RU2308399C1 - Aircraft - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: proposed aircraft has fuselage, two hulls, power plant, mid-mounted wing of low aspect ratio provided with control surfaces and main wing on pylons which is used for connecting the fuselage and hulls in such way that connecting members work in compression; aircraft is also provided with horizontal tail mounted in its nose section, quick-detachable coupling units and parachute systems. Hulls and fuselage are provided with pylons. Main wing is provided with triple-slotted flaps and systems of two-mode control jets at tips of its outer panels; it is articulated on pylons. Horizontal tail is mounted in nose section between fuselage and hulls. Main wing and mid-mounted wing are of low aspect ratio and are spaced apart relative to each other along aircraft axis in such way that aircraft center of mass is located between centers of pressure of main wing and mid-mounted wing.

EFFECT: reduction of mass; improved aerodynamic efficiency; enhanced seaworthiness and afloat maneuverability.

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Description

The present invention relates to the field of aviation, in particular to multihull aircraft. The aircraft can be used as a passenger, cargo, passenger, fire and rescue aircraft, capable of landing both on the water surface and on land. Known adopted for the analogue amphibious aircraft design R.L. Bartini / 1 /, containing the fuselage, connected by a center section with two side bays, floats, wing, plumage and power plant.

However, a significant drawback of this amphibious aircraft is the location of the fuselage and the side compartments of the floats on the same horizontal line, which leads to the center section working on bending and, consequently, to increasing its relative thickness, increasing weight and aerodynamic drag.

There is a group of multihull planes / 2, 3, 4, 5, 6 /, containing interfusel-bearing aerodynamic surfaces, for example, horizontal tail mounted on the nose of the aircraft and made rotary, the main wing mounted on pylons and pivotally mounted on them. However, the totality of the known features in the listed patents does not coincide with the totality of the claimed features.

Of the known technical solutions, the closest one selected as a prototype is an airplane / 7 / containing a fuselage, pitch and heading control surfaces, a vertical surface with rudders and a horizontal bearing surface with elevators, a power plant and parachute systems mounted on it, moreover, the fuselage and at least two additional fuselages, spaced relative to each other in height and horizon, are interconnected by quick-release bearing planes according to the power polygon scheme .

The disadvantages of this aircraft are:

- the biplane arrangement of the wings almost halves their wingspan, which makes it difficult to control the course;

- the installation of a vertical surface with rudders and a horizontal bearing surface fixed to it with elevators creates an additional load on the nose of one of the fuselages, which necessitates its strengthening and, consequently, an increase in weight;

- fastening the wings directly to the fuselage increases interference, which reduces the quality of the aircraft;

- since the fuselages are spaced relative to each other, this leads to an increase in the required area of the control surfaces.

The objective of the invention is to reduce the weight of the aircraft while increasing aerodynamic quality, improving seaworthiness and maneuverability afloat.

The problem is achieved in that in an aircraft containing a fuselage, two boats, a power plant, a middle wing of small elongation with control surfaces and a main wing on pylons connecting the fuselage and boats so that the connecting elements operate in compression, the horizontal tail mounted in the bow parts of the aircraft, quick-disconnect docking units and parachute systems, boats and fuselage are equipped with pylons, the main wing is equipped with three-slot flaps, the span of which is not less than 90% of its scope, and dual-mode jet systems rudders mounted on the end parts of its consoles, the main wing pivotally mounted on the said pylons, and the horizontal tail mounted in the bow between the fuselage and boats with the ability to change the angle of attack at any stage of flight, the main wing and the middle wing are made of small elongation and spaced relative to each other along the axis of the aircraft so that the center of mass of the aircraft is located between the centers of pressure of the main and middle wings.

The invention is illustrated by the accompanying drawings, where:

figure 1 shows a General view of the aircraft from the front;

figure 2 is a General view of the aircraft from the side;

figure 3 is a General view of the aircraft from above.

The aircraft contains the fuselage 1, in which the crew, passengers, equipment and systems for flight are located, in the bow of the fuselage 1 there is a front controllable landing gear and control devices for it. The fuselage 1 can be both from airplanes in use at a given time using their serial rigging and equipment, airplanes that have already been discontinued, and specially designed depending on the TTT for the airplane.

In boats 2, depending on the embodiment of the aircraft are:

- in the passenger version, passengers, equipment providing them with normal flight conditions, stewardesses with the necessary equipment, power supply and communication systems, parachute systems were placed in the bow and tail parts, as well as in the center of gravity of the boat to rescue passengers when the aircraft is divided in an emergency, main chassis and control systems;

- in the cargo version, lengthy and ordinary loads, mail, people accompanying the cargo, cargo loaders are equipped in the rear parts of the boats;

- in the fire variant, tanks with defoaming liquid are placed in the keel of the boats from the bow to the stern, firemen with their equipment, water intake devices are placed inside the boats;

- in the rescue version, inside the boats are operating units, stretchers for the seriously injured, chairs for the injured, medical personnel and rescuers, containers with medicines and medical equipment, portable resuscitation chambers, means of search and rescue on the water - inflatable boats.

Boats 2 can be both from commercially available seaplanes, and specially designed.

