• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The present invention refers to a set of three wings joined with or without marginal plates for aerial, aquatic, terrestrial or space vehicles, in order to reduce induced resistance and interference, greater maneuverability, independence in the design of the or fuselage, installations or not of systems of the propelling plant (s), whether or not it has a landing gear system, maximum speed increase, minimum speed reduction that can reach zero or stationary flight; perform flights both forward, backward, sideways or up and down, or turns on their axes. (Machine-translation by Google Translate, not legally binding)
    公开号:ES2711660A1
    申请号:ES201731283
    申请日:2017-11-02
    公开日:2019-05-06
    发明作者:Ottonello Carlos Cesar Manterola
    申请人:Ottonello Carlos Cesar Manterola；
    IPC主号:
    专利说明:

    [0001]
    [0002] Set of three composite wings for air, water, land or special vehicles
    [0003] Field of the invention
    [0004]
    [0005] The invention relates to a set of three composite wings for air, water, land or space vehicles.
    [0006]
    [0007] Background of the invention
    [0008]
    [0009] Within the field of the invention there is the Argentine patent AR247163 "SET OF COMPOSITE WINGS FOR AIRCRAFT", from the same inventor as the present, where one shows the front wings, which are those taken in the lower and front position of the o the fuselages, moving backwards and upwards, joining in the external zone of the same with the other two wings; the central wings, are the one that is in the upper and central zone of the fuselages, joining in its external zone with the other two wings; the rear wings, are those that meet the upper and rear position of the fuselajes-drifts, moving forward and downward, joining in the outer zone with the other two wings. In this patent, therefore, the 3 wings are always located in three different planes and in three different positions. The union of the wings in their respective wing tips is through the marginal plates.
    [0010]
    [0011] Description of the invention
    [0012]
    [0013] The present invention refers to a set of three wings joined with or without marginal plates for air / water / land or space vehicles, in order to reduce the induced resistance and interference, greater maneuverability, independence in the design of the or fuselage, system installations or not of the propelling plant (s), whether or not it has a landing gear system, maximum speed increase, minimum speed reduction that can reach zero or stationary flight; perform flights both forward, backward, sideways or up and low, or turns on their axes.
    [0014]
    [0015] The invention of a set of joined wings with or without marginal plates can be applied to different types of vehicles such as, for example, air vehicles, such as an aircraft, unmanned aircraft, model, drones, model airplanes, etc.-; helicopters, etc .; aquatic vehicles such as, for example, amphibious aircraft, amphibious helicopters, etc .; vehicles terrestrial, such as a plane, motorbike, etc. or space vehicles such as ships, shuttles, etc .; for transport tasks, such as cargo, people, equipment, etc .; works like fumigation, surveillance; being able to be manned, unmanned or autonomous, etc .; It consists of three wings.
    [0016]
    [0017] The invention, therefore, describes a set of three composite wings for air, water, land or special vehicles that is formed by:
    [0018]
    [0019] - front composite wings,
    [0020]
    [0021] - central composite wings and
    [0022]
    [0023] - rear composite wings,
    [0024]
    [0025] wherein said front composite wings are located in the lower and front position of the fuselages of the vehicle, moving backwards and upwards,
    [0026]
    [0027] wherein said front composite wings are joined in the outer zone thereof with said central composite wings and said composite rear wings,
    [0028]
    [0029] wherein said front composite wings have arrow and positive dihedral formed with power plants (1) therein, tilting planes (2), elevator-ailerons and high-lift (3), to join said central and rear composite wings,
    [0030]
    [0031] wherein said central composite wings are located in the upper area of the fuselages of said vehicle,
    [0032]
    [0033] wherein said central composite wings are joined in their outer zone with said rear composite wings and said front composite wings,
    [0034]
    [0035] where said central composite wings have arrow and dihedral formed with power plants therein (11), tilting planes (12), elevator-ailerons and hypersusceptors (4), and wing tips (5),
    [0036]
    [0037] wherein said rear wings are located in the upper and rear position of the fuselajesderivas of said vehicle, moving forward and downward,
    [0038]
    [0039] wherein said rear wings are joined in their outer zone with said front wings and said central composite wings,
    [0040]
    [0041] where said composite rear wings with arrow and negative dihedral are formed with a system of power plants (6) in them and in the union with drift or drifts (7), tilting pianos (8), elevator-ailerons and high-lift (9), to join with the central and rear composite wings.
