RU2781871C2 - Vehicle with three composite wings - Google Patents

Abstract

FIELD: vehicles.

SUBSTANCE: vehicle for air, water, land, or space vehicles contains a fuselage, front, center, and rear composite wings. Front composite wings have a sweep and a positive transverse V, first inclined planes (2), the first elevators, the first ailerons, and first means (3) of increasing lift force, and they are made with the possibility of connection to central and rear composite wings. Central composite wings are made with second inclined planes (12), the second ailerons, second means of increasing lift force (4), and wingtips (5). Rear wings are located in upper and rear positions relatively to the fuselage and rudder (7) of the vehicle in the forward and downward direction. Each of front wings, central wings, and rear wings is equipped with power plant (1, 6, 11). Central composite wings are located in the upper part of the fuselage, and the transverse V changes so that it is positive, zero, or negative. The change is carried out in a fixed manner in a vehicle structure or before the vehicle is operated. Rear wings are connected in the outer part to front composite wings and central composite wings. Rear composite wings are swept with a negative transverse V, have two third elevators, the third ailerons, two third inclined planes (8), third means of increasing lift force (9), and are connected by rudder (7) to the fuselage.

EFFECT: invention is aimed at reduction in inductive resistance and interference resistance, provision of greater maneuverability, increase in the maximum speed, and reduction in the minimum speed.

9 cl, 1 dwg

Description

Field of invention

This invention relates to an arrangement of three composite wings for air, sea, land or space vehicles.

State of the art invention

Within the prior art of this invention, there is an Argentine patent AR247163 "ASSEMBLY OF COMPOSITE WINGS FOR AIRCRAFT" ("Assembly of composite wings for an aircraft") of the same author as presented, which shows one of the front wings that are in the lower or front position relative to the fuselage or fuselages, moving backwards and upwards, connecting in the outer part with the other two wings; the central wings are located in the upper and central part of the fuselage or fuselages, connecting in the outer part with the other two wings; the rear wings are in the upper and rear position relative to the rudder-fuselage(s), moving forward and downward, connecting in the outer part with the other two wings. Therefore, in this patent, the 3 wings are always located in three different planes and in three different positions. The connection of the wings at their respective tips is provided by edge plates.

Description of the invention

The present invention relates to an arrangement of three wings connected with or without edge plates for air/water/land or space vehicles to reduce inductive drag and interference drag and provide greater maneuverability, independence in fuselage design, optional installation of a propulsion system, optional system landing gear, increasing the maximum speed and reducing the minimum speed, with the ability to reach zero speed or hover. The layout also allows for forward, backward, sideways, up and down flight, or rotation around the vehicle's axes.

The invention of the arrangement of wings, connected with or without edge plates, can be applied to various types of vehicles, such as air vehicles such as an airplane, drone, model, drones, model aircraft, etc.; helicopters, etc.; waterborne vehicles such as amphibious aircraft, amphibious helicopter, etc.; ground vehicles such as cars, motorcycles, etc. or space vehicles such as ships, shuttles, etc.; for transport tasks such as transportation of goods, passengers, equipment, etc.; works such as fumigation, supervision; with the possibility of human control, without human or automatic control, etc.; she has three wings.

Therefore, the present invention describes an arrangement of three composite wings for air, sea, land or space vehicles, which is formed:

- front composite fenders,

- central composite wings and

- rear composite fenders,

moreover, said front composite wings are located in the lower and forward position relative to the fuselage or fuselages of the vehicle, moving in the rearward and upward direction,

wherein said front composite fenders are externally connected to said central composite fenders and said rear composite fenders,

moreover, these front composite wings have a sweep and a positive transverse V and are made with two power plants (1) in them, tilting planes (2), elevators-ailerons and means of increasing lift (3) in order to connect the said central and rear composite wings ,

wherein said central composite wings are located at the top of the fuselage or fuselages of said vehicle,

wherein said central composite fenders are externally connected to said rear composite fenders and said front composite fenders,

moreover, these central composite wings have a sweep and transverse V and are made with two power plants (11) in them, tiltable planes (12), elevators-ailerons and means for increasing lift (4) and wingtips (5),

moreover, said rear wings are located in the upper and rear position relative to the rudder-fuselage or rudders-fuselages of the specified vehicle, moving in the forward and downward direction,

moreover, said rear wings are connected in the outer part with said front wings and said central composite wings,

moreover, said swept rear composite wings with a negative transverse V are made with a system of power plants (6) in them and in connection with a rudder or rudders (7), tiltable planes (8), aileron elevators and means for increasing lift (9) with the purpose of connection with the central and rear composite fenders.

