Durov Dmitrij Sergeevich

Bio: Durov Dmitrij Sergeevich is an academic researcher. The author has contributed to research in topics: Fuselage & Thrust. The author has an hindex of 5, co-authored 92 publications receiving 130 citations.

Multirotor convertible high-speed helicopter

Abstract: FIELD: aircraft engineering.SUBSTANCE: this helicopter is equipped with the system of distributed thrust of different-size rotors in X2+3 configuration. One smaller rotor turning in vertical plane is fitted at fuselage end and panels of first swept-forward wing and second swept-back X-like wing. Besides, there are two large and smaller rotors. Helicopter represents a monoplane of two-beam configuration with mid-wing. It comprises fuselage-nacelle, power plant including engine and reduction gearbox with rear dual concentric rotors. The latter allow horizontal thrust and vertical or inclined thrust corresponding to deflection between two-keel rudder and three-leg undercarriage. Rotor system with distributed thrust of different-size rotors in 2+3 configuration comprises smaller rotor mounted at rotary reduction gearbox, larger rotors mounted at first wings pylons and two smaller rotors arranged with their reduction gearboxes at second wing tips. Helicopter allows conversion of its flight configuration from five-rotor one into rotorcraft configuration or winged autogiro with single-rotor propulsion.EFFECT: better weight efficiency, better transverse and longitudinal controllability.2 cl, 3 dwg, 1 tbl

Multipurpose multi-tiltrotor helicopter-aircraft

Abstract: FIELD: transport. ^ SUBSTANCE: invention relates to aircraft engineering, in particular, to design of converter planes with tiltrotors. Proposed helicopter-aircraft represents a high-wing monoplane with twin-fin tail, fuselage, power plant engines transmitting power via system of transmission connection shafts to front and rear reduction gears equipped with output tilt shafts with tractor and pusher propellers to generate thrust and lift, tricycle-equipped retractable landing gear with nose and main lateral gears. Helicopter-aircraft represents a modular multi-tiltrotor convertible plane with, at least, two pods on wing, each supporting front and rear propellers extending beyond appropriate wing tips. Transmission comprising two main and intermediate rotor gears for each engine represents configuration H-shaped in plan. Transmission allows driving all rotors from one running engine in the case of failure of another engine or at surplus power of power plant. ^ EFFECT: higher reliability and safety, rolling stability, transverse controllability in transition maneuvers and hovering. ^ 2 dwg

High-speed turbofan combined helicopter

Abstract: FIELD: aviation.SUBSTANCE: high-speed turbofan combined helicopter is designed according to the concept of propeller and jet thrust and is equipped with combined traction and lifting systems having a jet thrust with a thrust of different-sized propellers, directed along the axis of symmetry or perpendicular to the latter during VTL or hovering from TRTE with a controlled thrust vector together with thrust of two smaller propellers mounted on the V-shaped stabiliser consoles, or from TRTE together with the thrust of two larger main rotors. The rotational planes of blades of the larger main rotors are located between the biplane wings, forming the left and right trapezoidal slotted channels by inner sections, and fixed to the output shafts of console gearbox. Each gearbox is placed in overwing fairing on the tip of the lower wing and is provided with a hollow fixed support mounted coaxially inside the rotor shaft. The upper part of the support protruding from the shaft is fixed in the overwing fairing of the upper wing, forming a high-positioned biplane with wings of a closed structure, having a diamond-shaped configuration.EFFECT: reducing the required power for longitudinal balancing, increasing the speed, height and range of flight.3 cl, 1 tbl, 1 dwg

Multipurpose hydroconvertipropeller plane

Abstract: FIELD: aircraft engineering. ^ SUBSTANCE: invention relates to aviation and pertains to development of multipurpose hydroconvertipropeller plane. The propose plane wing spins accommodates two rotary propellers to create horizontal and vertical thrust with turning assemblies and reduction gears. The latter are linked up, via connection shafts, with the main reduction gear driven from the power plant two engines mounted in nacelles on both sides of the fuselage lengthwise axis and furnished with timing shaft. This propeller plane can get converted in helicopter modes from two-propeller lengthwise configuration in to four-propeller configuration combining crosswise and lengthwise configuration and vice versa. It can also, in aircraft conditions, change over from monoplane configuration in to lengthwise configuration of triplane and vice versa. Transmission incorporating two reduction gears with rotors and lengthwise system of the shafts represents X-figure in horizontal plane. Front and rear rotors, and L.H. and R.H cantilever propellers run in mutually opposite directions. Front and rear rotor reduction gears mounted on, rhombic in plane, cross-piece arranged zigzag-like along its smaller diagonal, the larger diagonal of the latter and along the fuselage lengthwise axis. Aforesaid cross-piece consists of two different-size levers representing V-like hollow load-bearing beams with spaced apart eyes hinged to the fuselage top part and allowing their mutual turning at fixed and independent deviation in vertical plane for positive and negative different-size angles. The front smaller lever can deviate for larger negative angles, while the rear one deviates for large certain positive angles. All-moving horizontal and vertical empennages are mounted on the larger rear lever end, attached to its lateral V-like sides. Lengthwise shafts passing, inside the levers, from the rotor reduction gears to the main reduction gear located at the center of rhombic frame feature universal joints to transfer power to the above rotors at various inclinations of the levers in vertical lengthwise plane. ^ EFFECT: increased take-off weight and load ratio, simpler tail beam design, improved longitudinal and yaw control in vertical take-off, landing and hovering, that allows landing on limited-size sites in surface, ship deck and sea surface. ^ 2 dwg