    [0042]
    [0043] As it is observed, unlike existing solutions, with the present invention, through different determined configurations, improvements or advantages can be achieved in terrestrial, aerial, aquatic or space vehicles, such as:
    [0044]
    [0045] • Increasing the structural rigidity by the union of the wings themselves without plates, or with the elliptical / circular form thereof, leading to the reduction of the weight of the vehicle and therefore more range or less energy for the same range.
    [0046]
    [0047] • Increasing the aerodynamic cleanliness by the union of the wings themselves without plates, or with the elliptical / circular shape of the wings, that is, more range or less energy for the same range. Improvement of the aerodynamic performance with the variation of the tapers and lengthening. To be able to achieve design configurations for different types of flights with the variation of the lengthening and / or tapering of the three wings
    [0048]
    [0049] • Improvement of the stability at low and high speeds with the variation of the central wing arrow. As well as the increase and reduction of high and low speeds with the variation of the central wing arrow. Also, to be able to improve the stability with the variation of the dihedral of the central wing.
    [0050]
    [0051] • Increase the supporting forces of the central and rear wings can obtain a significant variation in the CG of the vehicle.
    [0052]
    [0053] • By placing a power plant system in the junction drift / s-rear wings aerodynamic cleanliness is improved, which leads to having more range or less energy for the same range.
    [0054]
    [0055] • Being able to install the power plant on the wings besides the fuselage allows us to perform maneuvers such as: vertical takeoff and landing; forward and backward movements with positive / negative angle of the "fuselage", with positive / negative tilting, left / right drift; turn on its axis 360 ° left or right with positive / negative angle of the "fuselage", with positive / negative sloping; lateral movement with positive / negative angle of the "fuselage", with positive / negative sloping, left / right drift. These maneuvers and combinations of them. In other words, maneuvers that other designs can not do.
    [0056] • By having the increase of the wing surface, maintaining the structural rigidity, allows us to install solar charging system to power the electrical system (batteries, motors, etc.)
    [0057]
    [0058] • Being able to build with different types of materials optimizing the weight given the structural rigidity of the design.
    [0059]
    [0060] • Considering that the wings themselves are a self-supporting structure, the independence of what you want to install as an air, land, water or space transponder system to carry cargo (person, equipment, etc.) is achieved.
    [0061]
    [0062] • According to the versatility in the movements allowed by the design, I can install different types of landing gear or similar.
    [0063]
    [0064] These and other advantages are apparent in light of the detailed description of the invention.
    [0065]
    [0066] Brief description of the drawings
    [0067]
    [0068] Figure 1 shows a representative view of the configurations that can be achieved with the present invention.
    [0069]
    [0070] Detailed description of the invention
    [0071]
    [0072] The elements defined in this detailed description are provided to assist a comprehensive understanding of the invention. Accordingly, those skilled in the art will recognize that variations and modifications of the embodiments described herein may be made without departing from the scope and spirit of the invention. In addition, detailed descriptions of sufficiently known functions and elements are omitted for reasons of clarity and concision.
