ES2387784B1 - SOIL EFFECT VEHICLE. - Google Patents

Abstract

Ground effect vehicle, comprising two helmets (1) in catamaran configuration, between which a front wing (2) and a rear wing (3) in tandem configuration are located, leaving between said wings (2, 3) a space center (4) hollow, so that the front wing (2) is curved towards the front of the vehicle while the rear wing (3) is curved towards the rear of the vehicle, each wing (2, 3) being able to individually modify its transverse position and inclination with respect to the helmets (1), being able to rotate with respect to rotation directions perpendicular to the helmets (1), and the vehicle comprising propulsion means (5) capable of generating propulsion of the vehicle, which allows high stability and maneuverability of the vehicle, while its cost is reduced.

Description

SOIL EFFECT VEHICLE D E S C R I P C I Ó N

TECHNICAL FIELD OF THE INVENTION

The present invention relates to a ground effect vehicle, which has application in the aircraft industry.

BACKGROUND OF THE INVENTION

Ground effect vehicles, in English Ground Effect Vehicle (GEV), are those that are maintained at a level very close to the earth's surface or the sea during their flight, that is, at very few meters of altitude, by virtue of a reduction of induced friction that occurs as a result of the elimination of the vortices of the wing ends, and by virtue of an air cushion that is at high pressure and is created as a result of the aerodynamic interaction between the wings of the vehicle and the surface itself, what is called the ground effect.

These vehicles are also called ekranoplanos, a word of Russian etymology that refers to the aforementioned "ground effect", as well as vehicles with wings of ground effect, in English Wing-In-Ground-effect (WIG) vehicle.

At present, these ground effect vehicles are considered as intermediate vehicles between a hovercraft, in English Hovercraft, and an airplane, although the International Maritime Organization (IMO) classifies them as vessels.

Unlike an airplane, a ground effect vehicle cannot operate without the intervention of said ground effect, that is, its operation is limited to very low height and determined by the wingspan of its wings, this effect being notable up to an altitude equivalent, more or less, to the wingspan of the ship, and being useful up to an approximate altitude of 0.4 times said wingspan. Thus, a ship with 10 m wingspan could theoretically fly, at cruising speed, up to an altitude of 4 m.

Regarding its operation, unlike

the

planes conventional, that be benefit from a

aspiration

toward above by effect from the lift, the

vehicles

from effect ground they can fly in virtue from a

overpressure that occurs in the front and bottom of its wings, which forms the air mattress that ensures the vehicle's lift. Therefore, while conventional airplanes have wings that narrow towards their ends, in order to avoid the formation of turbulence that reduces the lift of the plane, in ground effect vehicles the wings usually have a constant width, having a configuration more square, in order to maximize the air cushion that forms under these wings. At present, for ground effect vehicles it has been proven that a reverse delta wing configuration is more efficient and stable than the square wing configuration.

In ground effect vehicles, when the vehicle reaches a certain speed it stops being in contact with the water and travels flying over the surface, however the aerodynamic lift is reduced as the flight altitude increases, so to move optimally, it must be maintained at a certain altitude very close to the surface.

The main applications that these vehicles have are both military and civil transport applications, mainly of people, being used as recreational vehicles of various sizes, from the transport of few people to the transport of several hundred on ferry lines.

However, among the inconveniences that presently existing ground-effect vehicles present, it is worth mentioning the fact that they have a low longitudinal stability, as well as that their maneuverability and navigation is not completely safe, especially in already high load conditions. speeds. They also have weight limitations and flight conditions that are largely determined by the width of the wings, so they require

distances

from takeoff Y landing, or splashdown,

relatively

big, the that determines he fan from

conditions of

sea that They allow the flight.

In short, the current configurations of this type of vehicles are difficult to maneuver, and at the lower lateral inclination of the vehicle, for example during a turning maneuver, and given the navigation conditions very close to the surface, accidents of fatal consequences can occur.

Also, another danger that is present in the displacement of these vehicles is the possibility of collision with floating or semi-submerged elements, which implies the need for the vehicle to be able to avoid such floating or submerged objects.

DESCRIPTION OF THE INVENTION

The ground effect vehicle that the invention proposes comprises two helmets in catamaran configuration, which allow the vehicle to float, between which a front wing and a rear wing are located that have configuration in

tandem, leaving between these wings a hollow central space and

understanding

he vehicle media from propulsion able from

generate

the propu lsion necessary for he displacement of the

vehicle.

