RU2444445C1 - Aviatransformer - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to amphibious vehicles, particularly, to development light amphibious airplane. Proposed aviatransformer has fuselage with streamlined cockpit and bottom section made up of boat bottom with keel, three-wheel retractable undercarriage with controlled front wheel. Two-keel tail unit is attached in cantilever to fuselage on beams. Engine with pusher propeller is fitted on fuselage rear wall closed by fairing. Top wing has outer panels folding along fuselage lateral surfaces, panel tips being located in lower half-plane in center wing section wherein parachute and fuel tanks are arranged. Fuselage central, nose and rail parts make an aerodynamic minor-elongation wing with edges changing, in lower central part, into two parallel constant-width keels with bases, as-folded, are located in wing panel one plane at distance that does not interfere with propeller rotation.

EFFECT: decreased sizes, short takeoff and landing.

9 cl, 6 dwg

Description

The invention relates to the construction of light amphibian aircraft with a short take-off and landing, the possibility of take-off and landing on a snow, water or ground surface. Amphibious aircraft transforming into a car, snowmobile or boat with the overall dimensions of a minibus.

A vehicle is known that can be converted into an aircraft, comprising a body having a longitudinal shape of a streamlined profile, a landing gear, a power unit, a propulsion device, a two-wing tail unit mounted on a variable-length cantilever suspension, and a two-wing wing with end semiconsoles attached to a central parts of the housing with the possibility of their installation in the lateral planes of the housing and within its dimensions with a transverse shaft located in the central lower part of the housing, with pivotally fixed and on this shaft, with semi-cantilevers associated with the corresponding drives, with possible displacement of the hinge axes of the mounting of the semi-cantilevers on the shaft down relative to the longitudinal axis of the shaft by the radius of the cross section of the latter, with the possibility of driving the articulated rotation of the semi-cantilever around the axis of the aforementioned shaft, made in the form of a screw pair (patent RF №4931623 / 11, IPC ВРР 5/02, filed March 15, 91).

The disadvantages of this design include the impossibility of movement, takeoff and landing from the surface of the water and snow.

Known planing boat hull with a vaulted bottom and parallel, not converging in the nose sides, invented at the beginning of the XX century by American designer A. Hickman. Thanks to two keels, which resemble sled runners, the contours are called “sea sleds” (Guide to boats, boats and motors / Edited by G.M. Novak. - 2nd ed., Revised and additional - L. : Shipbuilding, 1982.- 352 p., Pp. 54, 55). Two long keels, immersed in water, contribute to good stability on the course. The disadvantages of the bottom design in relation to amphibious aircraft include the acute form of the base of the keels, not adapted for movement on snow.

Other multi-purpose aircraft are known, including an amphibious aircraft according to the patent of the Russian Federation No. 2272752, IPC ВСС 35/02 dated 2004.09.02 and a light amphibious aircraft according to the patent of the Russian Federation №92007775, IPC В64С 35/00 from 1992.11.25 .

One of the main problems of these aircraft is the lack of convenience of their storage and operation in various living conditions in the absence of equipped runways.

The closest analogue selected as a prototype is the aircraft transformer according to the patent of the Russian Federation No. 2139795, IPC B60F 5/02, filed December 10, 1998, and containing the fuselage, which is a pilot-passenger cabin, rear screw installation, front and rear wheels of the chassis folding right and left wing and tail planes, detachably connected to the fuselage, with a separate compartment for the middle engine and the rear screw installation, with two open compartments for the front and rear wheels of the chassis, made with transmissions and their mechanisms cleaning and release, with a separate nose compartment closed from the external environment and two aerodynamic streamlined windows above the pilot's cabin for mirror observation and control of the take-off and landing directions, with two air chambers that change their volume located in the fuselage, with a take-off and landing device located in the front lower part of the fuselage, including a hydraulic cylinder, a frame and a wheel, pressed after the flight and landing to the bottom of the fuselage, while the left and right wing planes are made with possibly sectional folding using a hydraulic device located in sections of each wing plane, and equipped with front and rear struts, screw units and engines located in front of the main sections, the wheeled chassis is made with skis for movement in snow and water, and the tail part is made with the possibility of folding to form a land vehicle.

The main objective of the invention is the creation of an amphibian aircraft that is convenient to operate with a short take-off and landing on a snow (ice), water, unpaved surface, two-lane road with the possibility of transformation into vehicles for movement on the ground, on water and on a snowy surface with the dimensions of a minibus .

