RU2519307C1 - Aviatransformer - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: aviatransformer comprises fuselage with streamlined canopy with bottom shaped to boat bottom, three-wheel undercarriage, engine with pusher propeller, top wing with left and right outer wings folding along fuselage side surface, upper centre-section, empennage with two aerodynamic fins. Fuselage bottom is shaped to boat bottom and comprises boards changing at mid section to two bottom parallel hydrodynamic keels of invariable width with bases located in one horizontal plane. Fuselage bottom part between hydrodynamic keels is composed of short-span airfoil. Said hydrodynamic keels are smoothly conjugated with aerodynamic keels at fuselage tail bottom section.

EFFECT: improved takeoff and landing.

5 cl, 4 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. An amphibious airplane 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 plant, an engine, a two-keel tail unit mounted on a variable length cantilever suspension, and a two-wing wing with end semiconsoles attached to the 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 B60F 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.

Also known is the aircraft transformer according to the patent of the Russian Federation No. 2139795, IPC B60F 5/02, filed December 10, 1998, containing the fuselage, which represents the pilot-passenger cabin, the rear screw installation, the front and rear wheels of the landing gear, folding the right and left wing planes into the tail part 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 mechanisms for their cleaning and release, with a separate one closed from the external environment with a bow compartment and two aerodynamic streamlined windows above the pilot's cockpit for mirror observation and control of takeoff and landing direction, with two air-volume cameras 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, which are pressed after the flight and landing to the bottom of the fuselage, while the left and right wing planes are made with the possibility of sectional folding using hydraulic of the device, located in sections of each wing plane, and equipped with front and rear struts, screw mounts and engines located in front of the main sections, the wheeled chassis is made with skis for movement on snow and water, and the tail part is made for folding to form ground vehicle.

The disadvantages of the proposed air transformer include the complexity of the design, leading to excessive weight and low efficiency during operation associated with the use of multiple engines.

Other multi-purpose aircraft are known, including an amphibious aircraft according to RF patent No. 2272752, IPC ВСС 35/02 dated 02.09.2004, and a light aircraft - amphibian according to RF patent №92007775, IPC ВСС 35/00 dated 25.11 .1992

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 RF patent No. 2444445, IPC B60F 5/02, filed November 19, 2010, containing the fuselage with a streamlined surface lamp and a lower part in the form of a boat bottom with two keels, a three-wheeled retractable landing gear with a controlled swivel front wheel, two-tail tail mounted to the fuselage cantilever on the beams, a motor with a pushing 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 and the left and right wing consoles with wingtips in the lower half-plane, with a center section containing a parachute and fuel tanks, with the lower central, nose and tail parts of the fuselage, made in the form of an aerodynamic wing of small elongation, with sides turning into two in the lower middle part parallel to the keel of the bottom of constant width with the bases located in the same plane, while the wing consoles in the folded position are located at a distance that does not prevent the rotation of the screw. With the ability to perform the lantern and the adjacent part of the cockpit in the upper half-plane of the fuselage in accordance with the equation

, $${\left(\frac{x}{a}\right)}^n+{\left(\frac{|\; |\; |y|\; |\; |}{b}\right)}^m+{\left(\frac{z}{c}\right)}^k=\mathrm{one}$$

,

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≥l, 5, k≥1.5 - exponents. With the ability to perform the plane of the base of the keels of the bottom in the rear of the fuselage, 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. With the possible location of the lower point of the front wheel in the upper (retracted) position in the same plane with the base of the keels and in this position the wheel is rotary and controllable.

The main objective of the invention is to improve the take-off and landing conditions of the aircraft transformer, movement on a snowy and icy surface, landing of the fuselage on the water.

The technical result is achieved by creating a geometric shape of the rear fuselage, a special layout of the front chassis, a special surface coating.

