологиям, с уникальными образовательными программами, востребованными на российском и мировом рынке образовательных услуг.

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Аксенов

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Виктор Серафимович

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Только метаданные
AUTOTHERMAL NATURAL GAS CONVERSION AND ALLOTHERMAL GASIFICATION OF LIQUID AND SOLID ORGANIC WASTES BY ULTRASUPERHEATED STEAM
(2022) Frolov, S. M.; Smetanyuk V. A.; Sadykov I. A.; Silant'ev A. S.; Aksenov, V. S.; Shamshin I. O.; Avdeev K. A.; Frolov F. S.; Фролов, Сергей Михайлович; Аксенов, Виктор Серафимович
Только метаданные
Deflagration-to-Detonation Transition in Air Mixtures of Polypropylene Pyrolysis Products
(2019) Zvegintsev, V. I.; Bilera, I. V.; Kazachenko, V. M.; Shamshin, I. O.; Frolov, S. M.; Aksenov, V. S.; Фролов, Сергей Михайлович; Аксенов, Виктор Серафимович
© 2019, Pleiades Publishing, Ltd.Abstract: A new method to determine fuel detonability has been proposed, which is based on measuring the length and time of a deflagration-to-detonation transition (DDT) in a calibration pulsed-detonation wind tunnel (CPDWT). The fuel was polypropylene granules (PG). A test stand was designed and built, which included the CPDWT and a gas generator to obtain PG pyrolysis products (PGPP) at a decomposition temperature to 800°C. Experiments for studying DDT in PGPP–air mixtures were carried out. It was shown that the detonability of PGPP is close to that of a stoichiometric mixture of autogas liquefied petroleum gas with air under normal conditions.
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АЭРОДИНАМИЧЕСКОЕ РАСПЫЛЕНИЕ СТРУЙ МЕТАЛЛИЧЕСКИХ РАСПЛАВОВ ИМПУЛЬСНЫМИ УДАРНЫМИ И ДЕТОНАЦИОННЫМИ ВОЛНАМИ
(НИЯУ МИФИ, 2025) ФРОЛОВ, С. М.; ИВАНОВ, В. С.; АКСЕНОВ, В. С.; ШАМШИН, И. О.; Аксенов, Виктор Серафимович; Фролов, Сергей Михайлович
Предложен новый способ получения металлических порошков для аддитивных технологий путем аэродинамического распыления свободно падающей струи расплава поперечными импульсными ударными или детонационными волнами. Импульсные ударные и детонационные волны, используемые для распыления свободно падающих струй расплавов, генерируются импульсно-детонационной пушкой, работающей на стехиометрической смеси жидкого углеводородного горючего и газообразного кислорода. Показано, что минимальный размер частиц получаемых порошков составляет 0,1–1 мкм.
Только метаданные
AIR-BREATHING PULSE DETONATION THRUST MODULE
(2025) Frolov, S. M.; Ivanov, V. S.; Aksenov, V. S.; Shamshin, I. O.; Фролов, Сергей Михайлович; Аксенов, Виктор Серафимович
Только метаданные
Air-breathing pulsed detonation thrust module: Numerical simulations and firing tests
(2019) Zangiev, A. E.; Frolov, S. M.; Aksenov, V. S.; Ivanov, V. S.; Shamshin, I. O.; Фролов, Сергей Михайлович; Аксенов, Виктор Серафимович
© 2019 Elsevier Masson SAS The air-breathing pulsed detonation thrust module (TM) for an aircraft designed for a subsonic flight at a speed of up to 120 m/s when operating on a standard aviation kerosene was developed using the analytical estimates and parametric multivariant three-dimensional (3D) calculations. The TM consists of an air intake with a check valve, a fuel supply system, a prechamber-jet ignition system and a combustion chamber with an attached detonation tube. An experimental sample of TM was fabricated, and its firing tests were carried out on a test rig with a thrust-measuring table. In firing tests, TM characteristics are obtained in the form of dependencies of effective thrust, aerodynamic drag and fuel-based specific impulse on fuel consumption at different speeds of the approaching air flow. It has been experimentally shown that the fuel-based specific impulse of the TM reaches 1000-1200 s, and the effective thrust developed by it reaches 180–200 N.
Только метаданные
Deflagration-to-detonation Transition in Stratified Oxygen–Liquid Fuel Film Systems
(2022) Shamshin, I. O.; Frolov, S. M.; Aksenov, V. S.; Фролов, Сергей Михайлович; Аксенов, Виктор Серафимович