As can be seen, unlike existing solutions, with the help of the present invention, through various specific configurations, it is possible to provide improvements or advantages to air, water, land or space vehicles, such as:

• Increased structural rigidity by joining the wings themselves without plates or elliptical/annular, resulting in lower vehicle mass and hence more range (flight) or less energy for the same range.

• Increased aerodynamic efficiency by connecting the wings themselves without plates or their elliptical/annular shape, ie. greater range (flight) or less energy for the same range. Improved aerodynamic performance through changes in wedge shape and elongation. Ability to provide structural configurations for different types of flight by changing the wedge shape and / or elongation of the three composite wings.

• Improved stability at low and high speeds by changing the sweep of the center wing. As well as increasing or decreasing low and high speeds by changing the sweep of the central wing. In addition, the possibility of improving stability by changing the transverse V of the central wing.

• By increasing the lift forces of the center and rear wings, a significant change in the CG (center of gravity) of the vehicle can be obtained.

• By placing the propulsion system at the junction of the rudder(s) and rear wings, aerodynamic refinement is improved, resulting in greater range (of flight) or less power for the same range.

• Possibility of installing a power plant in the wings in addition to the fuselage allows you to perform maneuvers such as: vertical takeoff and landing; forward and backward movement with a positive/negative "fuselage" angle, with a positive/negative turn, left/right rudder; rotation around its axis by 360° with a positive/negative "fuselage" angle, with a positive/negative turn; lateral movement with a positive/negative "fuselage" angle, with a positive/negative turn, left/right rudder. These maneuvers and their combinations. In other words, maneuvers that other structures cannot perform.

• The ability to increase the surface area of the wing while maintaining structural rigidity allows you to install a solar charging system to power the electrical system (batteries, motors, etc.).

• Ability to build from different types of materials with mass optimization for a given structural rigidity of the structure.

• Due to the fact that the wings themselves are self-supporting structures, this allows for the independence of whether to install as an air, land, water or space transportation system for the transport of goods (passengers, equipment, etc.).

• According to the versatility of movement that the design provides, different types of chassis or similar mechanisms can be installed.

These and other advantages will become apparent in light of the detailed description of the invention.

Brief description of graphic materials

On FIG. 1 is a representative view of the configurations that can be provided by the present invention.

Detailed description of the invention

The elements defined in this detailed description are provided to help understand the invention as a whole. Accordingly, those skilled in the art will appreciate that various variations and modifications of the embodiments described herein may be made without departing from the scope and spirit of the invention. In addition, a detailed description of well-known functions and elements is omitted for reasons of clarity and conciseness.

The present invention relates to a system formed by three connected wings, with propulsion in them and in the rudder(s), tiltable planes, lifting elements and without edge plates, which is made as follows:

Swept front wings with a positive transverse V, made with power plants (1) in them, tilting planes (2), elevators-ailerons and means of increasing lift (3), and with tips curved to connect with the central wings. In swept central wings with tiltable planes and transverse V, made with elevators-ailerons and means of increasing lift (4), and wingtips (5). In swept rear wings with a negative transverse V, made with a system of power plants (6) in them and in connection with the rudder(s) (7), tiltable planes (8), aileron-elevators and means for increasing lift (9), and endings, curved to connect with the central wings. The rudder of the fuselage is connected to the same wings (10).

Various embodiments for the invention are described below.

In one embodiment, the three groups of composite wings (front, center and rear) are connected together without edge plates by flexing or not flexing the wingtips in the case of the front and rear composite wings to connect to the center composite wings; and while the wedge shape and/or elongation of the three groups of composite wings (front, center and rear) may or may not change.

The connection through the said bends of the front and rear composite wings makes it possible to reduce the aerodynamic interference resistance without plates, i.e. reduction of traction energy consumption. In addition, the flow of structural stresses is reduced due to the compression of the stress concentration point and their distribution over the specified contact surfaces, i.e. weight reduction and a corresponding reduction in traction energy.

Moreover, the ability to change the ratio between the root chord and the end chord of the plane of each wing leads to a decrease in inductive resistance, i.e. reduction of traction energy consumption. Similarly, if the span of the plane of each wing increases, there is a decrease in inductive drag, i.e. reduction of traction energy consumption.

In another embodiment, one possible configuration without edge plates is where the front and rear composite fenders are elliptical and/or annular at the elevation joints.

