RU2537350C1 - Air cushion vehicle - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to vehicles. Proposed vehicle comprises two connected wings arranged one after another, fuselage, engine, discs and screw propulsor. Fuselage is connected with beam supporting second wing and two-leg wheeled undercarriage. First wing is connected with said beam and equipped with two-leg wheeled undercarriage. Every wheel is equipped with disc and motor with screw propulsor. Said motor is equipped with electrical generator. Said wings and beams can telescope for in-flight control. Wings and/or beams can vary their position for aircraft controllability.

EFFECT: simplified in-flight control.

12 dwg

Description

The invention relates to the field of vehicles intended for movement on the ground and control in flight by changing the overall dimensions of the apparatus.

The apparatus (RF Patent No. 2283795 from 2005.03.21, IPC: B64C 29/00, B64C 27/28, patentee: Durov Dmitry Sergeevich, publ. 2006.09.20) is made according to the flying wing scheme. The apparatus contains a fuselage, a wing, a power plant, including two engines located in the nacelles, three rotary screws in the channels equipped with turning units, and a V-shaped tail unit. The wing is made in terms of a W-shaped with different-sized consoles, respectively, reverse and direct sweep. Two rotary screws are mounted in front of the V-shaped kinks in terms of the leading edge of the wing sweep consoles, and one between the nacelles at the rear of the wing. The sides of the trapezoidal shape in terms of the steering surface are made in the form of a continuation of the trailing edge of the consoles of the reverse sweep of the wing.

The disadvantages of the device. The presence of two engines and three rotary screws with rotation nodes complicate the design of the device and flight control.

The closest solution is an air cushion device (RF Application for Utility Model No. 2004122525 dated July 26, 2004, published: April 10, 2005). The hovercraft includes two wings connected one after the other, the fuselage, the engine, the disks, the propeller, the fuselage is connected to the beam, on which the second wing and the two-wheeled landing gear are located. A screw propeller made in the form of a single rotor with a vertically arranged drive shaft mounted on an articulated suspension in the fuselage, with the possibility of tilting the shaft and, accordingly, the rotor relative to the vertical axis of the fuselage in all directions.

The disadvantages of the prototype. A screw propeller made in the form of a single rotor with a vertically located drive shaft mounted on an articulated suspension in the fuselage, with the possibility of tilting the shaft and, accordingly, the rotor relative to the vertical axis of the fuselage in all directions, complicates the design and flight control.

The technical result of the claimed technical solution is to simplify the design and simplify control in flight.

The technical result is achieved by the fact that the hovercraft includes two connected and located one after the other wings, the fuselage, the engine, the disks, the propeller, the fuselage is connected to the beam, on which the second wing and the two-wheeled chassis are placed, and the first wing is also connected by a beam and equipped with a double-wheeled chassis; each wheel is equipped with a disk, an electric motor with a screw propulsion; the engine is equipped with an electric generator; wings and beams are telescopically retractable for control in flight; when the wings and beams are fully extended / retracted, the engine with the generator is in the center of mass; the engine with the generator are the most massive components of the apparatus, the displacement of the center of mass is insignificant when the overall dimensions of the apparatus change, while the center of mass will be in a different place relative to the changed geometry (geometric center) of the apparatus, the wings and / or beams will change position by a certain angle relative to the screen ( land, water), which ensures the controllability of the apparatus.

The technical solution is presented in the drawings:

Figure 1 - apparatus with fully extended wings and beams, side view;

Figure 2 - apparatus with fully retracted wings and beams, side view;

Figure 3 - apparatus with fully extended wings and beams, top view;

Figure 4 - apparatus with fully retracted wings and beams, top view;

Figure 5 - apparatus with fully extended wings and beams, longitudinal section;

6 - apparatus with fully extended wings and beams, rear view;

Fig.7 is an apparatus with fully extended wings and beams, a top view in isometry;

Fig - apparatus with fully extended wings and beams, a bottom view in isometry;

Fig.9 - apparatus with extended wings and beams, the rear beam is retracted, top view;

Figure 10 - apparatus with extended wings and beams, the front beam is retracted, top view;

11 - apparatus with extended wings and beams, the right wings are retracted, top view;

Fig - apparatus with extended wings and beams, the left wings are retracted, top view,

where the following notation is given:

1 - the first wing;

2 - second wing;

3 - engine;

4 - disk;

5 - screw propulsion;

6 - fuselage;

7 - front beam;

8 - middle beam;

9 - generator;

10 - rear beam;

11 - two-wheeled chassis;

12 - wheel;

13 - axis;

14 - an electric motor;

15 - screw propulsion;

16 - window;

17 - the right front wing;

18 - the right rear wing;

19 - left front wing;

20 - left rear wing;

21 is the center of mass of the apparatus with the wings / beams fully extended / retracted;

22 - geometric center of the apparatus with the fully extended / retracted position of the wings and beams;

23 - the center of mass of the apparatus with the extended / retracted position of the left / right wings, front / rear beams;

24 - the geometric center of the apparatus with the extended / retracted position of the left / right wings, front / rear beams;

25 - diagonal of a conditional rectangle;

26 - conditional rectangle, the sides of which correspond to the overall dimensions of the apparatus.

