RU2014247C1 - Flying vehicle - Google Patents

Abstract

FIELD: aircraft engineering. SUBSTANCE: flying vehicle has rotary platform 6 with hoist 7, the platform is mounted on fuselage 1. Axle of rotation 8 of platform 6 is parallel to axis 7 of the flying vehicle. Wings 9 are fastened to axle 8. Axle of rotation 8 is connected to hydraulic cylinders 10 and inertial force accumulators 11. In the horizontal flight the wings may be fixed in a horizontal position. Tail surface 5 has drive-hydraulic cylinder 15 for mounting a fin down the flow induced by a flapping wing. The surfaces are mounted on axle 14. The flying vehicle has stationary wing-pylon 16. EFFECT: improved take-off-landing efficiency. 5 cl, 9 dwg

Description

 The invention relates to aircraft, in particular to aircraft (LA) vertical take-off and landing (GDP).

 A significant number of aircraft is known for GDP, using various methods of creating lifting and driving forces (“Designing Aircraft,” S. M. Eger et al., M., “Mechanical Engineering, 1983, pp. 297-299). The helicopter due to the aerodynamic features of the carrier system has a limited speed and low aerodynamic quality, which decreases sharply with increasing flight speed. Aircraft of GDP should have a thrust-to-weight ratio of at least 1.05 ... 1.45, which leads to an increase in the relative mass of the power plant, a large fuel consumption in takeoff and landing modes and, as a result, a decrease in weight return or flight range. The exhaust jet of engines has a high speed and temperature, which leads to erosion of the runway.

 Known aircraft GDP V-22 company "Bell", containing the fuselage, wing, tail, landing gear and engines with three-blade propellers mounted at the ends of the wing. To ensure vertical take-off and landing, engines with screws rotate relative to the wing (Results of science and technology. "Aircraft". Volume 10, VINITI, M., 1989, p. 42 - prototype).

 The disadvantages of this type of GDP aircraft are the design complexity associated with the rotation of engines, the occurrence of large unbalanced destabilizing moments during the failure of one engine both in takeoff and landing modes and in horizontal flight, which requires the connection of both engines using a long (equal to wing span) and heavy synchronizing shaft. Compared with a single-rotor helicopter of the same size, the area swept by the screws is at least half that size, and therefore the required power is greater. Using propellers as propulsors in horizontal flight limits maximum speeds due to a sharp drop in propeller efficiency. The wing, to the ends of which motors with screws are attached, is used only in horizontal flight. With vertical take-off and landing, the wing is not used, but only prevents the jet from the propeller. The presence of a wing and rotors increases the weight of an empty aircraft.

 The aim of the present invention is to remedy these shortcomings and create an aircraft capable of, along with vertical take-off and landing, to provide high-speed movement and high aerodynamic quality in horizontal flight, that is, a combination of the advantages of a helicopter and an aircraft in one aircraft.

 This goal is achieved in that the aircraft containing the fuselage, tail, landing gear, wings and power unit, is equipped with a rotary platform with a lifting mechanism mounted in the fuselage, with a pivot axis parallel to the Z axis of the aircraft, on which the wings connected with the hydraulic cylinders are pivotally mounted drive waving motions and batteries of inertial forces.

 The waving motions drive is equipped with an additional hydraulic pump drive turbine installed with the possibility of its operation from the aircraft power plant in takeoff and landing modes.

 The drive of the flapping movements is equipped with locking locks for fixing the wing in a horizontal position, while the horizontal required thrust is created by the aircraft power plant.

 The tail unit is equipped with a drive for turning and installing the stabilizer in the flow induced by the flapping wing, and mounted on a horizontal transverse axis.

 The aircraft is equipped with a lower stationary wing-pylon.

 In FIG. 1 shows a General view of the aircraft; in FIG. 2 - take-off position of the wing and plumage; in FIG. 3 - the beginning of the turn of the wing, take-off; in FIG. 4 - horizontal flight; in FIG. 5 - area swept by the wing; in FIG. 6 - the lifting mechanism of the platform with the horizontal position of the wing; in FIG. 7 - the same when turning the wing; in FIG. 8 is a view along arrow A in FIG. 6; in FIG. 9 is a view along arrow B in FIG. 8.