The front and rear composite wings form an ellipse or ring, and when the central composite wings are connected to them, this provides, on the one hand, a reduction in inductive resistance, i.e. reduction of traction energy consumption; on the other hand, the reduction of structural stresses, which leads to a reduction in mass and, consequently, a reduction in traction energy.

In another embodiment, one possible configuration, with or without edge plates, is where edge lift elements can be added to the center composite wings, i.e. the left lift booster is in the left center wing, and the right lift booster is in the right center wing.

By installing said lift increasing elements in the central composite wings, the lift force of said wings is increased and, at the same time, the takeoff and landing speed is reduced and, consequently, the length of the runway is reduced.

In another embodiment, one of the possible configurations with or without edge plates is one in which the leading edge lift elements can be installed in the rear composite wings, i. e. the left lift booster is in the left rear fender, and the right lift booster is in the right rear fender.

Similarly, as in the case of the central composite wings, by installing elements for increasing the lift force in the rear wings, the lift force of these wings is also increased and, at the same time, the takeoff and landing speed is reduced and, consequently, the length of the runway is reduced.

In another embodiment, one possible configuration with or without edge plates is one in which the span of the central wing is larger than the span of the other two wings in both a fixed manner, i.e. in design, and in a dynamic manner, where the influx can be released and removed before vehicle operation.

In the case of a fixed or variable span wing intrusion, it may be carried out in one of the following ways:

• Wingtips (winglets, plates, etc.) may or may not be mounted on the edges of the extended wings.

• Lift elements may or may not be mounted on the extended wings on their leading edges.

• Elevator-aileron elements may or may not be mounted on the extended wings on their trailing edges.

With a larger wingspan of the central composite wings, i.e. when the center wings "extend" in span beyond the connection with the other two wings (front and rear), and considering that the other two wings become, in addition to the wings, support wings for the center composite wings so that the span of the center wings can be increased, and the load on the wings can be reduced by reducing the inductive drag. In the case where the bulge can be released prior to vehicle operation, this makes it possible to have two types of vehicles in one, one with high wing loading (eg agile aircraft) and another with low wing loading (eg glider).

In the case when the specified influx is mobile, i.e. the wingspan can be lengthened and/or shortened during vehicle operation.

In this case, it is an improvement to be able to lengthen the central composite wings during operation, as this will allow, if necessary, takeoff with reduced central composite wings and therefore low parasitic drag during operation; so that the climb and elongation of the central wings increases the parasitic drag in a small proportion, but significantly reduces the induced drag (which prevails at high altitudes due to the low air density). As an example, this situation is useful to have a maneuverable aircraft at takeoff and a glider at altitude.

The following three implementation options for a moving influx are proposed:

• Wingtips (winglets, plates, etc.) may or may not be mounted on the edges of the extended wings.

• Lift elements may or may not be mounted on the extended wings on their leading edges.

• Elevator-aileron elements may or may not be mounted on the extended wings on their trailing edges.

Placing the wingtips on the ribs of the center composite wings provides a reduction in induced drag and, if the wingtips are fitted as wingtips, further improves forward thrust.

At the same time, due to the presence of elevators-ailerons on the trailing edges, it is possible to obtain greater lift and additionally increase maneuverability with minimal aileron deflection and a corresponding decrease in drag. Likewise, extending the center composite wings beyond the junction with the other two wings and the possibility of installing lift enhancing elements at the leading edges in the center extendable wings increases the lift of the wing assembly and at the same time reduces the speed of takeoff and landing and, consequently, reduces the length of the takeoff and landing. bands in addition to reducing inductive reactance.

In another respect, one of the possible configurations with or without edge plates is one in which the center composite wings can be swept, i.e. they can be swept forward and/or swept back, with the following implementations:

• Fixed, ie. in construction, or adjustable before vehicle operation.

The ability to change the sweep, for example, to a position with a forward sweep, allows you to get a higher maximum speed due to the reflection of the shock wave. In the case of swept back, this reduces losses by being able to operate at low speeds, or in other words, improving stability at low speeds. This is more feasible with this design, since the wingtips are fixed by connecting the front and rear wings, which nullifies the effect of sweptback divergence; similarly, in the case where the center wings have a larger span than the front and rear wings, this allows the use of most of the center wings with reverse sweep, since it is fixed by connecting the front and rear wings to eliminate the effect of divergence, and in part of the sagging of the center wings this discrepancy effect can be controlled. There may also be a design in which the inner part of the central wings is swept back and the wings are forward swept, which provides maximum speed.