To solve the problem with achieving the specified result in an aircraft transformer containing a fuselage with a streamlined surface lamp and a lower part in the form of a boat bottom with sides passing in the lower part into two parallel hydrodynamic keels of a constant-width bottom with bases in the middle of the bottom located in one horizontal the plane, the plane with the base of the hydrodynamic keels in the rear of the bottom, located in a plane inclined at an angle of 5 ÷ 10 ° to the horizontal plane, the lower part of the fuselage between with the drag keels in the form of the aerodynamic surface of a wing of small elongation, a tricycle retractable landing gear with a steered front wheel in the retracted and released position, a motor with a pushing screw mounted on the rear wall of the fuselage cabin, the upper wing with folding left and right wing consoles along the side surfaces of the fuselage, in the folded position, located at a distance that does not prevent the rotation of the screw, the upper center section containing a parachute in the central part and fuel tanks on the sides a, empennage with two aerodynamic keels, unlike the known structure in the rear lower part of the fuselage hydrodynamic fins smoothly conjugate with aerodynamic keels.

The lower part of the rudders on aerodynamic keels can be lowered to such a level that when moving in water in the planing position it is immersed in water.

The front chassis can be made so that the lower point of the front wheel of the chassis in the upper (retracted) position protrudes beyond the plane of the base of the keels by 10 ÷ 50 mm.

The plane passing through the base of the aerodynamic keels and rudders can be located at an angle of 10 ÷ 15 ° with respect to the horizontal plane.

The lower part of the hydrodynamic keels may be coated with a low coefficient of friction.

The distinctive features of the claimed design of the aircraft transformer are the following features:

- in the lower tail of the fuselage, the hydrodynamic keels smoothly interfaced with the aerodynamic keels;

- the lower part of the rudders on aerodynamic keels can be lowered to such a level that when moving in water in a planing position it is immersed in water;

- the front chassis can be made so that the lower point of the front wheel of the chassis in the upper (retracted) position extends beyond the plane of the base of the keels by 10 ÷ 50 mm;

- the plane of the base of the aerodynamic keels and rudders can be located at an angle of 10 ÷ 15 ° to the horizontal plane;

- a low friction coefficient coating may be applied to the lower part of the hydrodynamic keels.

The implementation of the connection with smooth pairing in the rear lower part of the fuselage of the hydrodynamic keels with the aerodynamic, as the simulation shows, allows to reduce the warming of the tail of the fuselage in water, to reduce the impact force on the surface of the water during landing due to the partial repayment of the impact force protruding beyond the fuselage body with the keels, the first meeting the surface of the water during landing, reduce the mass of the structure by eliminating the beams connecting the aerodynamic keels with the fuselage.

The location of the lower part of the rudders on the aerodynamic keels to the level of immersion in water when moving in water in the planing position allows you to increase the controllability of the aircraft in the take-off section, preceding separation from the water, and at the initial moment of landing on the water.

The protrusion of the lower point of the front wheel of the chassis in the upper (retracted) position beyond the plane of the base of the keels by 10 ÷ 50 mm allows you to increase the controllability of the air transformer when moving on a snowy and ice surface by increasing the pressure on this wheel and increasing the contact area when crushing the pneumatics at the surface.

An angle of 10 ÷ 15 ° in the plane of the base of the aerodynamic keel and rudder relative to the horizontal plane protects against damage to the bottom of the aerodynamic keel and rudder when it hits the ground in case of emergency take-off or landing.

The presence on the lower part of the hydrodynamic keels of the coating with a low coefficient of friction allows landing on a hard uneven coating, such as arable land.

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

The invention is illustrated in figures 1-4. 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. In Fig. 3, a side view shows an aircraft transformer with wing consoles in the folded position and with the landing gear retracted to move through water or snow. Figure 4 shows the lower part of the rudders on aerodynamic keels when moving in water in a planing position.

Figure 1 shows the aircraft transformer in flight state with the landing gear extended, consisting of the fuselage 1 with a flashlight 2 and a lower part in the form of the bottom of a boat 3, a three-wheeled landing gear 4 and 5 with a swiveling front wheel 4, a twin-tail plumage consisting of hydrodynamic keels 6, smoothly interfaced with aerodynamic keels 7, with a stabilizer 8 and rudders 9, motor 10 with a pushing screw 11, mounted on the rear wall of the fuselage 12, closed by a fairing 13, the upper wing, consisting of the right 14 and left 15 consoles with tips 16 and center section 17, inside which fuel tanks are located on the left and right sides 18, and a parachute in the center 19.