 The aircraft has a fuselage 1, a power plant 2, the main 3 and the tail 4 legs of the landing gear, tail unit 5. A platform 6 is installed at the top of the fuselage, which, using the lifting mechanism 7, can rotate around the transverse axis Z relative to the fuselage 1, changing the angle of inclination of the plane of the plane . The axle 8 of the suspension bracket of the wing consoles 9, the hydraulic cylinders 10 of the wing drive, the accumulators 11 of the inertial forces of the waving consoles are attached to the platform 6. The hydraulic cylinders 10 of the drive are powered by synchronized hydraulic pumps 12, having a drive from additional turbines 13, to which exhaust jets of engines 2 are sent in takeoff and landing modes. The tail unit 5 for takeoff and landing modes can be rotated on the axis 14 using the hydraulic cylinder 15 to ensure controllability. In the lower part of the fuselage 1, a lower stationary wing-pylon 16 is installed, which serves to accommodate fuel in its internal volumes, external suspensions and fasten the main legs of the chassis 3.

 In FIG. 2, 3, 4, 5 show the configuration of the aircraft in different flight modes. On takeoff, the platform 6 with the help of the lifting mechanism 7 is rotated relative to the fuselage 1 so that the plane of the fly 17 was approximately parallel to the ground. During its movement, the wing sweeps the area 18, creating a lifting force 19. The exhaust jet of the engines 20 passing through the additional turbines 13 is directed downward, the tail unit is deflected to increase its efficiency so that the horizontal and vertical tail planes are located along the flow induced by the flapping wing . Then the platform 6 using the lifting mechanism 7 begins to return to a horizontal position. The plane of Mach 17 also rotates, approaching the vertical. The resulting aerodynamic forces 21 of the flapping wing deviates forward, creating traction and accelerating the apparatus. When reaching a speed sufficient for horizontal flight with the wing stopped, the wing consoles can be locked with locks, exhaust jets of engines are sent through conventional nozzles, creating thrust, and the aircraft can fly on an airplane. Landing occurs in the reverse order.

 The flow around the flapping wing, especially in the absence of translational speed, is characterized by extreme non-stationarity.

 Studies have shown that the reason for the large aerodynamic forces created in this case is explained by significant positive accelerations of the flow, when the wing, as it were, involves large attached masses of air. Therefore, the flapping movement of the wing is very advantageous to use for vertical takeoff and landing.

 Aircraft with a flapping wing on takeoff and landing are more effective than GDP aircraft, since the power required for vertical takeoff is the greater, the lower the speed and the greater the mass of exhaust air. An aircraft with a flapping wing, like a helicopter, has the largest area swept by the wing or blades and can throw down maximum air masses at the lowest required speeds. In horizontal flight, such an aircraft has the advantages of an aircraft, since the aerodynamic quality of its wing is much higher than that of a rotor of a helicopter. Thus, an aircraft using flapping wing movement on takeoff and landing combines the advantages of both a helicopter in takeoff and landing modes and an airplane in horizontal flight.

 According to the proposed scheme, aircraft of various purpose can be created. Completed projects of the proposed type of aircraft showed that, compared to similarly designed aircraft, the proposed aircraft has the advantages of aerodrome-free basing, compared with helicopters - the horizontal flight speed is 2 ... 3 times higher, and the flight range is 30 ... 50 percent.

 Compared to Bell V-22 type aircraft (prototype), the proposed aircraft has 40. ..50% higher flight speed, 15 ... 20% less weight than an empty aircraft, due to the fact that the flapping wing is a single carrier system, used on takeoff and landing modes and in horizontal flight.

Claims (5)

 1. Aircraft, containing the fuselage, plumage, landing gear, wings and a power unit, characterized in that it is equipped with a rotary platform with a lifting mechanism mounted in the fuselage, with a pivot axis parallel to the Z axis of the aircraft, on which the wings connected articulated hydraulic cylinders of the drive of moving movements and accumulators of inertial forces.  2. The apparatus according to claim 1, characterized in that the waving motions drive is equipped with an additional hydraulic pump drive turbine installed with the possibility of its operation from the aircraft power plant in takeoff and landing modes.  3. The apparatus according to claims 1 and 2, characterized in that the drive of the flapping movements is equipped with locking locks for fixing the wing in a horizontal position, while the horizontal thrust is created by the power plant of the aircraft.  4. The apparatus according to claims 1 and 2, characterized in that the tail unit is provided with a drive for turning and installing a stabilizer in the flow induced by the flapping wing, and mounted on a horizontal transverse axis.  5. The apparatus according to claim 1, characterized in that it is equipped with a lower stationary wing-pylon.

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