ES2611024B1 - AIRCRAFT - Google Patents

Abstract

Aircraft comprising a structure, two or more wings (2, 5), one or more engines (4, 16), and braces (3, 6), each of which joins a wing with a point of the structure by below the point of union of the wing with the structure, where the braces are able to rotate around its longitudinal axis. The braces fulfill a double function: as a structural reinforcement element for the wings and, simultaneously, as a support element. Turning along its longitudinal axis varies its angle of incidence and generates a variable aerodynamic bearing force. The aircraft can also have fusiform balloons with a gas lighter than air, thus combining the aerodynamic lift of the wings and braces with the aerostatic lift of the fusiform balloon. Preferably the aircraft is of modular construction.

Description

Field of the Invention

The invention relates to an aircraft comprising a structure, at least two wings, one on each side of the structure and at least one engine.

As will be detailed below, the aircraft according to the invention presents a plurality of alternatives and optional improvements, such as the fact of being of modular construction, incorporating one or several fusiform balloons, wings (and rudders) containing in their upper part photovoltaic cells to energize the aircraft, braces arranged under the wings that contain batteries for energy storage, etc. The braces have a mechanism that allows them to rotate around their longitudinal axis, so that they can change their angle of incidence. This allows to reach higher flight levels. In addition, the aircraft has a very low weight (which, in addition, is adjustable to the requirements of each flight thanks to its modular construction) of the set. An adequate combination of several of the mentioned elements allows to obtain aircraft with a virtually indefinite autonomy.

State of the art

Aircraft that include cables, braces and / or braces are known as structural elements that extend from the wings to the fuselage of the aircraft. In some cases, these braces or braces have a flattened shape to reduce aerodynamic drag. However, these elements are fixed and do not participate in the necessary lift force for the aircraft to fly.

There are currently heavier aircraft than the air that mount large wings, which can incorporate photovoltaic cells in their extra alarms, the best known of which is the Solar Impulse, this aircraft however can not assume large payloads and suffers from a certain strength structural that does not allow you to fly safely with mild adverse weather.

US Patent 1,726,062, of 1929, shows an airship incorporating wings, which however are almost embryonic, and the airship continues owing most of its ascensional force to the gas contained in the expandable tanks. Another patent analogous to that mentioned is US 5,823,468 A, which also has small swinging wings at the end of which motors are mounted that allow horizontal or vertical flight.

Exhibition of the invention

The object of the invention is to overcome these drawbacks. This purpose is achieved by an aircraft of the type indicated at the beginning characterized in that the wings are fixed to the structure above the center of gravity of the aircraft, it has two braces, each of which joins a wing with a point of the structure below the point of union of the wing with the structure, and the braces are able to rotate around its longitudinal axis.

In the present description and claims it has been considered that the horizontal stabilizer is a particular case of wing, that is to say that within the "wing" concept, horizontal stabilizers are generally included. That is, for example in relation to the previous section, the braces according to the invention may be joining the horizontal stabilizers with the structure.

There are a plurality of aircraft that have large wings that require some reinforcement elements, such as cables or braces. In the present invention, the braces fulfill a double function: as a structural reinforcement element for the wings and, simultaneously, as a support element, for which they are able to rotate along its longitudinal axis, which allows varying their angle of incidence and, in this way, generate a variable aerodynamic lift force so that it can be adjusted to that required in each case.

Preferably the aircraft comprises at least one fusiform balloon fixed to the structure, suitable for containing a gas lighter than air. In this way, the aerodynamic lift of the wings and, where appropriate, of the braces, is combined with the aerostatic lift of the fusiform balloon. In general, it is advantageous that the aerostatic lift generated by the balloon or balloons is less than the weight of the aircraft without them, that is, the concept is that the balloon's aerostatic lift is a complement to, the aerodynamic lift of the wings and , where appropriate, the braces. In this way, the aircraft according to the invention combines the advantages of airplanes, such as greater maneuverability, less vulnerability to wind, etc., with the advantages of balloons or airships, such as the ability to fly at a lower speed, shorter length of take-off runway, lower energy cost for the transported payload, greater autonomy, greater flight altitude, etc., and, moreover, it is safer since in case of a failure both in the balloon (gas leak) or in the engine, the aircraft can be lowered with a certain control since, in any case, it maintains part of its sustaining force.

