RU2739451C1 - Amphibious with increased carrying capacity - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: invention relates to aircrafts heavier than air. Amphibious aircraft with increased carrying capacity consists of airframe and power plants. Airframe comprises fuselage made in the form of monocoque boat with tail beam and tail unit, wing made free-carrying and trapezoidal in plan with profile of convex-concave shape equipped with flaps and ailerons. Supporting floats are arranged under wing brackets. Above fuselage there is an upper glass hatch. On sides of fuselage there are recesses for arrangement of two main chassis, which are retracted by means of lifting and pressing to side parts of fuselage. In the tail beam rear part there is a recess for the third chassis. Tail beam has a flat upper surface and has a two-keel V-shaped empennage with arrangement of a stabilizer and elevator at the keel top. Airframe is solid composite and is equipped with front areas - spray splitters located at fuselage nose. Wing is equipped with mechanization - slot flaps and consists of three parts - centre wing section and two consoles. Pylons with power plants installed on them are located on the centre wing section. Pilot cabin is brought forward behind plane of screws rotation and is equipped with side doors for crew entry and exit. Fuselage includes crew workstation, front technical compartment, passenger compartment and cargo compartment with loading ramp for loading of small self-propelled equipment. Tail beam has a straight wide flat upper surface with spaced vertical empennage. Sliding hatch-ladle is made on flat tail surface of tail boom.

EFFECT: invention is aimed at possibility of loading and unloading of large and long cargoes.

1 cl, 3 dwg

Description

The invention relates to the field of aeronautics, namely, to aircraft heavier than air, and can be used as a cargo-passenger vehicle, with the possibility of loading small vehicles (snowmobile, ATV, etc.) on their own.

Designed for takeoff both from a hard surface and from the surface of the water, preferably when transporting goods and passengers in areas with an underdeveloped road network, but with a developed water area, as well as for patrolling, rescue operations, ice reconnaissance, monitoring fires, etc. etc.

Known amphibious aircraft - LA-8RS (patent RU No. 169994, В64С 35/00, 02/02/2017), containing a fuselage in the form of a boat with contours, allowing you to place the retractable landing gear without changing the dimensions of the aircraft cabin, and the fuselage is made as a single unit with a vertical keel empennage and is equipped with three doors (hatches): the main access hatch located on the upper part of the fuselage and providing the embarkation and disembarkation of passengers or loading and unloading both afloat and on the ground, and two emergency-release side sealed hatches, a tail boom with a keel and tail assembly, a wing made one-piece with a solid spar and hinged attachment to the fuselage, a power plant of two or more engines with pulling propellers, mounted on the wing, a retractable tricycle landing gear with a front support, transverse stability floats located under the wing, part of which made sealed and serves as fuel tanks and equipped with two-section flaps with the same and the angles of deflection of the outer and inner sections of the flaps and ailerons, and the wingtips are made sealed, while the tail is made cruciform, and a stabilizer with an elevator and trim tabs is attached to the keel.

The disadvantage of this amphibious aircraft should be recognized as imperfect aerodynamic contours of the fuselage, which entails an increase in the drag of the amphibious aircraft.

Known amphibious aircraft Dornier CD-2 Seastar (Canada) (https://www.bjonline.com/aircraft/dornier-seaplane-company-seastar-cd2), which is the largest all-composite amphibious aircraft, is not subject to corrosion, which gives the ability to operate it in both salt and fresh water. The Dornier CD-2 Seastar is powered by two RT-6 turboprop engines and has a cruising speed of 330 km / h and a range of 1300 km. The Dornier CD-2 Seastar allows you to safely land on water at wave heights up to 1 meter. This aircraft has the best flight performance in its class, it is reliable and versatile. The Dornier CD-2 Seastar is FAA and EASA certified.

The main disadvantage of this amphibious aircraft is the parasol wing attachment scheme, which significantly worsens the airframe's aerodynamic quality and increases the drag coefficient (Cx). And also a small entrance hatch located on the side of the fuselage, which makes it difficult to load and unload cargo.

Known amphibious aircraft (patent RU No. 173780, В64С 35/00, 09/11/2017), chosen by the authors as a prototype, containing a fuselage made in the form of a boat - a monocoque, in which the cockpit is located, which unites the crew workplace and the cargo-passenger cabin.