According to the invention, the front wing of the vehicle has a curved configuration in a single plane, which in an inoperative position can be said to be horizontal or parallel to the plane defined by both helmets, pointing towards the front of the vehicle while the rear wing has configuration curve, also in a single plane, also horizontal, pointing towards the rear of the vehicle.

This doubly curved wing configuration provides the vehicle with certain pressure stability points when the wings are inclined at low speeds. The ground effect generates more pressure under the wings, the bearing capacity being greater the closer the ground is to the wing. In this case, in which the front wing has a curved configuration pointing towards the front of the vehicle, so that the greater the angle of said inclination, the front wing has extreme areas, close to the helmets due to the forward curvature , which are closer to the surface, forming two areas of high pressure, and with the center of the wing away, becoming a zone of low pressure.

In turn, the rear wing is curved in reverse, a low pressure point in the center constituting two low pressure points in the extreme or lateral areas, which produces a high pressure triangle that rests on a low pressure triangle , acting as a tripod when the vehicle travels at low speeds, which contributes positively to facilitating the vehicle's turning maneuvers.

Although this design is optimal to achieve the three pressure points for the support or seat of the vehicle, it is also contemplated that the wings are mounted with their curvatures upside down, that is to say with their ends directed towards the central space, in order to reverse these three points.

Likewise, each wing has the capacity to individually modify its transverse position with respect to helmets, for which the inner face of said helmets has transverse guides.

Preferably, said modification of the transverse position or height of each wing is carried out by means of a mechanism that is located inside the helmets, consisting of an apparatus that rises and falls inside the helmet, being fixed to an arm or axis to which attach the wing.

In turn, each wing has the capacity to individually modify its inclination with respect to helmets, being able to rotate with respect to rotation axes that are perpendicular to the helmets, said inclination can be made mechanically, hydraulically or electrically. These axes of rotation are those that serve as a coupling between the wings and the helmets. According to a preferred embodiment, the mechanism that allows the rotation of each wing housed inside the wing itself.

The curvature of the wings is only in a horizontal plane, so that by tilting the wings and having the hollow central space the effect against the ground begins to take the form of an inverted tripod, when the curvature of the wings causes this effect to appear , which causes stability to increase.

Each wing is curved in one plane, both in its area

or inner perimeter, that is, close to the hole, as per its outer zone or perimeter, both inner and outer areas of each wing being curved towards the same part, that is, in each of the curvatures of both are substantially parallel.

The different curvatures are designed to give stability at low flight speeds, when the wings are curved they maintain a high or medium angle of attack, that is, an inclination of up to 3 O or, so that two tripods of pressure zones are formed higher and lower, depending on how closely the rear edges are to the ground or the sea surface. In this situation, the curves offer different pressures along them, forming areas of high pressure where the wing is closer to the ground, and of lower pressure, where it is further away, forming a tripod of pressure zones that adds stability to the flight . In addition, when the wings are flat, that is to say horizontal, configuration that is adopted for high speed, in the event that a bow lift occurs due to the action of the rotational forces themselves in these vehicles, a danger recognized in this type of ships, carrying the front wing out of the ground effect zone, lift is lost since they are more effective only within the ground effect zone, so that the hollow central space formed by the curvature of the wings collaborates in the ventilation of the front wing, avoiding the channeling of the air under the ship that would be formed if it were a single continuous surface without the hollow central space, thus reducing even more the lift of the front wing, while the rear wing, being inside the ground effect zone at the moment of danger, showing more profile in front of the wind, causes the rear part to rise too, which together with the preliminary lifting of the and the bow, takes the entire ship out of the zone of influence of the ground effect, effectively straightening the ship horizontally, where already, being too high in the air to support itself, it will go down to a level where it once again holds the wings within the area

of ground effect.

Therefore, in accordance with the above, the hollow central space between the wings prevents rotational overturning, since it gives the air a chance to escape without raising the vehicle too much, separating the effect of each wing, so that the rear wing can straighten horizontally the ship once reduced the rotational effect produced as a result of the vehicle being higher.

On the other hand, the fact of being able to change the height and angle of the wings simultaneously is important for the control of the ship at different speeds and in different take-off and landing conditions. Of not having these two possibilities of change of orientation of the wings, like for example any ship of the state of the art that

It only has one option, the ship would be extremely limited in unsuitable conditions, just

where the vehicle of the invention can act in safe conditions by having both attributes at the same time, having a much broader spectrum of flight, takeoff and landing conditions, for which, under high swell conditions it is sufficient to raise the helmets to avoid colliding with the waves.