Preferably the engine is electric and advantageously the aircraft comprises a plurality of photovoltaic cells arranged on the upper face of the wings, generating electricity for the propulsion of the aircraft and / or for the supply of electrical equipment. In this way it is possible to have an aircraft with great autonomy. In this sense, the combination of electric motors and photovoltaic cells with fusiform balloons is particularly advantageous, since aircraft propelled with electric molars powered by photovoltaic cells usually have a rather limited power, which implies a load capacity and / or also limited autonomy. In this sense, the presence of balloons that help exert the total sustaining force of the aircraft allows the transport of larger payloads and / or greater autonomies.

Preferably, the aircraft has remote control means capable of governing the ship remotely.

Preferably, the braces house, inside, batteries for the storage of electrical energy generated in the photovoltaic cells. In this way the space inside the braces is used.

Preferably the aircraft comprises two fusiform balloons, where between both balloons there is a space suitable to accommodate payload.

Advantageously the payload is fixed to a substructure that has means

10 suitable for displacement of the payload with respect to the structure. Preferably these displacement means are wheels that run along guides arranged in the structure. In this way the distribution of weights can be adjusted in a simple way according to the particular payload of each flight.

15 Preferably the aircraft has at least one steering rudder arranged below the photovoltaic cells. This prevents the steering wheel from shading the photovoltaic cells, achieving optimal use of them.

20 Preferably the aircraft has an engine at each end of the wings. In this way, by varying the power of one engine with respect to the other, a torque is achieved that allows the aircraft to rotate (or aid the rotation of the aircraft) in one direction or another in an optimal way.

25 Preferably, the motor has rotation means suitable for rotating it along a horizontal rotation axis. In this way the engine can generate an additional supporting force, for example that helps in the takeoff and landing phases, or even that helps during the flight (for example in the case of heavy payloads).

A particularly advantageous embodiment of the aircraft of the invention is that it is modular, where the balloon and wings are removably attached to the structure. In this way the entire aircraft can be configured in one way or another depending on the needs of each flight.

Preferably, the structure has telescopic sleepers, suitable for adjusting the width of the space for the payload.

In one of the preferred configurations, the aircraft comprises two balloons and two pairs of wings, each with its corresponding brace.

10 Preferably each of said braces is displaced longitudinally with respect to its corresponding wing. Indeed, it is inevitable that a turbulence zone will be generated in the junction area of the braces with the wings, with the consequent loss of effectiveness. By longitudinally displacing the braces with respect to the wings, this inconvenience is avoided or at least reduced.

Alternatively, or additionally, the aircraft can be designed so that each of the wings has a wingspan greater than the size of its corresponding brace, and preferably has a wingspan greater than 10% of the wingspan of its corresponding brace. In this way, the increase in wing length compensates for the stretch of turbulence in the junction zone between the brace and the wing.

Advantages of the various embodiments of the invention

By combining wings and balloons, there is an aircraft that combines in the same

25 apparatus the advantages of airplanes and airships. From the airplanes the supporting and maneuvering surfaces are taken, namely the wings and the rudders of direction and depth, and from the airships its most characteristic element is taken: its balloons containing gases lighter than air, preferably helium before hydrogen.

30 The hybrid apparatus resulting from this mixture offers optimum flight characteristics, especially those that refer to the assumption of high flight altitudes, or maximum flight dwell times, this is possible in principle by the action of the containers of gas that with its vertical thrust counteract the weight of the device and its payload.