The wing is made cantilever in the form of a single structure, with a convex-concave profile, trapezoidal in plan and equipped with flaps and ailerons. Supporting floats are located under the wing consoles. Engines are located above the wing on pylons in streamlined hoods. The fuselage smoothly passes into the tail boom with two V-shaped keels, at the tops of which there is a horizontal tail, consisting of a stabilizer, an elevator and a trim tab. The two main landing gear legs are retracted into the niches by lifting and pressing against the side parts of the fuselage. At the rear of the tail boom there is a niche for accommodating the tail landing gear. On the rear part of the fuselage, an entrance hatch is made, which is the main means of entering and exiting the cockpit located in the inner space of the fuselage for the crew, passengers and cargo. An upper glazed hatch is located above the crew's workplace in the upper part of the fuselage. The front and side surfaces of the fuselage cockpit are also glazed.

Disadvantages - low carrying capacity, aircraft of a different weight category, due to the small cargo-passenger hatch, it is impossible to load bulky and long cargo. The presence of a single wing structure complicates the routine maintenance of control systems and complicates the dismantling and installation of power plants.

The objective of the invention is to create an amphibious aircraft of increased carrying capacity with universal operating conditions.

The technical result is an increase in carrying capacity without reducing reliability and efficiency during operation; the ability to load and unload bulky cargo; the ability to load and unload small vehicles on their own; ease of entry and exit of passengers; the opportunity sits both on the water surface and on the coastal strips.

The set technical result is achieved by the fact that the amphibious aircraft of increased carrying capacity consists of a glider, which includes a fuselage made in the form of a monocoque boat with a tail boom and tail unit, a wing made of cantilever and trapezoidal in plan with a convex-concave profile, equipped with flaps and ailerons, support floats are located under the wing consoles, an upper glazed hatch is located above the fuselage, niches are located on the sides of the fuselage to accommodate two main landing gear, which are removed by lifting and pressing against the side parts of the fuselage, and in the rear part of the tail boom there is a niche for the third chassis, the tail boom is made with a flat upper surface and has a two-fin V-shaped tail assembly with a stabilizer and an elevator at the top of the keels, as well as power plants. The glider of the amphibious aircraft is one-piece composite and is additionally equipped with front platforms - splash guards located on the nose of the fuselage, the wing is equipped with mechanization - slotted flaps serving to ensure a lower landing speed and consists of three parts - a center section and two consoles, while on the upper part of the center section pylons with power plants installed on them. The cockpit is moved forward beyond the plane of rotation of the propellers and is equipped with side doors for entry and exit of the crew. The fuselage of the aircraft includes a crew workplace, a front technical compartment, a passenger compartment and a cargo compartment with a loading ramp for loading small self-propelled vehicles and other cargo. The tail boom is made straight with a wide flat upper surface with spaced vertical tail, and on the upper flat surface of the tail boom there is a sliding hatch ladder for loading and unloading operations and boarding passengers.

A distinctive feature of an amphibious aircraft with increased payload is that the airframe of the aircraft is completely made of composite material, which increases maintainability and eliminates corrosion during operation in an active environment and improves its aerodynamic qualities. Until now, composite materials have not been used for the production of aircraft of this dimension in Russia. As a composite material, fiberglass and carbon fabrics can be used, as well as the use of special epoxy resins that are not affected by ultraviolet radiation. That provides out-of-hangar storage of amphibious aircraft.

The aerodynamic contours of the fuselage, reaching 15 meters in length, provide a laminar flow around the air flow, which reduces drag. Hydrodynamic contours of the lower part of the fuselage ensure safe, without tendencies to leopard, operation on the water surface in all design modes and exclude water jets from entering the windshield, rotor blades, wing and tail. The fuselage contours also create a sufficient internal usable volume.

The tail boom of this amphibious aircraft of increased carrying capacity is equipped with a retractable gangway, which provides loading and unloading of small vehicles on their own.

The proposed wing design, which has a full span of 20 meters, is a split structure, consisting of three elements - from the center section and two consoles, which improves the maintenance of the control systems in the wing and the installation and dismantling of the aircraft power plants. The wing is equipped with advanced mechanization in the form of flaps and ailerons. The effective profile of the wing console of a convex-concave shape, the presence of developed mechanization in the form of flaps, the absence of wing struts, the placement of engines on the pylons above the wing in total reduces the drag and increases the lift of the wing.