    [0073]
    [0074] The invention refers to a system formed by three joined wings, with power plant in them and in the drift / s, tilting planes, support elements and without marginal plates that is formed as follows:
    [0075]
    [0076] The front wings with arrow and positive dihedral formed with: plants of power (1) in them, tilting planes (2), elevators-ailerons and high-lift (3), and their wing tips curling to join with the central wings. In the central wings with tilting planes and arrow and dihedral formed with: elevators-ailerons and high-lift (4), and wing tips (5). In the rear wings with arrow and negative dihedral formed with: system of power plants (6) in them and in union with the drift / s (7), tilting pianos (8), elevator-ailerons and high-lift (9), and their wing tips curling to join with the central wings. The fuselage-drift joins the same wings (10).
    [0077]
    [0078] In the following, different embodiments for the invention are described.
    [0079]
    [0080] In one of the embodiments the three groups of composite wings (front, center and rear) are joined together without marginal plates, using the curvature or not of their wing tips in the case of the front and rear composite wings to join with the central composite wings; and where the three groups of composite wings (front, center and rear) may or may not vary their taper and / or lengthening.
    [0081]
    [0082] The union using the same curvatures of front and rear composite wings allows to reduce the aerodynamic resistance of interference without plates, that is to say reduction of energy consumption of thrust. In addition, structural stress flows are reduced by decreasing stress concentration point and distributing them on the same contact surfaces, ie weight reduction and consequent thrust energy reduction.
    [0083]
    [0084] On the other hand, by being able to make a change in the relationship between the root and end cords of each wing plane, the induced resistance is reduced, that is to say, reduction of the energy consumption of the thrust. Likewise, if the wingspan of each wing plane is increased, the induced resistance is reduced, that is to say reduction of the energy consumption of the thrust.
    [0085]
    [0086] In another embodiment one of the possible configurations without marginal plates is that the front and rear composite wings are of elliptical and / or circular shapes.
    [0087]
    [0088] That the front and rear composite wings form an ellipse or circle and in the central composite wings attached thereto, allows on the one hand the reduction of the induced resistance, that is, reduction of thrust energy consumption; on the other hand, a reduction of the structural efforts with what leads to a reduction of weight and consequently a reduction of the thrust energy.
    [0089]
    [0090] In another embodiment one of the possible configurations with or without marginal plates is that in the central composite wings it can be added at the edge of high-lift elements, that is to say that in the left central wing there is the left-hand high-lift, and in the wing Right central is the right fork lift.
    [0091]
    [0092] By installing said high-lift elements in the central composite wings, the support of said wings increases and with it the reduction of the take-off speed and landing, and consequent reduction in runway length.
    [0093]
    [0094] In another embodiment, one of the possible configurations with or without marginal plates is that in the rear composite wings it is possible to install high-lift elements in the leading edge, that is to say that in the left rear wing there is the left fork lift, and in the Right rear wing is the right fork lift.
    [0095]
    [0096] As with the central composite wings, installing the hypersustational elements on the rear wings also increases the support of said wings and with it the reduction of the takeoff and landing speed, and consequent reduction of the runway length.
    [0097]
    [0098] In another embodiment one of the possible configurations with or without marginal plates is that the wingspan is greater than the other two wings, either fixedly, ie in the design or so that they can be disassembled and assembled. prior to the operation of the vehicle or dynamically.
    [0099]
    [0100] In the case of said extension of the fixed or mobile span, it can be carried out in one of the following ways:
    [0101]
    [0102] • That in the tips of the extended wings, wing tips (winglets, plates, etc.) can be installed or not.
    [0103]
    [0104] • That it can install or not on the outstretched wings high-lift elements on their edges of attack.
    [0105]
    [0106] • That it can be installed or not on the extended wings elevating elements-ailerons in their edges of flight.
    [0107]
    [0108] To have greater wingspan in the central composite wings, that is to say that the central wings "extend" in their wingspan beyond the union with the other two wings (front and rear) and considering that the other two wings become in addition to wings to be wing-stiles for the central composite wings, in this way the wingspan of the central wings can be increased and the wing load can be reduced with the reduction of the induced resistance. In the event that the extensions are removable prior to the operation of the vehicle, it allows to have two types of vehicles with only one: one with a large wing load (as an example, an aerobatics aircraft) and the other with a low wing load (as an example). a sailboat).