Aircraft vertical take-off system

Abstract: FIELD: aviation.SUBSTANCE: aircraft vertical take-off system (AKVV) consists of unmanned heavy carrier aircraft (BTSN) and two towed on wing tips light multipurpose aircraft (BLMS), each of which has fuselage with front arrangement of engine and two coaxial pull screws mounted in non-retractable landing gear with wheels mounted at cowls on ends of keels of tail fin. AKVV is made based on concept of distributed thrust of different-size rotors (RTRV) at X2+4 scheme, ensuring possibility of transformation with joining flight configuration for proposed and horizontal cruising flight in separate three twin-screw flight configurations for horizontal flight, coupling/uncoupling in air. BTSN and BMLS are made on based on concept of “tailless aircraft” and biplane scheme and is equipped with two top and two bottom keels. Each nacelle has screw with front arrangement inside arched cantilever of first wing. To perform coupling/uncoupling via “wing - in pylon fairing” each BLMS is equipped with corresponding decomposable catcher, having a system of emergency detachment by explosive bolts.EFFECT: simplified longitudinal controllability at hovering, improved transverse controllability at towed flight.2 cl, 2 dwg, 1 tbl

Aircraft Capable of Vertical Take-Off

Abstract: The invention relates to an aircraft (1) which can both take off and land vertically and can hover and also fly horizontally at a high cruising speed. The aircraft (1) has a support structure (27), a wing structure (15), at least three and preferably at least four lifting rotors (5) and at least one thrust drive (9). The wing structure (15) is designed to generate a lifting force for the aircraft during horizontal motion. To achieve this the wing structure (15) has at least one mainplane (3) provided with a profile that generates dynamic lift. The wing structure (15) is preferably designed as a tandem wing structure. Each of the lifting rotors (5) is fixed to the support structure (27), has a propeller (7) and is designed to generate a lifting force for the aircraft (1) by means of a rotation of the propeller (7), said force acting in a vertical direction. The thrust drive (9) is designed to generate a thrust force on the support structure (27), said force acting in a horizontal direction. The lifting rotors (5) can have a simple construction, i.e. they can have a simple rigid propeller for example, and a vertical take-off or hovering of the aircraft can be controlled, in a similar manner to quadcopters, by a simple control of the speeds of the lifting rotors. High cruising speeds can be achieved as a result of the additional horizontally acting thrust drive (9).

Aircraft capable of vertical takeoff

Abstract: An aircraft has a bearing structure, the bearing structure having at least one central fuselage and two pylons each situated at a distance laterally from the fuselage. In addition, the aircraft has a wing structure, at least four hub rotors, and at least one thrust drive. Each hub rotor is fastened to the bearing structure, has a propeller having two propeller blades, and produces, through rotation of the propeller, an upward drive force acting in the vertical direction on the aircraft. The thrust drive is produces a thrust force acting in the horizontal direction on the bearing structure. The pylons each have two hub rotors, the hub rotors being configured to arrest respective propeller blades of a hub rotor in a position relative to the pylons. In the arrested position, the propeller blades of a hub rotor do not extend beyond the outer dimensions of the pylons.

Hybrid-electric drive train for vtol drones

Abstract: A vertical take-off aircraft with a propulsion drive for generating a driving force being effective in a horizontal direction and with a lift drive for generating a lifting force being effective in a vertical direction includes a motor for providing mechanical energy for the propulsion drive and a first generator for providing electrical energy for the lift drive. Moreover, the aircraft includes an exhaust gas turbocharger for the motor with a first turbine being driven by an exhaust gas flow of the motor, wherein the first turbine is configured to provide mechanical energy for the propulsion drive.

Asymmetric four-rotor UAV (unmanned aerial vehicle) and control method thereof

Abstract: The invention discloses an asymmetric four-motor UAV and a control method thereof. According to the asymmetric four-motor UAV, the connection line between two large motor propellers is perpendicular to that between two small motor propellers, and the connection line between the two small motor propellers is shorter than that of the two large motor propellers; the problem of control system divergence is solved through a Smith prediction algorithm; fuzzy control rules are designed and fuzzy inferences are utilized to achieve the optimized adjustment of PID (proportion-integral-derivative) parameters under different flight working conditions. The asymmetric four-motor UAV has the advantages of large take-off weight and good control robustness. The control method of the asymmetric four-motor UAV solves the problems of inaccurate control model and large system interference and reduces the control coupling degree of the four-rotor UAV, thereby reducing the control difficulty and achieving the smooth control of the four-rotor UAV.

Small-sized aircraft with tiltable rotor wings

Abstract: The invention belongs to an aircraft design technology, and relates to arrangement improvement of a small-sized aircraft with tiltable rotor wings. The small-sized aircraft is characterized in that a wing adopts a straight high monowing; four power units are divided into two groups, a first group is a front power unit group, fixed ends of front power unit tilting mechanisms (7c) in front power units (7) are connected with the front edge of the wing (5), and front power unit rotor wings (7a) are haul-in paddles; and a second group is a rear power unit group, fixed ends of rear power unit tilting mechanisms (6c) in rear power units (6) are connected with the rear edge of the wing (5), and rear power unit rotor wings (7a) are boosting paddles. With the adoption of the small-sized aircraft with the tiltable rotor wings, pneumatic disturbance of front and rear wings in the flying process can be eliminated, flying postures and control can be maintained without conventional manipulation of a control plane and a stabilizing plane, so that the aircraft structure is simplified, and the aircraft weight is reduced.