The extradós of the wing can have photovoltaic cells in order to provide the aircraft with a virtually indefinite autonomy, these photovoltaic cells cover the entire wingspan, and can also be arranged on the surfaces provided as horizontal stabilizers. The installed electrical power is, therefore, maximum, and the performance of the photovoltaic cells will increase as the aircraft reaches greater heights, above the orographic accidents of the terrain, pollution and clouds present in the lower layers of the troposphere.

To provide the aircraft with the maximum structural strength, ability to operate at night, and achieve even higher flight altitudes than those offered by its large wings and gas-filled depositories. It has been arranged under the wing of a brace that, in addition to acting as such (as reinforcement of the wing), has the ability to vary its incidence and act as a huge flap. In this way, by adopting angles of incidence greater than the neutral, an increase in lift is achieved, and, on the contrary, if this flap alar is tilted in negative values, the apparatus will lose lift when advancing. Thus, structural rigidity is achieved without adding weight in the form of braces or conventional reinforcements, but what in conventional airplane would be a conventional flap, in the present invention it is used to work as a brace of the upper wing. Another functional characteristic of the The brace according to the invention consists in acting alternately as a spoiler, and therefore introducing the ability to warp the aircraft, and with it the possibility that it can make coordinated turns with the steering rudders. Finally, the brace according to the invention is capable of containing the batteries necessary for night flight.

The concept of wing and flap alar is replicated in the stabilizing elements, so the stabilizer also has photovoltaic panels on top, and batteries in the corresponding braces. In this case, the braces, by varying their angle of incidence, are suitable to cause the pitching of the aircraft. It is possible that the stabilizer acts additionally, exclusively or alternatively as a vertical compensator.

To achieve the necessary propulsion, electric motors are used associated with the batteries placed inside the braces and the photovoltaic cells. These motors are located at the ends of the wings and stabilizers. As it is also possible to vary its incidence, it is feasible to undertake vertical take-offs when the motors are in vertical position and horizontal displacements, if the millors have rotated to this position.

While the modular capacity would allow the aircraft to operate with a single balloon, the preferred embodiment for providing more remarkable performance in all fields includes two balloons. In this way there is space between the two sectors to locate the payload, which may be, for example, cameras focused on the earth or space, communications antennas, and cargo in the form of goods to transport. It is not discarded, as it is perfectly possible to install an appropriate container between the two balloons that can facilitate this personal transport.

In order to add greater possibilities for maneuvering the apparatus, it has been arranged that the payload be attached to a container with wheels, and these wheels placed in longitudinal guides, so that the position of the center of gravity of the aircraft can be varied. With this, it is possible to facilitate the pitching and help the horizontal stabilizer, in case its contribution is not sufficient for the maneuvers of gain or loss of height. The position of the load can be fixed on the ground, and as an additional alternative it will also be possible to move it when the Aircraft is flying.

Thanks to the modularity of the aircraft, the supporting surfaces can be moved forward or backward, according to the loads carried by the aircraft, in this way it is possible to place the lift center and the center of gravity in the optimal location that Deliver the best performance, or even dispense with a portion of these items if they are not necessary. In this way, the horizontal stabilizer assembly can be dispensed with by removing it from its usual position, or disassembling the alar assembly and transforming the stabilizer assembly into an alar assembly if it is not necessary to fly at great heights.

Taking into account the load to carry, in case it is wider or less, it is feasible to separate or bring the two parts of the aircraft closer together.

To stiffen the assembly, two extreme aerodynamic surfaces can be used, one acts as a canard, and the other as an auxiliary depth rudder. These surfaces can be equipped with compensating functions, in case the load introduced, or the speed of the aircraft so requires.

In order to enable the directional maneuver of the apparatus, it is entrusted to steering rudders located at the bottom of the aircraft. In this position they do not cause shadows on the photovoltaic panels located on the wings.

The modularity of the machine allows to operate it from its minimum expression (a simple structure with wings and braces (of variable incidence) for short translation flights without the need to transport large loads) to its maximum potential (two fusiform balloons, with two endowed wing assemblies of photovoltaic panels and batteries that allow flying at high altitude for a virtually undefined time.