• Mobility, ie. that their sweep may change, being a reverse sweep and/or forward sweep, or vice versa, passing through the sweep value "0" during operation of the vehicle. This movement can be carried out when the central wings (right and left) move along the root (fuselage) of the wings, and the axis of rotation is the connection of three wings.

The possibility of being swept forward and swept back has been detailed previously; therefore, this document highlights the fact that the center wings can be swept from reverse to straight, given that they move at the root in the fuselage and rotate around its axis in connection with the center and rear wings during operation of the vehicle, which will allow provide maximum speeds, control low speed and reduce minimum speeds by reducing inductive reactance.

In another embodiment, one of the possible configurations with or without edge plates is that in the central composite wings, the transverse V can vary to be positive, zero and/or negative, fixed as the design provides.

Therefore, positive and negative lateral V are improvements that provide better control at low and high speeds.

Another embodiment has a propulsion system or propulsion systems in conjunction with the rudder(s) and rear wing or rudders and rear wings (more than one rudder or more than one "fuselage-rudder", normal rudder, V-tail, etc.) .

If a propulsion/propulsion system is provided, the location in conjunction with the rear composite wings with the rudder or rudders provides traction and an aerodynamically perfect vehicle. In addition, since the propulsion system is fixed in three structural parts (rudder/rudders, left rear wing and right rear wing), and these structures are in turn part of the connected structural system, this allows to reduce stresses and, therefore, mass and traction energy.

In another embodiment, one of the possible configurations with or without edge plates is to install the propulsion system in one or more composite wings through one of these three options or a combination of them:

• The power units may or may not be mounted in the front composite fenders, and said power units may be fixed and/or tiltable. When they are tiltable, they may be tilted in said plane of the wing containing them, or they are tilted by said plane of the wing or part of the plane of the wing containing them.

• The power units may or may not be mounted in the center composite wings, and said power units may be fixed and/or tiltable. If they are tiltable, they can be tilted in the specified plane of the wing containing them, or they are tilted by the specified plane of the wing or part of the plane containing them. Likewise, in the event of a change in sweep, the possibility of rotation or not for the purpose of orientation in accordance with the direction of flight.

• The propulsion unit may or may not be mounted in the center composite wings, and said propulsion unit may be fixed and/or tiltable. If they are tiltable, they can be tilted in the specified plane of the wing containing them, or they are tilted by the specified plane of the wing or part of the plane containing them.

Said propulsion system may be installed in front, center, rear composite wings, or combinations thereof.

Placing a fixed propulsion system in the front, center and rear composite wings allows direct thrust as well as control or compensation of rotation relative to the vehicle's CG.

The placement of the power plant system in the front, central and rear movable inclined composite wings provides the ability to move forward, backward and sideways, up and down, rotation relative to the axes; those. in all directions and with the movement of the fuselage inseparable from them. Additionally, it is emphasized that when aligned with the prevailing direction of flight, maximum speed can be achieved. This is a combination of an airplane and a helicopter, but with more maneuverability than a helicopter, and at the same time with the same speeds as an airplane.

With a movable tilt system containing said propulsion system, the same improvements as listed in the previous paragraph (movable tilt of said propulsion system) can be achieved, but in this case, better energy efficiency is provided, taking into account that the planes, moving together with the power plant system, if necessary, provide a reduction in interference and resistance of the planes when moving the vehicle forward.

In addition, when explaining a propulsion system, it can be defined as a propulsion system such as, for example and without limitation, a turbojet, a turboprop, propellers such as jet nozzles, orientable or not, hypersonic ramjet, ramjet, jet engine, rocket engine, electric engine, fuel engine, etc.

In another embodiment, one of the possible configurations with or without edge plates is the installation of elements that allow the use of solar radiation as energy, such as solar panels or other elements that are integral to the surfaces of the wings.

The fact that it is possible to have large wing surfaces (front, rear and center with ribs) that maintain structural rigidity and low loading on the wings in conjunction makes it possible to have a solar energy system for the vehicle.

In another embodiment, one of the possible configurations with or without edge plates is to design a structure with aeronautical, marine, land or space materials; such as, for example and without limitation, aluminum, steel, wood, composite materials, graphene, etc.

The fact that the connection structure of the three composite wings and fuselage provides a significant reduction in torsional stresses as well as bending stresses means that almost any type of material can be used.

In another embodiment, one of the possible configurations of the fuselage or support structure is the ability to install or not a rear cargo hatch, the ability to install large hatches and windows, and the ability to quickly remove and install a fuselage container or passenger cabin, a structure such as a ground vehicle (in the form of a car , motorcycle, etc.) attached with a self-supporting three-wing structure.