The technical result is achieved by creating a geometric shape of the fuselage; special layout of airframe units; development of chassis, wing designs, engine mounts and wing consoles.

To solve the problem with achieving the specified result in a well-known aircraft transformer containing a fuselage with a streamlined surface lamp and a lower part in the form of a boat bottom with a keel, a three-wheeled retractable landing gear with a controllable swivel front wheel, a two-wing tail unit attached to the fuselage console on beams, a motor with a pusher screw mounted on the rear wall of the fuselage, covered by a fairing, the upper wing with folding along the side surfaces of the fuselage left and right wing consoles with in the lower half-plane, with a center section containing a parachute and fuel tanks, in contrast to the known constructions, the lower central, bow and tail parts of the fuselage are made in the form of an aerodynamic wing of small elongation with sides passing in the lower middle part into two parallel keels of the bottom of constant width with bases located in the same plane, while the wing consoles in the folded position are located at a distance that does not impede the rotation of the screw.

The lantern and the adjacent part of the cockpit in the upper half-plane of the fuselage may have a surface shape defined by the equation

where a, 2b, c is the maximum length, width and height of the lamp along the corresponding coordinate axes 0≥x≥a, -b≥y≥b, 0≥z≥c; n≥1.5, m≥1.5, k≥1.5 - exponents.

The plane of the base of the keels of the bottom in the rear of the fuselage can be beveled at an angle of 5-10 ° relative to the plane of the base of the keels of the bottom in the middle of the fuselage.

The wingtips can be made at an angle of 35 ± 5 ° to the vertical plane passing through the longitudinal axis of the aircraft, and the front edge is beveled at an angle of 50 ± 5 ° relative to the vertical line.

The wing consoles can have rotatable struts of variable length.

The motor mount can be additionally equipped with one or two struts.

In the retracted position, the wheels of the rear chassis can be located above the deck under the motor at the rear of the fuselage cabin.

The lower point of the front wheel in the upper (retracted) position can coincide with the plane of the base of the keels and in this position the wheel is rotary and steered.

The beams of the keels with the folded position of the wing consoles can partially move into the wells in the rear of the fuselage.

Distinctive features of the claimed design are the following features:

- the lower central, nasal and tail parts of the fuselage are made in the form of an aerodynamic wing of small elongation with sides passing in the lower middle part into two parallel keels of the bottom of constant width with the bases located in the same plane;

- wing consoles in the folded position are located at a distance that does not impede the rotation of the screw;

- the lamp and the adjacent part of the cockpit in the upper half-plane of the fuselage may have a surface shape defined by the equation

where a, 2b, c is the maximum length, width and height of the lamp along the corresponding coordinate axes 0≥x≥a, -b≥y≥b, 0≥z≥c; n≥1.5, m≥1.5, k≥1.5 - exponents;

- the plane of the base of the keels of the bottom in the rear of the fuselage can be beveled at an angle of 5-10 ° relative to the plane of the base of the keels of the bottom in the middle of the fuselage;

- wingtips can be made at an angle of 35 ± 5 ° to the vertical plane passing through the longitudinal axis of the aircraft, and the front edge is beveled at an angle of 50 ± 5 ° relative to the vertical line;

- wing consoles can have rotatable struts of variable length;

- the motor mount can be additionally equipped with one or two struts;

- in the retracted position, the wheels of the rear chassis can be located above the deck under the motor behind the fuselage cabin;

- the lower point of the front wheel in the upper (retracted) position can coincide with the plane of the base of the keels and in this position the wheel is rotary and controllable;

- the keel beams when the wing consoles are folded can be partially moved into the wells in the rear of the fuselage.

The implementation of the lower central, fore and aft parts of the fuselage in the form of an aerodynamic wing of low elongation makes it possible to increase the lifting force of an airplane by 10-30%. In this regard, the wing area can be reduced and its span can be reduced to 6–8 m, which helps to reduce mass and air resistance, and, if necessary, allows take-off and landing of the aircraft in the dimensions of a two-lane highway.

The sides, passing in the lower middle part in two parallel keels of the bottom of constant width with the bases located in the same plane, on the one hand, provide stable movement on the water when taking off and landing on the water, on the other hand, these keels are skis when landing on snow or ice, on the third hand, keels prevent the overflow of air with increased pressure from under the fuselage, increasing the lift in flight and enhancing the screen effect during takeoff and landing.

The movement of the aircraft transformer with the wing consoles folded along the fuselage occurs due to the propelling force of the screw. The wing consoles in the folded position, resting on the ends of the center wing at one end and on the outer surfaces of the keels at the other end, are located at a distance that does not prevent the rotation of the screw. The wing consoles in the folded position with the engine running protect people around in case of possible emergency destruction of the propeller blade.