Figure 2 presents the aircraft transformer in flight state with the tricycle landing gear 4 and 5 released, the lower part of the fuselage in the form of the bottom of the boat 3 with sides turning into two parallel hydrodynamic keels of the bottom 6 of constant width with the bases in the middle part located in one horizontal plane 20 , the bottom with the aerodynamic surface of the wing of small elongation 21, in the rear lower part of the fuselage, the hydrodynamic keels 6 are smoothly interfaced with the aerodynamic keels 7, with a stabilizer 8, rudders 9, wing consoles 14 and 15 with ends vkami 16 and center section 17. The lower part of the hydrodynamic fins 20, 22, 23 may be coated with a low friction coefficient.

Figure 3 shows an aircraft transformer with wing consoles 14 and 15 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 prevent the rotation of the screw 11. The front wheel of the chassis 4 in the retracted position is rotatable and controllable and is designed so that the lower point of the wheel 24 protrudes beyond the plane of the base of the keels in the middle of the bottom (horizontal plane) 25 by 10 ÷ 50 mm . The wheels of the rear chassis 5 in the retracted position are located above deck 26 under the motor 11 behind the rear wall of the fuselage 12.

Figure 4 shows the lower part of the rudders 9 on the aerodynamic keels 7, smoothly interfaced with the hydrodynamic keels 6. The base 27 of the aerodynamic keel and rudder is located at an angle of 10 ÷ 15 ° to the horizontal plane with the plane of the base of the keels in the rear of the bottom 23, located at an angle of 5 ÷ 10 ^° to the horizontal plane with the base plane of the keels in the middle part of the bottom 25, parallel to the horizontal plane. When moving in water in a planing position, the lower part of the rudders 9 are submerged below the level of the surface of the water 28.

The air transformer as an aircraft is operated as follows. During take-offs and landings from the ground cover, the chassis 4 and 5 are in the released state and retract 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 14 and 15 are in a folded position along the fuselage and are fixed from displacement by one end on the ends of the center section 17 and the other end on the aerodynamic keels 7. The driving force of the aircraft transformer is the thrust of the rotor screw 11. The direction of movement is 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 design with woven glass or carbon fiber lining with a filler made of foam or honeycomb and can be made by laying out the mold with subsequent evacuation and heat treatment. As an engine, for example, a Rotax or Lycoming engine can be used. Avionics, chassis wheels, propeller and parachute are proposed to use purchased, well-known and proven design. The geometry, thicknesses, materials of airframe parts and joints are determined by special calculations and must comply with the Airworthiness Standards.

Claims (5)

1. An aircraft transformer containing a fuselage with a streamlined surface lamp and a lower part in the form of a boat bottom with sides passing in the middle part into two parallel hydrodynamic keels of a constant-width bottom with bases located in the middle part in the same horizontal plane, with the base of the hydrodynamic keels in the rear part of the bottom located in a plane inclined at an angle of 5 ÷ 10 ° to the horizontal plane, the lower part of the fuselage between the hydrodynamic keels in the form of the aerodynamic surface of the wing of small elongation, retractable retractable landing gear with steered swivel front wheel in the retracted and extended position, a motor with a pushing screw mounted on the rear wall of the fuselage cabin, the upper wing with folding along the side surfaces of the fuselage of the left and right wing consoles, in the folded position, located at a distance that does not prevent rotation propeller, the upper center section containing a parachute in the central part, and fuel tanks on the sides, tail unit with two aerodynamic keels, characterized in that it has a tail Second bottom of the fuselage hydrodynamic keels smoothly conjugate with aerodynamic keels. 2. The aircraft transformer according to claim 1, characterized in that the lower part of the rudders on aerodynamic keels when moving in water in a planing position is immersed in water. 3. The aircraft transformer according to claim 1, characterized in that the lower point of the front wheel of the chassis in the upper (retracted) position protrudes beyond the plane of the base of the keels by 10 ÷ 50 mm. 4. The aircraft transformer according to claim 1, characterized in that the plane passing through the base of the aerodynamic keels and rudders is located at an angle of 10-15 ° to the horizontal plane. 5. The aircraft transformer according to claim 1, characterized in that the lower part of the hydrodynamic keels has a coating with a low coefficient of friction.

Images