CONTENTS #5 (May) 2019
Leaders of Rocket Engine Development. To 90th Anniversary of NPO Energomash Named after Academician V.P. Glushko (p. 5 – 11)
P.S. Levochkin, V.K. Chvanov, V.S. Sudakov
The article is devoted to the activities of the leading Russian enterprise on development of powerful liquid propellant rocket engines – JSC «NPO Energomash named after academician V.P. Glushko». Its history began 90 years ago, when, a group under the leadership of V.P. Glushko began work on the development of rocket engines and rockets in Gas-Dynamic Laboratory in Leningrad. The enterprise has passed a great and glorious way. Almost all domestic space launch vehicles were launched into space with the help of engines developed by NPO Energomash. The world’s most powerful rocket engines RD-170 /171 are also created in NPO Energomash. Since 2000 NPO Energomash is conducting now the development of a powerful rocket engine for new advanced Russian launch vehicles.
Keywords: liquid propellant rocket engines; rocket and space technology; LOX-kerosene LPRE; schematics with afterburning of oxidizer-rich gas.
Development of a Promising Stub Design for Air Intake Devices of Modern Rocket-Direct-Flow Engines with Solid Rocket Fuel (p. 12 – 16)
V.A. Sorokin, M.A. Tikhomirov, E.A. Stirin, O.V. Mokretsova, P.V. Nikitin, P.V. Valuy, G.G. Kobko
Briefly discusses the existing technical solutions for the rocket-direct-flow engine air intake devices stubs’ opening during the transition to the march mode. The results of the development of a non-resettable stub promising design for air intake devices of rocket-direct-flow engines with solid rocket fuel are presented.
Keywords: stub; air intake device; rocket engine; launch mode; march mode.
Acoustic Emission Control of the Wing Box Defects of a Carbon-Fiber Aircraft Wing in the Process of Static and Impact Loadings (p. 17 – 24)
V.E. Barsuk, A.N. Seryeznov, L.N. Stepanova, V.V. Chernova
Acoustic emission emission (AE) monitoring of the wing box made of composite material Torayca T800 was carried out under static and impact loads. Two piezo-antennas were installed on the lower and upper zones of the wing box, consisting of four acoustic emission transducers. Under static loading, active sources of AE signals were identified. They were located on the lower surface of the wing box. The structural coefficient, amplitude, and frequency were used as the main informative parameters of the AE signals.
Under impact loading of the wing box by a falling metal rod, the AE signals were recorded and located at the moment of impact. 212 signals with an amplitude not higher than 200 mV were recorded, of which 163 signals came from the lower zone of the wing box and 49 signals from the upper zone of control with a strike.
Keywords: aviation; wing box; carbon fiber; acoustic emission; location; defect; nondestructive test.
Probable Evaluation of the Results of Detection and Recognition of Ground Objects During Air Laser-Location Shooting (p. 25 – 30)
The result of the airborne laser-radar survey is a cloud of laser reflection points from the scanned surface, attached to the coordinate system built in the navigation blocks of the laser locators. The process of detection and recognition based on the data obtained is preceded by the process of classification of laser reflection points: land, vegetation, natural and artificial objects. The reliability of the recognition results depends on the qualitative classification process. To solve the problem of recognition of ground objects, they must first be divided into classes. In this article, the author proposes a method for the probabilistic evaluation of recognition algorithms based on reclassified data.
Keywords: laser location; algorithm; feature dictionary; alphabet of classes; recognition; sampling; аposteriori аprobability; priori probability; conditional probability; probability matrix.
Optimal Control of the Angular Velocity of the Asymmetric Probe in the Atmosphere of Mars Through Low-Thrust Engines (p. 31 – 36)
V.V. Lyubimov, E.V. Kurkina
A linearized dynamical system describing the motion of a descent probe with inertial asymmetry in the atmosphere of Mars is considered. The optimal law of controlling the angular velocity of the descent probe by means of jet thruster in the atmosphere of the planet. In the synthesis of control, the dynamic programming method and the averaging method are used. The results of numerical modeling of the controlled motion of the probe relative to the center of mass are given.
Keywords: optimal control; atmosphere; angular velocity; dynamic programming; asymmetry; jet engines.
Modernization of Il-76 Transport Aircraft to Creat Reusable Aerospace System (p. 37 – 46)
S.V. Petukhov, Yu.N. Pugachev, P.A. Gamburg, R.A. Latyshov
The article presents two projects of the multifunctional aerospace system (MAKS) of multi-access use for provide freight and touriss flows of Ears-AES-Earth. For the first stage, a modification of the serial Il-76 military transport aircraft is used. By comparing the proparties and characteristic of the options of the MAKS it is shown that one of the possible options is a system with the first stage made according to the catamaran scheme.
Keywords: reusаble aerospace system; multifunctional aerospace system; space tourism; transpоrt aircraft; flying cosmodrom; air start.
Legal Problems of the Military Use of the Outer Space and Ways of Their Overcoming (p. 47 – 56)
K.G. Bomstein, V.Yu. Granich, Yu.M. Dzema
Two variants of the military use of outer space are presented: a real non-weapon (providing) system and a hypothetical weapon system. The functional capabilities of the military use of outer space systems are revealed. The potential threat to the continued existence of mankind has been revealed in the implementation of the concepts of the weapons-based military space system. In this connection, the questions of the legal protection of the cosmos are analyzed, in order not to become a fully possible sphere of deployment of weapons. The proposals of our country on the prevention of armed militarization of outer space are presented.
Keywords: militarization of outer space; legal base; non-weapon (providing) system; weapon system; deployment of weapons; prevention of armed militarization of outer space.
The Effect of the Geometric Nonlinearity on the Twisting Angle of the Control Surface (p. 57 – 62)
The effect of taking into account the geometric nonlinearity on the twist angle of the control surface of a compound construction consisting of two rods that to model the carrier and control surfaces of the aircraft is evaluated.
Keywords: lifting member and control surface; geometric nonlinearity; twist angle.