The proposed equation for the shape of the surface of the lantern and the adjacent part of the cockpit in the upper fuselage half plane in the form

It allows a wide range to vary both overall dimensions using the parameters a, b, c, and the completeness of the profile, depending on the exponents n, m, k, to ensure optimal layout of the cabin volume and high aerodynamic quality of the fuselage.

To facilitate separation of the aircraft during take-off from water or from a snowy (icy) surface, the plane of the bottom keel base in the rear of the fuselage can be beveled at a separation angle from the surface (5-10 °) when taking off relative to the plane of the bottom keel base in the middle part of the fuselage. The presence of the proposed keel bevel will contribute to a soft landing when the keels touch the surface of water or snow (ice).

Wing tips made at an angle of 35 ± 5 ° to the vertical plane passing through the longitudinal axis of the aircraft with a leading edge beveled at an angle of 50 ± 5 ° relative to the vertical line, on the one hand, like floats, prevent the aircraft from turning over at large lateral angles of heel on the water , on the other hand, they perform the function of end aerodynamic surfaces (Whitcomb wings) that increase the aerodynamic quality of the wing, on the third hand, the presence of a bevel of the leading edge when the tip moves in water or snow creates a vertical a component of the drag force that pushes the wing out of water or snow.

The wing console with a rotatable strut of variable length allows you to simplify the mechanisms of folding and installing consoles.

Mounting the engine mounts with one or two additional struts to the power sets under the deck in the aft part of the fuselage allows you to increase the rigidity of the screw suspension system.

In flight, when moving on water or in snow (ice), the chassis is in the retracted position. In the retracted position, the wheels of the rear landing gear can be located above the deck under the motor at the rear of the fuselage cabin, which ensures satisfactory flow around the fuselage and optimally position the rear landing gear relative to the center of mass of the aircraft.

The front chassis can be used to control the aircraft when driving on water and on snow. Motion control can be carried out by turning the front wheel in the retracted position. To do this, the lower point of the front wheel in the upper (retracted) position must coincide with the plane of the base of the keels and in this position the front wheel is rotary and steered.

Beams of keels, pushed into the wells in the rear of the fuselage, reduce the length of the air transformer.

These signs are significant, since each of them is aimed at achieving the claimed technical result in accordance with the task. In technical solutions of the previous level of their use is not found.

The invention is illustrated in figures 1-6. Figure 1 in axonometric projection shows an aircraft transformer in flight position with the landing gear extended in a top and side view. Figure 2 in axonometric projection shows an aircraft transformer in flight position with the landing gear extended in a bottom and side view. Figure 3, in side view, shows an aircraft transformer with wing consoles in a folded position with the landing gear retracted to move through water or snow. Figure 4 shows in front view an embodiment of the tip of the right wing. Figure 5 shows a side view of an embodiment of the tip of the right wing. Figure 6 shows the lower part of the keel beam located in the well of the rear of the fuselage.

The air transformer in flight state with the landing gear extended (FIG. 1) consists of a fuselage 1 with a flashlight 2 and a lower part 3 in the form of a boat bottom; three-wheeled chassis 4, 5 with a swivel front wheel 4; two-tail plumage 6 console mounted to the fuselage by means of beams 29 with stabilizer 7; a motor 8 with a pushing screw 9, mounted on the rear wall of the fuselage 10, closed by a fairing 11; the upper wing, consisting of the left 12 and right 13 consoles with tips 14 and center section 15; inside the center section on the left and right sides 16 there are fuel tanks, and in the center 17 - a parachute.

Figure 2 presents the lower part of the fuselage of the aircraft transformer 3 with the aerodynamic surface of the wing of small elongation 18 in flight state with the tricycle landing gear 4 and 5 released, twin-tail plumage 6 mounted on beams 29 with stabilizer 7, wing consoles 12 and 13 with wingtips 14 and center wing 15. In the lower middle part of the fuselage there are two parallel keels of the bottom 19 with the bases 20 located in the same plane. The plane of the base of the keels in the rear of the fuselage 21 can be beveled relative to the plane of the base of the keels 19 at an angle of 5 ÷ 10 °.

