CONTENTS #1 (January) 2019
Researches of the Civil Aircrafts Perspective Engines and Power-Plants of 2020–2030 years (p. 3 – 13)
A.V. Lukovnikov, A.S. Polev, A.I. Lanshin
Review of complex researches of critical technologies and system decisions, which carry out in Central Institute of Aviation Motors named after P.I. Baranov, in the field of a scientific and technical reserve on perspective to engines and power-plants of the civil planes of 2020 – 2030 creation is resulted. Engines of traditional and nonconventional schemes for passenger planes and demonstrators of technologies corresponding to them on particular subassemblies, elements and systems are considered.
Keywords: gas turbine engine; engine core; critical technologies; aircraft; power plant; design parameters; technology readiness level.
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Vortex Model of Aerodrome, Euro-Asian and American Tornadoes (p. 14 – 27)
A.G. Prudnikov, A.K. Goncharov, N.N. Zakharov, A.M. Podvalnyy, V.V. Severinova
The aerodynamical parameters of aerodrome tornado and natural tornado are presented. The physics model of vortex mechanics is given.
Keywords: vortex mechanics; vortex model; toroidal vortex; tornado; aerodrome tornado; aerodynamical parameters.
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To the Question of Accounting for the Risks of Achieving the Assigned Aircraft Performance
(p. 28 – 32)
V.A. Klyagin, D.A. Laushin
When developing a new aircraft, technical decisions are made in the condition of inadequate information on the mass – size, aerodynamic characteristics of the aircraft and the engine altitude-airspeed performance that will be achieved in the process of the project. The article describes an approach that allows to reduce the risk of failure to meet the requirements of the tactical and technical assignment in conditions of uncertainties at the conceptual stage of design.
Keywords: uncertainties; risks; flight performance; preliminary design of the aircraft.
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Design and Analysis of the Tether-Assisted Schemes for Returning Payloads from LEO (p. 33 – 40)
Z. Dong, Yu.M. Zabolotnov, C.Q. Wang
The multiple tether-assisted schemes for returning payloads from LEO are designed and analyzed in this paper. The feature of this work is that the aerodynamic forces acting on all parts of the system including on the tether are considered. In addition, the proposed schemes for returning payloads include the use of the atmospheric probe as an additional braking device.
Keywords: space tether system; payload; returning schemes; atmospheric probe; reentry angle.
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A Perspective System of Air Supply for Air Intake Devices of Modern Rocket-Direct-Flow Engines with Solid Rocket Fuel (p. 41 – 44)
V.A. Sorokin, E.A. Stirin, D.Yu. Fedorov, A.N. Molodsov, P.V. Valuy, V.P. Mahrov, O.V. Somov
The existing arrangements of air intake devices on aircrafts using solid- fuel rocket-direct-flow engines are considers.The results of patenting of the air intake device design perspective with a distributed air supply for the use in a rocket-direct-flow engine with solid rocket fuel are presents.
Keywords: rocket engine; air intake device; afterburning chamber; air intake windows; air intake pipebranch of detonation.
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Principles of Construction and Control of the Target Operation of a Cluster of Small Observation Satellites with a Distributed Optical Aperture (p. 45 – 54)
V.Yu. Klyushnikov
The article deals with the task of autonomous control of a promising self-organizing cluster of small Earth remote sensing satellites with a distributed optical aperture. Adaptive cluster self-organization is achieved through the use of multi-agent technologies (swarm control technologies).
Keywords: small satellite; formation flying; cluster; multi-agent technologies; swarm contro.
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A Way to Determine the Fuel Quantity During the Testing of Low Thrust Engines in Assembly
(c. 55 – 62)
E.G. Alekhin, A.A. Belkin, D.B. Danilov, V.A. Morozov, I.E. Fedorov
Describes a method for determining the volume of propellant components spent during the operation of the low-thrust engines in the event of complex bum-though tests for propulsion units with a pressurized fuel feed based on the actual consumed volume of the pressurizing gas.
Keywords: complex bum-through tests; low-trust liquid propellant rocket engine; rocket fuel components; rocket technology; spherical supercharger tank; gas-dynamics evaluation.
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