© 2021 Taylor and Francis Group, LLC.Deflagration-to-detonation transition (DDT) in gas (oxygen)–liquid n-heptane film and gas (oxygen)–liquid n-decane film systems is registered experimentally using a fused or exploding wire as a weak ignition source that generates a primary shock wave with a Mach number ranging from 1.02 to 1.6. In a straight smooth-walled channel of rectangular cross section 54 × 24 mm, 3 and 6 m long with one open end, the DDT is obtained at distances 900 to 4000 mm from the ignition source 3 to 1700 ms after ignition. The DDT is obtained for n-heptane and n-decane films 0.2 to 0.7 mm thick, which corresponds to the overall fuel-to-oxygen equivalence ratios of 15 to 40. The registered detonation velocities range from 1400 to 2000 m/s. In several experiments, a high-velocity quasi-stationary deflagration front propagating at an average velocity of 700–1100 m/s is recorded. The structure of this front includes the leading shock wave followed by the reaction zone separated from each other by a time delay of 90 to 190 μs. The results obtained are important for explosion safety and for better understanding of the operation process in the continuous-detonation and pulse-detonation combustors of advanced rocket and air-breathing engines with the supply of liquid fuel in the form of a wall film.
Только метаданные
Detonability of fuel–air mixtures
(2020) Zvegintsev, V. I.; Bilera, I. V.; Kazachenko, M. V.; Shamshin, I. O.; Frolov, S. M.; Aksenov, V. S.; Фролов, Сергей Михайлович; Аксенов, Виктор Серафимович
© 2020, Springer-Verlag GmbH Germany, part of Springer Nature.A new experimental method for evaluating the detonability of fuel–air mixtures (FAMs) based on measuring the deflagration-to-detonation (DDT) run-up distance and/or time in a standard pulse detonation tube (SDT) is used to rank gaseous premixed and non-premixed FAMs by their detonability under substantially identical thermodynamic and gasdynamic conditions. In the experiments, FAMs based on hydrogen, acetylene, ethylene, propylene, propane–butane, n-pentane, and natural gas of various compositions, as well as FAMs based on the gaseous pyrolysis products of polypropylene (PP), are used: from extremely fuel-lean to extremely fuel-rich at normal temperatures and pressures. The concept of equivalent FAMs exhibiting the same or similar detonability under the same conditions is proposed. Equivalent FAMs can be used for predictive physical modeling of detonation processes involving FAMs of other fuels. The ranking of FAMs in terms of their relative detonability allows choosing a propylene FAM for physical modeling of the operation process in the PP-fueled solid-fuel ramjets operating on detonative combustion.
Только метаданные
AMPLIFICATION OF THE SHOCK WAVE IN A TWO-PHASE MIXTURE OF SUPERHEATED STEAM AND LIQUID TRIETHYLALUMINUM
(2024) Frolov, S. M.; Shamshin, I. O.; Byrdin, K. A.; Aksenov, V. S.; Фролов, Сергей Михайлович; Аксенов, Виктор Серафимович
Только метаданные
Pulsed detonation hydroramjet: simulations and experiments
(2020) Avdeev, K. A.; Frolov, F. S.; Sadykov, I. A.; Tukhvatullina, R. R.; Frolov, S. M.; Aksenov, V. S.; Shamshin, I. O.; Фролов, Сергей Михайлович; Аксенов, Виктор Серафимович
© 2019, Springer-Verlag GmbH Germany, part of Springer Nature.A water transportation engine of a new type—a pulsed detonation hydroramjet (PDH)—has been designed, manufactured, and tested. The PDH is a pulsed detonation tube (DT) inserted in an open-ended water guide. The thrust is developed by shock-induced pulsed water jets periodically emanating from the water guide nozzle. Numerical simulations indicate that valveless and valved PDH models can produce thrust with the specific impulse on the level ranging from 600 to 2400 s. Test firings of PDH models of various designs with a 2-liter DT were carried out on a specially designed test rig, which provides the approaching water flow in the form of a submerged jet at a speed of up to 10 m/s. The measured average specific impulse of valveless and valved PDH models was on the level of 350–400 s when the first operation cycle was not considered. The measured values of the average thrust and specific impulse in the first operation cycle were shown to be always much higher than those in the subsequent cycles: In the tests, the average value of thrust in the first cycle varied from 300 to 480 N, and the value of the specific impulse varied from 960 to 2690 s, which indicates the potential of increasing the thrust performance.
Только метаданные
SHOCK-TO-DETONATION TRANSITION IN A TWO-PHASE MIXTURE OF LIQUID TRIETHYLALUMINUM WITH SUPERHEATED STEAM
(2025) Frolov, S. M.; Shamshin, I. O.; Byrdin, K. A.; Avdeev, K. A.; Aksenov, V. S.; Фролов, Сергей Михайлович; Аксенов, Виктор Серафимович