In another embodiment, one of the possible configurations is the ability to install or not, in the group of wings and / or in the fuselage / fuselages of the landing gear (traditional, three-wheeled, two-wheeled, four-wheeled, etc.) and / or racks, and / or skids , and/or floats, and/or supports, etc.

The fact that the design of the connection of the three composite wings and the fuselage provides a significant reduction in torsional stress, allows you to increase the size of the hatches and windows of the fuselage. And since the bending stresses of the fuselage tail cone are reduced by the fact that they absorb it and deflect it to the rest of the structure by connecting the rudder(s) and rear wings, this allows for a cargo hatch that can be opened in flight if required. In addition, since the wings form a connected and independent group, this allows the fuselage container or passenger cabin to be quickly connected to the fuselage or fuselages without changing the vehicle of said cargo.

In addition, the fact that the vehicle can perform vertical takeoff maneuvers like a helicopter or an airplane provides the flexibility to industrially install different landing gear systems, racks, etc.

As can be appreciated, these embodiments may be implemented in a unique or separate manner, or by combining some or all of them.

Claims (23)

1. Vehicle with three composite wings, containing at least one fuselage; front, center and rear composite wings located in the direction respectively relative to the specified fuselage in the lower part, in the upper part and above the upper part, said front composite fenders are externally connected to central composite fenders and rear composite fenders, said front composite wings have a sweep and positive transverse V, first tiltable planes (2), first elevators, first ailerons and first means (3) for increasing lift, and are configured to be connected to said central and rear composite wings, said central composite wings are located in the upper part of said fuselage, and the transverse V is changed so that it is positive, zero or negative, and said change is carried out in a fixed manner in the vehicle structure or before vehicle operation, Said central composite wings are configured to change forward sweep to reverse sweep, wherein said change may be fixed in the vehicle or adjustable prior to vehicle operation, and/or dynamic, i.e. with the possibility of changing from one direction to another during the operation of the vehicle, said central composite fenders are externally connected to said rear composite fenders and said front composite fenders, said central composite wings are made with second tiltable planes (12), second ailerons, second means for increasing lift (4) and wingtips (5), the specified rear wings are located in the upper and rear position relative to the specified fuselage or fuselages and at least one steering wheel (7) of the specified vehicle in the forward and downward direction, the rear wings are connected in the outer part with the specified front composite wings and the specified central composite wings, the rear composite wings are swept with a negative transverse V, have two third elevators, third ailerons, two third inclined planes (8), third means for increasing lift (9), and are connected by at least one steering wheel (7) to the fuselage, wherein each of said front fenders is equipped with at least one power unit (1), and/or each of said central wings is equipped with at least one power plant (11), and/or each of said rear fenders is equipped with at least one power unit (6), and/or the power plant (6) is located at the connection of said rear fenders with said at least one steering wheel (7), respectively. 2. The vehicle according to claim. 1, characterized in that the front, center and rear composite fenders are connected to each other or to the edge plates so as to use the curvature or camber of the wings in the case of front and rear composite fenders in order to connect to the central composite fenders . 3. The vehicle according to claim 1, characterized in that said front and rear composite wings are straight at the edges or form an approximately ellipse or ring, as seen in a vertical projection of said wings. 4. The vehicle according to claim 1, characterized in that the span of the central composite wings is greater than the span of both the front and rear composite wings, while the central composite wings are made with the possibility of disassembly and assembly before the operation of the vehicle, or the central composite wings configured to lengthen or shorten said span dynamically during vehicle operation. 5. The vehicle according to claim 1, characterized in that said power plant system in at least one of the three composite wings, central, front or rear, in connection with the steering wheel or rudders (7), is tiltable, and it tilts in the same plane as the wing containing it, or it is inclined by the same wing plane or part of the plane containing it. 6. Vehicle according to claim. 1, characterized in that at least one of the composite wings contains a solar energy system for powering the vehicle with energy. 7. Vehicle according to claim. 1, characterized in that said arrangement of three composite wings is made containing one or more of the following materials: aluminum, steel, wood, fabric, acrylic, composite materials or graphene. 8. The vehicle according to claim. 1, characterized in that the specified fuselage contains at least one hatch or porthole, or a container or a passenger cabin, or a cargo cabin. 9. The vehicle according to claim 1, characterized in that it has supports selected from the group including chassis, racks, skids, skis, floats.

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