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CONTENTS #1 (January) 2017

To work as Ilyushin – easy, reliably, durable (p. 3 – 7)

G.V. Novozhilov

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The Effect Of Lowering Technogenic Impact Level Of Proton-M By Applying Digital Flight Control System (p. 8 – 16)

A.V. Vladimirov, V.L. Ivanov, V.D. Borisenko

Reduction of technogenic impact level of the integrated space vehicle (ISV) launches due to digital flight control system is analyzed herein. A comparative comprehensive assessment of space rocket complexes (SRC) ecological safety by investigating the SRC impact on the various environment components with their further convolution is carried out.

Keywords: digital control system; ecological safety; space rocket complex; integrated space vehicle; launch vehicle.

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Monitoring The Status And Technical Diagnostics Of Onboard Equipment Of Flying Vehicle (p. 17 – 22)

G.P. Shibanov

Presents the algorithms of monitoring status of onboard equipment and this technical diagnostics. Algorithms base on pattern recognition theory. Construct the proof of effectiveness this algorithms for monitor the status of onboard equipment and this technical diagnostics of flying vehicle. Algorithms the check is satisfied at flight onboard computer.

Keywords: algorithms; methods of check; technical diagnostics; onboard equipment; pattern recognition theory; flying vehicle.

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Assessment Method Of Aircraft Trail Influence During Aircraft Flights At Close Combat Order
(p. 23 – 28)

O.A. Balyk

Evaluation methods of wake vortex characteristics occurring behind the maneuvering aircraft are considered in this work. Model description of the near wake vortex is given. Parameter calculation of aircraft trail of up-to-date maneuverable aircraft and aircraft movement modeling under aircraft trail effect are stated here.

Keywords: model; wake vortex; aircraft; aircraft trail; vortex circulation; modeling results.

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Problem Of Selection Of Parameters Of A Helicopter, Which Carries Out A Two-Stage Transportation Mission (p. 29 – 43)

B.L. Artamonov, V.N. Zhuravlev, V.I. Shaidakov

The described research investigates the features of design of a single-rotor transport helicopter, which carries out a two-stage transportation mission. The paper gives an outline of mathematical models, which are proposed by the authors for analysis of helicopter weight and aerodynamics. The application of the proposed models is illustrated on the example of analysis of the ability of Mil-38 helicopter to complete an offshore transportation mission. This example is also used to investigate and show the influence of the main rotor diameter on technical effectiveness criteria of a helicopter, which is designed for a specified mission.

Keywords: single-rotor helicopter; two-stage transportation mission; mathematical model; weight analysis; aerodynamic analysis.

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GNSS Signal’s Power Measurements By Means Of Large-aperture Dish Antenna System (p. 44 – 48)

О.V. Denisenko, V.N. Fedotov, I.S. Silvestrov, V.L. Voronov, A.S. Zavgorodniy, I.V. Ryabov, A.I. Bolkunov

This article is dedicated to the GNSS signal’s power measurements by means of a specialized metrological system, located in FSUE «VNIIFTRI». The technical characteristics of the measuring equipment, are presented, the measuring procedure and results processing in order to reduce the interference effects are described. The GNSS satellites observations results with a period of 8 days are also given.

Keywords: power; GNSS; dish antenna.

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Assessment Of Test-Flight Equipment For Parachute Systems Of The Big Areas (p. 49 – 56)

P.I. Ivanov, V.V. Krashilin, M.M. Krivorotov, Yu.L. Perkov

The one of types of flying equipment – weight models for flight tests of parachute systems of the big areas are presented. It is obligatory at certification of flight-test equipment.

Keywords: certification of flight-test equipment; weight models; parachute system.

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Capabilities Analysis And Performance Evaluation Of Two-Stage Combined Liquid-Electric Upper Stage (p. 57 – 61)

O.V. Mikheev, A.E. Pologentsev, S.V. Belik

Proposals for developing a two-stage Upper Stage are considered. The first stage is equipped with a liquid rocket engine-based propulsion system, the second stage is equipped with an electric propulsion system. The results of the design modeling are presented with respect to the determination of power performance capabilities of an upper stage like that.

Keywords: upper stage; liquid rocket engine; electric propulsion system; actuating medium; payload; geostationary orbit.

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