Brief description of the drawings

Other advantages and features of the invention can be seen from the following description, in which, without any limitation, preferred embodiments of the invention are mentioned, mentioning the accompanying drawings. The figures show:

Fig. 1, a perspective view of a first embodiment of an aircraft according to the invention.

Fig. 2, a perspective view of a second embodiment of an aircraft according to the invention.

Fig. 3, a perspective view of a third embodiment of an aircraft 5 according to the invention.

Fig. 4, a side elevation view of the junction area of the brace and the wing to the structure in the aircraft of Fig. 3.

10 Figs. 5 and 6, a partial perspective view of a wing and its corresponding brace with the brace in two different positions.

Figs. 7 and 8, a side elevation view of the junction area of the brace and the wing to the structure of the aircraft, corresponding to Figs. 5 and 6, respectively.

15 Fig. 9, a top plan view of a fourth embodiment of an aircraft according to the invention.

Fig. 10, a partial perspective view of the aircraft of Fig. 9.

Fig. 11, a perspective view of a fifth embodiment of an aircraft according to the invention.

Fig. 12, a side elevation view of the aircraft of Fig. 11, with the engines 25 rotated relative to a horizontal axis.

Fig. 13, a front elevation view of a sixth embodiment of an aircraft according to the invention with displacement means capable of displacing said payload relative to said structure

Fig. 14, an enlargement of the central part of the view of Fig. 13.

Fig. 15, a perspective view of the displacement means of the aircraft of Fig. 13.

Figs. 16 and 17, two exploded perspective views, showing the modular design of the aircraft.

Figs. 18 and 19, a partial front elevation view of an aircraft with telescopic sleepers.

Fig. 20, a perspective view of a seventh embodiment of an aircraft according to the invention.

Fig. 21, a perspective view of an eighth embodiment of an aircraft according to the invention.

Fig. 22, a perspective view of a ninth embodiment of an aircraft according to the invention.

Fig. 23, a perspective view of a tenth embodiment of an aircraft according to the invention.

Detailed description of embodiments of the invention

In Fig. 1 an aircraft is shown with the basic elements of the invention: a structure, with two stringers 12, which forms the fuselage of the aircraft, wings 2, 5 on both sides of the structure and fixed to the structure by above the center of gravity of the aircraft, a plurality of engines 4 (preferably electric), braces 3, 6, each joining a wing 2, 5 to the structure below the point of attachment of the wing 2, 5 a the structure. The braces 3, 6 are able to rotate about its longitudinal axis, thus varying its angle of incidence. This aircraft also has a plurality of photovoltaic cells 17 above its wings 2, 5, and the engines 4 are arranged at the ends of the wings 2, 5. It also includes a plurality of batteries (not shown in Figs.) which are housed inside the braces 3, 6 and that accumulate the electrical energy generated in the photovoltaic cells 17.

A variant of the aircraft of Fig. 1 is shown in Fig. 2, with two wings instead of 4. It also includes two canard surfaces 13, 14. As can be seen, the modular design of both alternatives makes it possible to transform the aircraft from An alternative to the other with great ease. In fact, as will be seen in the remaining alternatives, the modular concept is extensible to all of them, which means that the aircraft can be transformed in many ways, being able to adjust to the requirements of each flight.