The possibility is contemplated that the wings have the capacity to transport payload inside. The

helmets

from catamaran allow that he vehicle have

stability

in he air So how that can travel,

land

Y take off respect from the surface of the sea,

It can be adapted to operate on land by incorporating rolling elements in the lower area of these helmets. However, it is the two wings of the vehicle that can be used to transport payload inside, being the helmets with the sole function of keeping the wings in their relative position to each other, keeping them out of the water, which is why,

preferably said helmets are as light as possible, since they do not have the function of providing lift to the vehicle or carrying cargo. The invention does not contemplate that the passage or other cargo is housed in the helmets.

The vehicle of the invention is applicable in multiple transport areas, from private recreational navigation for short trips, with reduced dimensions and electric or diesel propulsion, ferry routes between islands or in areas of a bay for medium distance and hybrid propulsion, to large transatlantic lines with large dimensions for the transport of goods and passengers, with direct propulsion turbines or hybrid media, such as electric and / or diesel means.

The propulsion means may consist of flow or air jet propellants driven by electric, propeller, turbo propeller or turbojet engines, as well as a water jet.

In the case of water jet propulsion, or outboard, its situation at the rear ends of the hulls is contemplated, and they will preferably be used for low speed navigation over the water, since the flight's own propellers are not suitable For this end.

The use of other propulsion sources is also considered, depending on the size and configuration of the vehicle, as well as the conditions and place of use, although a preferred embodiment comprises at least one diesel engine and even propulsion turbines or jet turbines , although any combination between said propulsion means or the use of any other equivalent means of propulsion not specified is also contemplated.

It is contemplated that the propulsion means can rotate, that is, modify their inclination, with respect to axes

perpendicular to the helmets and generate, in addition to propulsion,

aerodynamic lift of the vehicle.

Also, depending on the particular dimensions and characteristics of each vehicle, the use of different mechanisms is contemplated, from rack-and-pinion mechanisms to hydraulic means.

In this way it is achieved that the wings can modify both their angle, inclination, and their height with respect to the catamaran hulls, which allows the wings to be raised with respect to the surface when the vehicle is stationary, so that the weight of the wings rest on the hulls, while in a situation of cruising at maximum speed the wings descend being the weight of the hulls that rests on the wings.

The angle and height of the wings are modified depending on the situation in which the vehicle is located, between the aforementioned stop and cruise or maximum speed flight positions, maintaining at all times an optimal position with respect to the surface depending on the speed, keeping the wings in ground effect, and producing their elevation until the wings are able to support the entire weight of the ship. At that time, and until the maximum speed regime is reached, the height of the vehicle above the surface becomes up to 40% of its wingspan or wing width. It is possible to modify the angle of the wings in order to gain or lose lifting capacity, as required.

In this case, the mechanism to modify the transverse position or height of each wing is located inside the hulls and is fixed to the axis of rotation of each wing.

However, at low speeds it is required that the sea surface be calm and flat, and for that reason the vehicle of the invention is capable of modifying the inclination of the wings, in order to achieve greater lifting capacity at low speeds. , allowing to quickly raise the vehicle to reach an operational altitude in safe conditions.

Be

contemplate that every helmet have a extreme

Forward

from setting hydrodynamics that suffers

narrowing

that favors he takeoff of the vehicle, Y

because each helmet comprises a vertical stabilizer or tail rudder located at its rear end to control the direction of advance of the vehicle. The hulls can be joined by thin, flat aerodynamic beams, between the two front ends and also between the two rear ends of the helmets, only to increase the rigidity of the structure.

The take off is done with the very inclined wings located immediately above the water surface, with the front ends of the helmets raised, as a consequence of the hydroski effect achieved with the thin surface of the front area of the helmets, which maximizes the lifting capacity at low speeds when the vehicle is still on the water. In addition, this configuration allows the front wing to direct the exhaust of the engines that it incorporates towards the rear wing, producing an increase in pressure under said rear wing, which also maximizes the lifting capacity at low speeds, when the vehicle is Still over water.

As the speed increases, the helmets continue to be raised first until they reach the same level as the wings, until the full takeoff is achieved, and then try to ensure that the vehicle gains height as quickly as possible. Then, the high speeds achieved force the angle of inclination to be reduced as it continues to gain altitude but more slowly, in order to obtain a more efficient wing configuration for the maximum speed regime.

Preferably, the propulsion means are fixed on an upper surface of the front wing, since by the angle required for takeoff they direct the jet towards the rear wing producing an increase in pressure under said rear wing on takeoff, as a consequence of the flow of the thrusters, although the provision of thrusters on the rear wings is also contemplated, and even mounted on the hulls, above or on its outer face, always depending on the design and final use of a particular vehicle model.