    [0109] In the event that said extension is mobile, that is to say, the span can be extended and / or retracted during the operation of the vehicle.
    [0110]
    [0111] In this case, it is an improvement to be able to extend the central composite wings during the operation since it allows, if so desired, to take off with the retracted central composite wings and consequently with low parasitic resistance during the operation; in such a way that taking height and extending the central wings increases in a small proportion the parasite resistance, but significantly reducing the induced (predominate in height due to low air density). As an example, this situation is useful to have an acrobatics aircraft to take off and a tall sailboat.
    [0112]
    [0113] The following three implementation options are proposed for the mobile extension:
    [0114]
    [0115] • That in the tips of the extended wings can install or not wing tips (winglets, plates, etc.).
    [0116]
    [0117] • That it can install or not on the outstretched wings high-lift elements on their edges of attack.
    [0118]
    [0119] • That it can be installed or not on the extended wings elevating elements-ailerons in their edges of flight.
    [0120]
    [0121] The fact of putting wing tips to the extensions of the central composite wings achieves a reduction of the induced resistance, and in the case of installing winglets as wing tips in addition to a collaboration in the forward thrust.
    [0122]
    [0123] While to have elevators-ailerons in their edges of flight can be obtained more sustentacion and in addition to increase the maneuverability with a minimum deflection of the ailerons and consequent reduction of the resistance. Likewise, the fact of extending the central composite wings beyond the union with the other two wings and being able to install elements of hyper-support on the leading edges on the wings central extensions increases the lift of the wing assembly and with it the reduction of the speed of takeoff and landing, and consequent reduction of track length, and also the reduction of induced resistance.
    [0124]
    [0125] In another relation one of the possible configurations with or without marginal plates is that in the central composite wings its arrow can be varied, that is to say that it is positive and / or negative, with the following implementation options:
    [0126] • Fixed, that is to say in the design or adjustable before the operation of the vehicle.
    [0127]
    [0128] The power to make the change of arrow as it can be the positive position allows to acquire more maximum speed moving away from the shock wave. In the case of the negative arrow allows to reduce the loss allowing to operate at low speeds or, better said, improve stability at low speeds. In this design this is more feasible given that the wing tips are fastened with the union of the front and rear wings, which cancels the divergent effect of the negative arrows; likewise, in the case that the central wings are larger than the front and rear wings, it allows a large part of the central wings with a negative arrow, such as this one, to hold the union of the front and rear wings without diverging effect and in the part of extension of the central wings can be controlled said divergent effect. Also the design can be given that the inner part of the central wings is of negative arrow and the extensions of positive arrow what allows is maximum speed.
    [0129]
    [0130] • Mobile, that is to say, that its arrow can vary forward and / or backward, or vice versa, passing by arrow "0" during the operation of the vehicle. This movement will be realized from the fact that the central wings (right and left) move in its root (fuselage) of the wings and its axis of rotation is the union of the three wings.
    [0131]
    [0132] The power to have positive and negative arrow has been detailed in the previous point; so here it highlights the fact that the arrow of the central wings can be moved forward and backward, considering that they move in their root inside the fuselage and turn in their axis in the union with the central and rear wings during the operation of the vehicle, which will allow to have maximum speeds, control low speed and lower the minimum speeds with reduced resistance induced.
    [0133]
    [0134] In another embodiment one of the possible configurations with or without marginal plates is that in the central composite wings it can be varied that its dihedral is positive, zero and / or negative, fixed as conceived in the design.
    [0135]
    [0136] Therefore, the positive and negative dihedral are improvements that allow better control at low and high speeds.
    [0137]
    [0138] Another embodiment is to have a power plant or power plants in the junction drift / s rear wing or rear drifts-wings (more than one drift or more than one "fuselage drift", normal drift, drift type "V", etc.).