The hovercraft includes two wings connected and arranged one after the other: the first wing 1 (Figure 1 ... 12), the second wing 2. The wings 1, 2 are made, for example, from a sheet of aluminum alloy D16 with a thickness of 1.5 mm. The apparatus also includes an engine 3, disks 4, a propeller 5. The fuselage 6 is connected to the front beam 7, the engine 3 with the generator 9 is located on the middle beam 8, then the rear beam 10 is located, on which the second wing 2 and the two-wheeled chassis 11 are located. The fuselage 6 is made, for example, of plastic. The first wing 1 is connected to the front beam 7 and is equipped with a double-wheeled chassis 11. Each wheel 12 of the wheel chassis 11 is equipped with a disk 4, an axis 13, an electric motor 14 with a propeller 5. The wings 1, 2 and the beams 7, 8, 10 are telescopically retractable for control in flight, for example using a hydraulic actuator (not shown).

Beams 7, 8, 10 and wings 1, 2 are made in the form of a pipe 15. In the bottom, as well as at the location of the screw mover 5, a window 16 is provided on the beam for creating an air cushion. The right front wing 17, the right rear wing 18, the left front wing 19, the left rear wing 20 extend and retract independently of each other. When the wings 1, 2 and beams 7, 8, 10 are fully extended / retracted, the engine 3 with the generator 9 are located in the center of mass 21 (Figs. 3, 4) and in the geometric center 22 of the apparatus, the center of mass 21 and the geometric center 22 of the apparatus match. When the extended / retracted position, for example the right front, right rear wings, the center of mass 23 (11) and the geometric center 24 do not match. Engine 3 with generator 9 are the most massive components of the apparatus, the displacement of the center of mass 23 is insignificant when the overall dimensions of the apparatus are changed, while the center of mass 23 will be in a different place relative to the changed geometry (geometric center 24) of the apparatus, the wings and / or beams will change position a certain angle relative to the screen (earth, water), which ensures the controllability of the device. Under the geometric center 22, 24 (Figs. 3, 4, 9 ... 12), the intersection of the diagonals 25 of the conditional rectangle 26, the sides of which correspond to the overall dimensions of the apparatus, is taken.

The operation of the device.

The engine 3 (Fig. 1 ... 12) with the generator 9 is turned on, the electric motor 14 with the screw drive 5 starts to rotate, the wheel 12 with the disk 15 starts to rotate in the opposite direction with respect to the screw propulsion 5 in the form of a blade, due to the reactive moment. The device begins to move on the ground. For movement in flight, wings 1, 2 and beams 7, 8, 10 extend telescopically. The revolutions of the screw propeller 5 increase, the speed of the apparatus increases, at the initial stage the apparatus maintains contact with the ground, while the incoming air flow and the air flow from the screw propellers 5 of each wheel 12 create an air cushion under the beam 7, 8, 10, and wings 1, 2 create lift due to the screen effect. Control in flight is carried out by extending or retracting the telescopic wing 1, 2 and / or the telescopic beam 7, 8, 10, while the center of mass 23 with respect to the new overall dimension (geometric center 24) will be in a different place. Since the engine 3 with the generator 9 are the most massive components of the apparatus, the displacement of the center of mass 23 is negligible compared to the change in the overall dimensions (geometric center 24) of the apparatus. For example, when flying in a straight line, both wings 1, 2 are fully extended, for gaining height the front beam 7 (Fig. 9) is fully extended, the rear beam 10 is partially extended, while the center of mass 23 will be at the rear with respect to the changed geometry (geometric center 24 ) apparatus and wings 1, 2 are at a certain angle of attack relative to the screen (earth, water). For landing, the front beam 7 (Figure 10) is partially extended, the rear beam 10 is fully extended, while the center of mass 23 will be in front of the relatively changed geometry (geometric center 24) of the device, and wings 1, 2 are at a different angle of attack relative to the screen (land, water). When turning in flight, for example, to the right, the right wings 17, 18 (Fig. 11) retract, the center of mass 23 appears on the right side relative to the changed geometry (geometric center 24) of the device, the device tilts to the right, air flows turn the device to the right. When turning left, the left wings 19, 20 (Fig. 12) are retracted, the center of mass 23 will be on the left side relative to the changed geometry (geometric center 24) of the device, the device tilts to the left, air flows turn the device to the left.

In contrast to the prototype in the proposed technical solution, the design is simplified by telescopic extension and retraction using a hydraulic actuator.

Unlike the prototype, in the proposed technical solution, control of the device in flight is simplified by changing the overall (geometric) dimensions of the device, while the center of mass in relation to the new overall size (geometric center) will be in a different place, since engine 3 (Figure 1 ... 12) with a generator 9 are the most massive components of the apparatus, the displacement of the center of mass is insignificant compared with the change in the overall dimensions (geometric center) of the apparatus.

The claimed invention is technically feasible, industrially feasible, the prototype tests carried out confirm the achievement of the claimed technical result - simplifying the design and simplifying flight control by changing overall dimensions.

In this regard, the invention corresponds to the level of patentability and is industrially applicable.

Claims (1)

An air cushion apparatus comprising two connected and located one after the other wings, the fuselage, the engine, the disks, the propeller, the fuselage is connected to the beam, on which the second wing and the two-wheeled landing gear are located, characterized in that the first wing is also connected by a beam and equipped with two-wheeled chassis; each wheel is equipped with a disk, an electric motor with a screw propulsion; the engine is equipped with an electric generator; wings and beams are telescopically retractable for control in flight; when the wings and beams are fully extended / retracted, the engine with the generator is in the center of mass; the engine with the generator are the most massive components of the apparatus, the displacement of the center of mass is insignificant when the overall dimensions of the apparatus change, the center of mass will be in a different place relative to the geometric center of the apparatus, the wings and / or beams will change position by a certain angle relative to the screen formed by land or water that provides controllability of the device.

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