Obviously, in order to simplify and reduce costs, it is also contemplated that the vehicle has fixed wings whose inclination and position are determined according to the navigation conditions and speed of use of the vehicle.

The tandem configuration wings of the vehicle of the invention have the ability to raise its height very quickly in the presence of an obstacle, by simply increasing its inclination, which at high speed causes the vehicle to be lifted, in addition to the configuration wings Tandem reduce the effect of the recoil moments that produce said rapid lifting of the vehicle, an effect that is not reduced in the ground effect vehicles of the state of the art being able to cause the vehicle to overturn, as described by GW Jorg in `` Tandem Airfoil Flareboat quot ;.

According to a preferred embodiment, the catamaran hulls have the configuration of the hull of a high-speed ship, being longer and having a small area in the front, as a narrowing, to

favor the hydro-ski effect, thus facilitating the lifting of the vehicle during water takeoff maneuvers.

It is contemplated that a front area of the front wing is transparent, said front wing housing a pilot, while the rear wing can accommodate the fuel tanks or the batteries of the vehicle, or any other cargo that is required to be transported.

In the event that the vehicle comprises electric motors, it is also contemplated that the vehicle comprises means for capturing solar energy located on an upper surface of the front wing and an upper surface of the rear wing for feeding the propulsion means, as well as in the upper surfaces of the helmets. In this way, the large horizontal surface available to the wings is used for the arrangement, for example, of photoelectric solar panels that allow charging electric batteries for the supply of the propulsion means, which, in energy terms, makes the vehicle self-sufficient , although the possibility of having a charger in port is also contemplated so that this recharge is complete. To avoid needing such a charger, the ideal would be to make short journeys with long downtimes that allow a complete recharge of the batteries by means of solar panels.

The advantages of the vehicle of the invention are that it allows very fast transport of heavy loads. It self-stabilizes and presents a safer and more comfortable navigation, while it is much cheaper. The combination of helmets with hydroski profile and the angle of attack of the wings by introducing the flow of the thrusters under the rear wing, can improve the take-off distance since these two factors can help lift the vehicle from the water earlier, thus decreasing the surface of the case in contact with water, which constitutes the

Main brake of a quick and short takeoff. It consumes less fuel than an airplane, but as it takes altitude the ground effect disappears, appearing more whirlpools that slow the advance of the vehicle, thereby increasing fuel consumption. It has high security and high speed.

In comparison with the ground effect vehicles of the prior art, the vehicle of the invention has more stability, in addition the design of wings in tandem configuration does not allow excessive elevation outside the area of influence of the ground effect, which is extremely useful to prevent the vehicle from tipping over.

DESCRIPTION OF THE DRAWINGS

To complement the description that is being made and in order to help a better understanding of the characteristics of the invention, according to a preferred example of practical implementation thereof, a set of drawings is attached as an integral part of said description. In an illustrative and non-limiting manner, the following has been represented:

The

figure one.- Sample a view schematic in

perspective of

vehicle of the invention with the wings to half

height

Y half inclination, representing a moment from

transition

between the takeoff Y the flight.

Figure 2.- Shows a schematic perspective view of the vehicle of the invention with the wings in the take-off position, where said wings are fully raised and inclined to favor the take-off of the vehicle.

Figure 3.- Shows a schematic perspective view of the vehicle of the invention with the wings in

position

from flight on he Water, where sayings wings be

they find

totally descend nididas Y in a position

substantially horizontal.

PREFERRED EMBODIMENT OF THE INVENTION

In view of the aforementioned figures, it can be observed that in one of the possible embodiments of the invention the ground effect vehicle that the invention proposes comprises two helmets (1) in catamaran configuration, which allow the vehicle to float and act as a quot; aletasquot; to reduce the vortices that occur at the ends of the wings as a result of the flow of air from high pressure areas to low pressure areas.

Between the helmets (1) there is a front wing (2) and a rear wing (3) that have a tandem configuration, leaving between said wings (2, 3) a central space (4) and the vehicle comprising propulsion means ( 5) capable of generating the propulsion of the vehicle, where said propulsion means (5) can consist of flow or air jet propellers driven by propeller engines, turboprops

or turboreactors.

The front wing (2) has a curved configuration pointing towards the front of the vehicle while the rear wing (3) has a curved configuration pointing towards the rear of the vehicle.

The propulsion means (5) can rotate with respect to axes perpendicular to the helmets (1) and generate, in addition to propulsion, aerodynamic lift of the vehicle.