    [0139] If it is desired to have a power plant / thrust system, the location in the union of composite rear wings with drift or drift allows to have thrust and an aerodynamically clean vehicle. In addition, since the power plant system is held in three structural zones (drift / drift, left rear wing and right rear wing) and these structures are part of the united structural system, it reduces stress and consequently the weight and push energy.
    [0140]
    [0141] In another embodiment one of the possible configurations with or without marginal plates is to install power plant system in one or several of the wings composed with one of these three options or combination of them:
    [0142]
    [0143] • On the front composite wings, power plants may or may not be installed, but the same power plants may be fixed, and / or tilting. In the case that they are tilting, they either tilt on the same plane of the wing that contains it, or they tilt with the same wing plane or part of the wing plane that contains it.
    [0144]
    [0145] • On the central composite wings, power plants may or may not be installed, but the same power plants may be fixed, and / or tilting. In the case that they are tilting, these, or tilt on the same plane of the wing that contains it, or tilt with the same wing plane or part of the plane that contains it. So also in the case of the variation of the arrow power turns or not to orient itself according to the direction of flight.
    [0146]
    [0147] • The rear composite wings may or may not install power plant, but the same power plants may be either fixed, and / or tilting. In the case of being tilters, either tilt on the same plane of the wing that contains it, or tilt with the same wing plane or part of the plane that contains it.
    [0148]
    [0149] The installation of said power plant system may be in the front, central, rear or composite combinations of wings.
    [0150]
    [0151] Placing a fixed power plant system on the front, center and rear composite wings allows for forward thrust, and to control or compensate for rotation to the CG of the vehicle.
    [0152]
    [0153] Placing a system of power plant on the front wings, central and rear mobile tilting allows to have forward, backward, sideways, up and down, rotate on their axes; that is, in all directions and with the attitude of the fuselage in indistinct to them. Also emphasizing that by aligning with the predominant flight direction, maximum speed could be achieved. It is a union of aircraft and helicopter, but with more maneuvers than the helicopter and the same speeds as one aircraft at a time.
    [0154]
    [0155] With a mobile system tilting the plane that contains the same power plant system, the same improvements are achieved as those listed in the previous paragraph (moving the same power plant system), but here a better energy performance is allowed, given that the planes, when moving with the power plant system, allows to reduce the interference and resistances of the planes with the advance movement of the vehicle where desired.
    [0156]
    [0157] On the other hand, when expressing power plant system, can be defined as a thrust system, such as, for example, non-limiting: turbo jet, turbohelices, propellers, steerable or no thrust nozzles, ramjet / scramjet, hyperreactor / ramjet, rocket motor, electric motor, fuel motor, etc.
    [0158]
    [0159] In another embodiment one of the possible configurations with or without marginal plates is to install elements that allow to use the solar rays as energy as plates / solar panels or other elements, indistinctly on the wing surfaces.
    [0160]
    [0161] The fact of being able to have large wing surfaces (front, rear and central with their extensions) maintaining unified structural rigidity and low wing load, allows to have solar energy system for the vehicle.
    [0162]
    [0163] In another embodiment one of the possible configurations with or without marginal plates is to construct the design with aeronautical, aquatic, terrestrial or space materials; as, for example, and in a non-limiting way: aluminum, steel, wood, composite, graphene, etc.
    [0164] The fact that the structure of the union of the three composite wings and the fuselage allows to substantially reduce the torsion efforts, but also the bending, which leads to be able to use almost any type of material.
    [0165]
    [0166] In another embodiment one of the possible configurations in the fuselage or supporting structure is to be able to install or not a rear loading door, to have larger doors and windows, as well as to be able to carry out the removal and installation of the fuselage-container or passenger cabin in the form fast, structure like a terrestrial vehicle (shape of car, motorcycle, etc.) attached to the self-supporting structure of the three wings.