In Figs. 16 and 17 show exploded views of another embodiment, in which the modular concept of the aircraft is clearly appreciated. In Fig. 16 you can see the assembly alar 2, 5 disassembled and about to be mounted on stringers 12 of the structure, which has a suitable slot so that they can enter through one end of the structure and move through it to the position appropriate, according to the final position of the payload, its weight and its dimensions. The modularity expressed in the alar assembly also extends to the horizontal stabilizer 5, which has the same ability to mount on the stringers 12, and run forward, or backward at will. In Fig. 17, the alar assembly and the stabilizer can be seen already arranged in the stringers 12, and about to be mounted the canard surfaces 13, 14. The holes of the stringers 12, as well as a good part of the holes introduced in the different parts that make up the aircraft, have as main purpose to reduce the weight of the piece, and as a whole the weight of the aircraft. In the case of the stringers 12, these holes are also used to connect the right and left sector of the aircraft with two balloons. This connection is made thanks to the sleepers 15, which, thanks to their telescopic properties, can shrink or lengthen according to the volume of the transported cargo. These sleepers extend from a threaded hole of one of the stringers to the corresponding threaded hole of the other stringer, thus enabling the aircraft with two balloons to remain attached (see also Figs. 18 and 19). The stringers 12 are a little longer than the gas tanks, in this way at the ends it is possible to include canard surfaces 13, 14, which act as auxiliary rudders, since if we move them properly we will be able to govern the aircraft in the vertical plane Other auxiliary functions of these canard surfaces may be the compensator and / or the structural reinforcement of the stringers 12.

The aircraft of Fig. 3 additionally comprises two fusiform balloons 1. These balloons contain a gas lighter than air (preferably helium). Between both balloons 1 there is a space suitable to accommodate the payload. In addition, the struts 3 are displaced longitudinally with respect to the corresponding wing 2, as can be seen in more detail in Fig. 4. This aircraft also comprises at least one engine, which has not been shown in Fig. 3 for greater simplicity of it.

In Figs. 5 to 8 shows a brace 3 arranged with a positive incidence angle (Figs. 5 and 7) and the same brace 3 with a negative incidence angle (Figs. 6 and 8), after having been rotated around its longitudinal axis .

The aircraft alternative of Figs. 9 and 10 has an additional reaction engine 16 to the propeller motors 4.

In Figs. 11 and 12 shows an example of an aircraft with rotating means that allow its engines to rotate around a horizontal axis. The arrangement of the motors 4 at the end of the wings facilitates their rotation. In this way, vertical take-offs can be achieved, abruptly braking the aircraft in the air and even changing the direction of travel without the need to turn the aircraft. To stabilize the aircraft in the vertical plane, horizontal stabilizers 5 are available, which also have photovoltaic cells on their upper face, and to head the aircraft, the corresponding braces 6 are available, whose rotational movement allows the bow or the bow to be raised or lowered. stern of the aircraft and therefore win

or lose flight height. The brace can also serve as a compensator. This aircraft also has telescopic sleepers 15 (see also Figs. 18 and 19) that allow adjusting the width of the space between both balloons 1, that is, the space for the payload. Also shown in Fig. 12 are steering wheels

7.

Another aircraft according to the invention is shown in Fig. 13, with 4 wings with their corresponding braces, a plurality of tandem engines and two fusiform balloons. This aircraft also comprises a substructure 8 with displacement means capable of displacing the payload with respect to the structure. These displacement means are formed by wheels 10 that run guides 11 (Klein type or similar) arranged in the structure. In this way the payload can be moved along the structure, and fixed in the most appropriate place to achieve an optimal weight distribution. In fact, in the embodiment of Fig. 13 there are two substructures 8, 9, one upper and one lower. These substructures are formed with bars with holes that can accommodate various widths and lengths, according to the payload to be transported. Thus the upper substructure 8 could carry space observation devices, while the lower substructure 9 could carry them for terrestrial or maritime observation.

Figs. 20 to 23 show other possible configurations of the aircraft according to the invention:

~ with a single balloon 1, with four wings without photovoltaic cells (Fig. 20),

~ with two balloons and two wings with photovoltaic cells (Fig. 21),

~ with two balloons and two wings with photovoltaic cells and with a plurality of motors that can be rotated around a horizontal axis and that are not only fixed to the wings but some of them are fixed to specific supports (Fig. 23),

~ the aircraft of the alternative of Fig. 22 has four wings and it is observed that the braces 3 corresponding to the longer wings do not extend to the end of the corresponding wing but instead join it at an intermediate point, in other words, the wing has been elongated to compensate the loss of effectiveness of the wing / brace junction section.