Each wing (2, 3) has the capacity to individually modify its transverse position with respect to the helmets (1), for which the inner face of said helmets (1) has

cross guides (9). Also, each wing (2, 3) has the capacity to individually modify its inclination with respect to the helmets (1), being able to rotate with respect to rotation axes that are perpendicular to the helmets (1), said inclination can be made mechanically, hydraulically or electrically .

The propulsion means (5) are fixed on an upper surface (11) of the front wing (2).

Each helmet (1) has a front end (6) of hydrodynamic configuration that suffers narrowing that favors the takeoff of the vehicle, and because each helmet (1) comprises a vertical stabilizer (8) or tail rudder located at its rear end (7 ) to control the forward direction of the vehicle.

A front area (10) of the front wing (2) is transparent, said front wing (2) housing a pilot (13).

The vehicle may comprise solar energy collection means located on an upper surface (11) of the front wing (2) and an upper surface (12) of the rear wing (3) for feeding the propulsion means

( 5) •

According to a particular embodiment of a small vehicle, the wings (2, 3) are approximately 7.2 m wide and 1 m thick in order to allow accommodation in the front wing (2) of the pilot (2). 13) in a sitting position, the two wings (2, 3) together with their curvature measure about 13 m. The helmets (1) have a length of 15.5 m, so that they protrude slightly in front and behind the wings (2, 3) in order to favor the ground effect, and 1.2 m wide, by what the total width of the vehicle is about 9.5 m. The take-off speed is around 30-6 km or h while the cruise speed is 150 km / h, with a margin of 20 km / h. The optimal flight altitude, considering that the different speeds depending on the flight conditions, is 40% wingspan, so it is approximately 2.8 m, for a speed of 200 km / h.

In figure 1 the vehicle can be seen with the wings (2, 3) located at medium height and half inclination, representing a transitional moment between takeoff and flight. Previously, in a forward position of the vehicle floating on the water, said wings (2, 3) would be elevated and in a substantially horizontal position. On the other hand in figure 2 the vehicle has the wings (2, 3) in the take-off position, fully raised and inclined, high angle of attack, to favor the take-off of the vehicle. The position of the wings (2, 3) is lowered as the vehicle ascends and its speed increases, until it reaches the situation represented in figure 3, where the wings (2, 3) are shown in flight position on the water, fully descended and in a substantially horizontal position, in order to keep the helmets (1) as far away from the water as the vehicle travels at high speed.

In view of this description and set of figures, the person skilled in the art will be able to understand that the embodiments of the invention that have been described can be combined in multiple ways within the scope of the invention. The invention has been described according to some preferred embodiments thereof, but it will be apparent to the person skilled in the art that multiple variations can be introduced in said preferred embodiments without exceeding the object of the claimed invention.

Claims (5)

l.-Ground effect vehicle, characterized in that It comprises two helmets (1) in catamaran configuration, between which a front wing (2) and a rear wing (3) are located, leaving between said wings (2, 3) a hollow central space (4), so that the front wing (2) is curved in a single plane towards the front of the vehicle while the rear wing (3) is curved in a single plane towards the rear of the vehicle, each wing (2, 3) being able to modify individually its transverse position and inclination with respect to the helmets (1), being able to rotate with respect to rotation directions substantially perpendicular to the helmets (1), and the vehicle comprising propulsion means (5) capable of generating propulsion of the vehicle. 2. A ground effect vehicle according to claim 1, characterized in that the wings (2, 3) have the capacity to transport payload inside. 3. - Ground effect vehicle, according to any of the preceding claims, characterized in that the propulsion means (5) can rotate with respect to rotation axes that are perpendicular to the hulls (1) and generate, in addition to propulsion, aerodynamic lift of the vehicle. 4.-Ground effect vehicle according to any of the preceding claims, characterized in that the propulsion means (5) are fixed on an upper surface (11) of the front wing (2). 5.-Ground effect vehicle, according to any of the preceding claims, characterized in that each helmet (1) has a front end (6) of hydrodynamic configuration that suffers narrowing that favors the take off from the vehicle, and because each helmet (1) comprises a vertical stabilizer (8) located at its rear end (7) to control the direction of advance of the vehicle. 5. A ground-effect vehicle according to any of the preceding claims, characterized in that a front area (10) of the front wing (2) is transparent, said front wing (2) housing a pilot (13). 7. A ground-effect vehicle according to any of the preceding claims, characterized in that it comprises solar energy collection means located on an upper surface (11) of the front wing (2) and an upper surface (12) of the rear wing ( 3) for 15 feeding of the propulsion means (5).