    [0167] In another embodiment one of the possible configurations is to be able to install or not so much in the group of wings and / or in the fuselage or fuselages of: landing gear (conventional, tricycle, bicycles, quads, etc.), and / or legs, and / or skates-skis, and / or floats, and / or supports, etc.
    [0168]
    [0169] The fact that the structure of the union of the three wings and the fuselage allows to substantially reduce the torsion efforts, allows to increase the size of the fuselage doors and windows. And having reduced the bending efforts of the tail cone of the fuselage because they absorb it and derive it to the rest of the structure, through the drift / rear rooms, it allows having a loading door with opening if desired in flight. In addition, by forming the wings a united and independent group allows to realize a fuselage-container system or passenger cabin to be able to join quickly to the fuselage or fuselages in a fast way without altering the transport vehicle of said cargo.
    [0170] In addition, the fact that the vehicle can perform vertical takeoff maneuvers such as a helicopter or an aircraft, allows the flexibility to install different train systems, legs, etc.
    [0171]
    [0172] As it can be deduced, these embodiments can be carried out in a single way or isolated each one of them or combining several or all of them.
    权利要求:
    Claims (17)
    [1]
    Set of three composite wings for air, water, land or special vehicles characterized because it consists of:
    - front composite wings,
    - central composite wings and
    - rear composite wings,
    wherein said front composite wings are located in the lower and front position of the fuselages of the vehicle, moving backwards and upwards,
    wherein said front composite wings are joined in the outer zone thereof with said central composite wings and said composite rear wings,
    wherein said front composite wings have arrow and positive dihedral formed with power plants (1) therein, tilting planes
    [2]
    (2), elevator-ailerons and high-lift
    [3]
    (3), to join said central and rear composite wings,
    wherein said central composite wings are located in the upper area of the fuselages of said vehicle,
    wherein said central composite wings are joined in their outer zone with said rear composite wings and said front composite wings,
    wherein said central composite wings have arrow and dihedral formed with power plants therein (11), tilting planes (12) with elevator-ailerons and high-lifters
    [4]
    (4), and wing tips
    [5]
    (5),
    wherein said rear wings are located in the upper and rear position of the fuselages of said vehicle, moving forward and downward,
    wherein said rear wings are joined in their outer zone with said front wings and said central composite wings,
    where said rear composite wings with arrow and negative dihedral are formed with a system of power plants
    [6]
    (6) in the same and in the union with the drift or drift
    [7]
    (7), tilting planes
    [8]
    (8), elevators-ailerons and hypersusceptors (9), to join with the central and rear composite wings.
    Set of three composite wings for air, water, land or special vehicles according to claim 1, characterized in that said sets of three composite wings, front, central and rear join together without marginal plates or not their taper and / or elongation.
    Set of three composite wings for air, water, land or special vehicles according to claim 2 characterized in that the curvature of their wing tips is used in the case of the front and rear composite wings to be joined with the central composite wings; and where the set of three composite wings varies or not their tapering and / or lengthening.
    Set of three composite wings for air, water, land or special vehicles according to claim 1, characterized in that said front and rear composite wings form approximately an ellipse or a circle.
    Set of three wings composed for air, water, land or special vehicles according to claim 1, characterized in that the wing tips are curved.
    Set of three composite wings for air, water, land or special vehicles according to claim 1, characterized in that said central composite wings are added at the leading edge with high-lift elements, that is to say that in the left central wing there is a left-hand lift, and in the right central wing there is a right fork lift.
    Set of three composite wings for air, water, land or special vehicles according to claim 1, characterized in that said rear composite wings are added at the leading edge with high-lift elements, that is to say that in the left rear wing there is the left-hand high-lift, and in the right rear wing is the right fork lift.
    Set of three composite wings for aerial, aquatic, terrestrial or special vehicles according to claim 1, characterized in that the wingspan of the central composite wings is greater than the other two composite wings, either fixedly, that is to say in the design or shape. that can be disassembled and assembled prior to the operation of the vehicle or dynamically, where said scope is extends or retracts the vehicle during the operation.