The main wing 3 is mounted hinged with the ability to change the angle of attack at all stages of flight on the pylons 4, which are located: lateral on the boats 2, the central one on the fuselage 1. In the main wing 3, there are slats and flaps control routes, caisson tanks with fuel supply . In pylons 4 there are control routes for the main wing 3, caisson tanks with an emergency fuel supply, as well as nodes for hinging the main wing 3, and in the central pylon there is a control mechanism for changing the angle of attack of the main wing 3, as well as quick disconnect nodes for undocking with boats 2 in emergency situation.

The power plant 5 is installed on the upper part of the main wing 3 against the pylons 4 and contains controls and pipelines for supplying fuel.

Inkjet rudders 6 are installed on the end parts of the main wing consoles 3, are powered by compressors of mid-flight engines and contain pipelines for supplying compressed air, regulating dampers, controls, rotary nozzles blocked by dampers, a chamber for “afterburning” compressed air included to increase the thrust of the jet rudders 6 and creating, if necessary, additional moments on the course and roll.

The middle wing of small elongation 7 is installed between the fuselage 1 and boats 2, connecting them. It runs the control and power supply routes from the fuselage 1 to boats 2, the main wing 3, the power plant 5 and the jet rudders 6, the control routes for slats and double-slotted flaps.

In the vertical tail 8, which is installed, if necessary, in addition to the jet rudders 6, control systems for rudders are placed.

The horizontal tail 9 is pivotally mounted between the fuselage 1 and boats 2 and can change its angle of attack at all stages of flight. It houses the control and power supply routes passing from the fuselage 1 to boats 2. The horizontal tail 9 is equipped with slats, double-slotted flaps and elevators.

The main wing 3 and the middle wing of small elongation 7 are spaced relative to each other along the longitudinal axis of the aircraft so that the center of mass 10 of the aircraft is located between the pressure centers 11 and 12 of these wings.

Thanks to this arrangement, balancing of the aircraft, pitch control improves, balancing resistance decreases, the aircraft becomes less sensitive to changes in alignment, the loads on the fuselage 1 and boat 2 are more evenly distributed, facilitating them.

The main wing 3 with pylons 4 mounted on boats and on the fuselage, the middle wing of small elongation 7 are tied together in a strong and rigid structure according to the "power polygon" scheme, which accepts all the current loads and in which all the connecting elements are like a "frame structure" , work mainly on compression-tension, and not on bending, which can significantly reduce the relative thickness of the wings while maintaining the required strength and stiffness, and this reduces the aerodynamic drag of the aircraft and its weight.

On the end parts of the consoles of the main wing 3, systems of “dual-mode” jet rudders are installed according to USSR author's certificates No. 343543 and No. 1338508 with compressed air taken from the compressors of the mid-flight engines, capable of “burning off” the selected air if necessary, increasing the thrust of the jet rudders 6. Since the jet 6 rudders are spaced a great distance from each other and can create a pair of forces when controlling in the direction and roll, then the required traction will be small, and the weight of the system is insignificant with sufficient reliability. In addition, the use of jet control will reduce the area of vertical tail, reduce the load on the rear of the boats 2, which will reduce their weight.

The main wing 3 is equipped with three-slit flaps with a wingspan of at least 90% of the wingspan. This was made possible thanks to the installation of the main wing 3 on the pylons 4 above the fuselage 1 and boats 2 and, therefore, above the water surface, which increased the lifting force of the wing and significantly increased the seaworthiness of the aircraft, and also made it possible to abandon the ailerons, replacing them with jet rudders.

The proposed design of the aircraft due to the separation of the main wing 3 and the middle wing of small elongation 7 on different sides of the center of mass 10 of the aircraft, the installation on the ends of the consoles of the main wing 3 of the dual-mode jet rudder system 6, the supply of the main wing 3 with three-slotted flaps allows:

- create a spatial power circuit that provides a reliable perception of existing loads;

- significantly improve take-off and landing performance;

- provide increased seaworthiness and maneuverability afloat up to a turn on the spot;

- reduce harmful resistance and reduce balancing resistance;

- reduce the weight of the aircraft structure;

- increase the number of passengers and goods carried;

- simplify alignment, increasing the range of acceptable values, improve stability and controllability of the aircraft.

Information sources

1. "Product 14M1P." Technical description, book 1, Flight performance ". Publishing House of TANTK named after Beriev. Taganrog.

2. RF patent No. 2101211.

3. RF patent No. 2099248.

4. RF patent No. 2065376.

5. RF patent No. 2151716.

6. Patent CA No. 1314035.

7. USSR patent No. 1804416 - prototype.

Claims (1)

A plane containing a fuselage, two boats, a power plant, a middle wing of small elongation with control surfaces and a main wing on pylons connecting the fuselage and boats so that the connecting elements work for compression, horizontal tail mounted in the nose of the aircraft, quick-disconnect docking units and parachute systems, characterized in that the boats and the fuselage are equipped with pylons, the main wing is equipped with three-slot flaps, the span of which is at least 90% of its scope, and dual-mode jet rudder systems installed at the end parts of its consoles, the main wing pivotally mounted on the said pylons, and the horizontal tail mounted in the bow between the fuselage and the boats with the possibility of changing the angle of attack at any stage of flight, the main wing and the middle wing are made of small elongation and spaced relative to each other along the axis of the aircraft so that the center of mass of the aircraft is located between the centers of pressure of the main and middle wings.

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