The proposed design of an amphibious aircraft of increased carrying capacity is illustrated by graphic material, where in FIG. 1 is a side view, FIG. 2 is a top view and FIG. 3 - front view, with the following designations used: fuselage 1, center section 2, wing consoles 3, flaps 4, ailerons 5, tail boom with keels and horizontal tail 6, main landing gear 7, niches for main supports 8, tail landing gear 9, a niche for the tail support 10, supporting floats 11, power plants 12, engine pylons 13; horizontal tail 14, stabilizer 15, elevator 16, elevator trim 17; entrance hatch 18, retractable loading and unloading ladder 19, upper glazed hatch 20, entrance area - splash guard 21, wing tips 22, entrance door 23, rudders 24; the cockpit is equipped with two windshields 25 and two side windows 26.

In the basic embodiment, the proposed design of an amphibious aircraft of increased carrying capacity contains a fuselage 1, which has the shape of a boat - a monocoque made of composite material, in which the cabin is located, which unites the crew's workplace and the passenger compartment, separated by a power frame, niches 8 are located on the sides of the fuselage for placement main landing gear in retracted position. The wing is also made of composite material and consists of three component parts, the center section 2 and two wing consoles attached to it 3. The profile of each wing console has a convex-concave shape, trapezoidal in plan and equipped with flaps 4 and ailerons 5. Under the wing consoles 3 are located supporting floats 11. On the upper part of the center section 2 there are pylons 13, on which power plants 12 are mounted in streamlined hoods, which are located in such a way that the planes of rotation of the propellers are located behind the cockpit in a special safe zone. The fuselage 1 smoothly passes into the tail boom 6 with two keels arranged in a V-shape, on the tops of which there is a horizontal tail 14, consisting of a stabilizer 15, an elevator 16 and an elevator trimmer 17. Two main landing gear supports 7 are removed by lifting and pressing against the side parts of the fuselage 1 in niches 8. In the tail boom 6 there is a niche 10 for accommodating the tail support of the chassis 9. On the rear part of the fuselage 1, an entrance hatch 18 is made, which is the main means of entering and exiting passengers and loading and unloading cargo. In the forward part of the fuselage, on both sides, two doors 23 are provided for the entry and exit of the crew members. On the front side parts of the fuselage, there are splash guards 21 that serve simultaneously as steps for the entry and exit of the crew. Above the workstation of the crew in the upper part of the fuselage 1 is an upper glazed hatch 20. The front and side surfaces of the pilot's cabin are also glazed. The glazing of the cabin consists of two windshields 25 and two side windows 26. The design of the tail boom 6 is made single with a flat upper surface providing functional operation both on water and on a hard surface - it is equipped with an opening hatch 18 and a retractable loading and unloading ladder 19, which makes it possible to use it for embarking and disembarking passengers, as well as loading and unloading cargo, including small self-propelled vehicles on their own.

This design of the amphibious aircraft provides increased payload without compromising reliability and efficiency during operation, the ability to load and unload bulky and long cargo, provides convenient entry and exit of passengers, and also ensures safe operation both from the water surface and from asphalt-concrete sites and coastal strips.

The increased operational reliability of the declared design of the amphibious aircraft of increased payload is ensured by ease of piloting and safe operation in all design modes.

Claims (1)

An amphibious aircraft of increased carrying capacity, consisting of a glider, including a fuselage, made in the form of a monocoque boat with a tail boom and tail unit, a wing made of cantilever and trapezoidal in plan with a convex-concave profile, equipped with flaps and ailerons, are located under the wing consoles supporting floats, an upper glazed hatch is located above the fuselage, niches are located on the sides of the fuselage to accommodate two main landing gear, which are removed by lifting and pressing against the side parts of the fuselage, and in the rear part of the tail boom there is a niche for the third landing gear, while the tail boom is made with flat upper surface and has a two-fin V-shaped tail unit with a stabilizer and elevator at the top of the keels, as well as power plants, characterized in that the amphibious airplane's airframe is an all-composite one and is additionally equipped with front platforms - splash guards located on the nose of the fuselage, roof the aircraft is equipped with mechanization - slotted flaps, which serve to ensure a lower landing speed, and consists of three parts - a center section and two consoles, while on the upper part of the center section there are pylons with power plants installed on them; the cockpit is moved forward beyond the plane of rotation of the propellers and is equipped with side doors for entry and exit of the crew; the fuselage of an amphibious aircraft includes a crew workplace, a front technical compartment, a passenger compartment and a cargo compartment with a loading ramp for loading small self-propelled vehicles; the tail boom is made with a straight wide flat upper surface with spaced vertical tail, and on the upper flat surface of the tail boom there is a sliding hatch ladder for loading and unloading operations and boarding passengers.

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