In general, all the alternatives shown are designed to be controlled through remote control means. However, any of the alternatives of the aircraft according to the invention could be equipped with a cockpit for a pilot and directly commanded by him.

The presented invention offers advantages for multiple uses, when the aircraft is configured to its maximum potential, especially those uses where long flight autonomies may be required. Currently, very few remote control airplanes can boast outstanding autonomies. The observation of traffic, volcanic activity, meteorology, or space observation are just a few of the many applications that an aircraft could optimally develop according to the invention. Being able to operate at high altitudes and autonomously, make it a more viable and economical alternative to operate for a wide range of missions than other current machines such as artificial satellites and helicopters. Another additional advantage is that it can optimally overcome the legal restrictions to which the current UAVs (Unmanned Aerial Vehicle) are subjected, this is because a loss of control of a traditional UAV can result in damage to third parties, while an aircraft according to the invention, on the other hand, can descend smoothly to the ground if, for example, control over it has been lost due to battery depletion, since the gas tanks will always give positive lift to oppose the weight of the device The modularity offered makes it possible to adapt the configuration of the aircraft to the demands of the mission to be undertaken.

Claims (1)

1 -Aircraft comprising a structure, at least two wings (2, 5), one on each side of said structure, and at least one engine (4, 16), characterized in that:

-

said wings are fixed to said structure above the center of gravity of the aircraft, - it presents two braces (3, 6), each of which joins a wing with a point of the structure below the point of attachment of said wing with the structure, and said braces are able to rotate about its longitudinal axis.

2 -Aircraft according to claim 1, characterized in that it comprises at least one fusiform balloon (1) fixed to said structure, suitable for containing a gas lighter than air. 3 -Aircraft according to one of claims 1 or 2, characterized in that said motor (4) is electric. 4 -Aircraft according to any of claims 1 to 3, characterized in that it comprises a plurality of photovoltaic cells (17) arranged on the upper face of said wings, generating electricity for the propulsion of the aircraft and / or for feeding a electrical equipment 5 -Aircraft according to any of claims 1 to 4, characterized in that it has remote control means 6 -Aircraft according to any of claims 1 to 5, characterized in that said braces house, inside, batteries for the storage of electrical energy generated in said photovoltaic cells. 7 -Aircraft according to any of claims 1 to 6, characterized in that it comprises two fusiform balloons, where between both balloons there is a space suitable for accommodating payload. 8 -Aircraft according to claim 7, characterized in that said payload is fixed to a substructure (8, 9) having displacement means (10) suitable for moving said payload with respect to said structure. 9 -Aircraft according to any of claims 4 to 8, characterized in that it has at least one steering rudder (7) arranged below said photovoltaic cells. 10 -Aircraft according to any of claims 1 to 9, characterized in that it has an engine at each end of said wings. 11 -Aircraft according to any of claims 1 to 10, characterized in that said motor has rotation means suitable for rotating said motor along a horizontal rotation axis. 12 -Aircraft according to any of claims 1 to 11, characterized in that it is modular, wherein said balloon and said wings are removably attached to said structure. 13 -Aircraft according to any of claims 1 to 12, characterized in that said structure has telescopic sleepers (15), suitable for allowing the adjustment of the width of the space for the payload. 14 -Aircraft according to any of claims 1 to 13, characterized in that it comprises two balloons and two pairs of wings, each with its corresponding brace. 15 -Aircraft according to any of claims 1 to 14, characterized in that each of said braces is displaced longitudinally with respect to its corresponding wing. Aircraft according to any one of claims 1 to 14, characterized in that each of said wings has a wingspan greater than the wingspan of its corresponding brace, and preferably has a wingspan greater than 10% to the wingspan of its corresponding brace. . .