Figure 3, in side view, shows an aircraft transformer with wing consoles 12 and 13 in a folded position with the landing gear retracted to move through water or snow. The consoles are located at a distance that does not interfere with the rotation of the screw 9 with the beams of the keels 29. The wheels of the rear chassis in the retracted position can be located above deck 22 under the motor 8 behind the rear wall of the fuselage 10. The front wheel of the chassis 4 in the retracted position can be rotated and steered and the lower the point of the wheel 23 coincides with the plane of the base of the keels 24.

Figure 4 shows a front view of a possible embodiment of the tip 25 by the example of the right wing 13, made at an angle of 35 ± 5 ° to the vertical plane 26, parallel to the vertical plane passing through the longitudinal axis of the aircraft.

Figure 5 shows a side view of the execution of the ending 25 (figure 4) with a front edge 27, beveled at an angle of 50 ± 5 ° relative to the vertical line 28.

Figure 6 shows the beam of one of the keels 30, partially pushed inside the well 31 under deck 22 in the rear of the fuselage 33.

The air transformer as an aircraft is operated as follows. During takeoffs and landings from the ground cover, the chassis 4 and 5 are in the released state and retracted in flight. When taking off and landing from the surface of the water or snow, the chassis 4 and 5 are in the retracted position. Depending on the take-off and landing conditions, it is possible, for example, take-off with the landing gear retracted, and landing with the landing gear released and vice versa.

As a boat or snowmobile, the aircraft transformer is operated as follows. Chassis 4 and 5 are in the retracted position. The wing consoles 12 and 13 are in a folded position along the fuselage and are fixed from displacement by one end at the ends of the center section 15 and the other end by keels 6. The driving force of the aircraft transformer is the thrust of the rotor screw 9. The direction of movement can be controlled by turning the front wheel of the chassis 4.

As a car, an aircraft transformer is operated similarly to a boat or snowmobile, only with chassis 4 and 5 released.

The hull parts of the airframe of the proposed air transformer can have a three-layer structure with sheaths made of woven glass or carbon fiber with a filler made of foam or honeycomb and can be made by laying out the mold with subsequent evacuation and heat treatment. As the engine can be used Rotax-912/914. Avionics, chassis wheels, propeller and parachute are proposed to use purchased, well-known and proven design. The geometry, thicknesses, materials of the airframe parts and joints are determined by special calculations and must comply with the requirements of the Airworthiness Standards.

Claims (9)

1. An aircraft transformer containing a fuselage with a streamlined surface lamp and a bottom part in the form of a boat bottom with a keel, a three-wheeled retractable landing gear with a steered front wheel, a two-tail tail unit attached to the fuselage cantilever on beams, a motor with a pushing screw mounted on the rear wall of the fuselage , closed by a fairing, the upper wing with folding along the side surfaces of the fuselage left and right wing consoles with wingtips in the lower half-plane, with a center section containing a parachute and fuel tanks willow, characterized in that the lower central, nasal and tail parts of the fuselage are made in the form of an aerodynamic wing of small elongation with sides turning in the lower middle part into two parallel keels of the bottom of constant width with bases located in the same plane, while the wing console is folded position are located at a distance not preventing the rotation of the screw. 2. The air transformer according to claim 1, characterized in that the lamp and the adjacent part of the cabin in the upper half-plane of the fuselage have a surface shape defined by the equation:

where a, 2b, c is the maximum length, width and height of the lamp along the corresponding coordinate axes; 0≥x≥a, -b≥y≥b, 0≥z≥c; n≥1.5, m≥1.5, k≥1.5 - exponents. 3. The aircraft transformer according to claim 1, characterized in that the plane of the base of the keels of the bottom in the rear of the fuselage is beveled at an angle of 5 ÷ 10 ° relative to the plane of the base of the keels of the bottom in the middle of the fuselage. 4. The air transformer according to claim 1, characterized in that the wingtips are made at an angle of 35 ± 5 ° to the vertical plane passing through the longitudinal axis of the aircraft, and the front edge is beveled at an angle of 50 ± 5 ° relative to the vertical line. 5. The air transformer according to claim 1, characterized in that each wing console is equipped with rotatable struts of variable length. 6. The aircraft transformer according to claim 1, characterized in that the motor mount is additionally equipped with one or two struts. 7. The air transformer according to claim 1, characterized in that in the retracted position the wheels of the rear chassis are located above the deck under the motor behind the fuselage cabin. 8. The aircraft transformer according to claim 1, characterized in that the lower point of the front wheel in the upper (retracted) position coincides with the plane of the base of the keels and in this position the wheel is rotary and controllable. 9. The air transformer according to claim 1, characterized in that the keel beams when the wing consoles are folded are partially retracted into the wells in the rear of the fuselage.

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