    [9]
    9. Set of three composite wings for air, water, land or special vehicles according to claim 8, characterized in that said magnification of span, whether fixed or mobile, is carried out according to one of the following methods:
    - installing ferrules on said extended compound wings of the winglets, plates, etc. type,
    - installing high-lift elements at the leading edges of the central composite wings, or
    - installing elevating elements on the extended central composite wings at their trailing edges.
    [10]
    10. Set of three composite wings for air, water, land or special vehicles according to claim 1, characterized in that the arrow on the central composite wings is varied, that is to say that it is positive and / or negative, where said variation can be fixed, that is, it is adjusted prior to the operation of the vehicle, or dynamic, that is to say that it is modified in one direction or another during the operation of the vehicle.
    [11]
    11. Set of three composite wings for air, water, land or special vehicles according to claim 1, characterized in that in the central composite wings the dihedral is varied, in such a way that it is positive, zero or negative, where said variation is carried out in a manner fixed or prior to the operation of the vehicle.
    [12]
    12. Set of three composite wings for air, water, land or special vehicles according to claim 1, characterized in that said assembly incorporates a power plant system in at least one of the three composite wings, central, front or rear, where said system of power plant is fixed or tilting and where, if it is tilting, either tilts on the same plane of the wing that contains it, or tilt with the same wing plane or part of the plane that contains it.
    [13]
    13. Set of three composite wings for air, water, land or special vehicles according to claim 12 characterized in that the variation of the arrow of the central wings can rotate to orient according to the direction of flight.
    [14]
    14. Set of three composite wings for air, water, land or special vehicles according to claim 1, characterized in that at least one of the composite wings incorporates a solar energy system to provide energy to the vehicle.
    [15]
    15. Set of three composite wings for air, water, land or special vehicles according to claim 1, characterized in that said set of three composite wings are constructed containing one or more of the following materials: aluminum, steel, wood, fabric, acrylics, composites or graphene.
    [16]
    16. Set of three composite wings for air, water, land or special vehicles according to claim 1, characterized in that said fuselage or fuselages or structure of said vehicle incorporates one or more doors, windows, containers, or passenger cabin and / or cargo.
    [17]
    17. Set of three composite wings for air, water, land or special vehicles according to claim 1, characterized in that said set of three wings or the fuselage or fuselages of the vehicle incorporates a landing gear, legs, skids or skis, floats or other type of vehicle support when it is on the surface.
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    同族专利:
    公开号 | 公开日
    CN111315655A|2020-06-19|
    ES2711660B2|2020-06-17|
    WO2019086742A1|2019-05-09|
    US20200247525A1|2020-08-06|
    EP3705401A4|2021-08-25|
    RU2020113557A|2021-12-02|
    EP3705401A1|2020-09-09|
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    法律状态:
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    优先权:
    申请号 | 申请日 | 专利标题
    ES201731283A|ES2711660B2|2017-11-02|2017-11-02|Set of three compound wings for air, water, land or space vehicles|ES201731283A| ES2711660B2|2017-11-02|2017-11-02|Set of three compound wings for air, water, land or space vehicles|
    US16/758,442| US20200247525A1|2017-11-02|2018-10-30|Assembly of three composite wings for aerial, water, land or space vehicles|
    EP18874847.9A| EP3705401A4|2017-11-02|2018-10-30|Assembly of three composite wings for aerial, water, land or space vehicles|
    PCT/ES2018/070704| WO2019086742A1|2017-11-02|2018-10-30|Assembly of three composite wings for aerial, water, land or space vehicles|
    CN201880071222.9A| CN111315655A|2017-11-02|2018-10-30|Assembly of three composite wings for air, water, land or space vehicles|
    RU2020113557A| RU2020113557A|2017-11-02|2018-10-30|THREE COMPOSITE WING ARRANGEMENT FOR AIR, WATER, LAND OR SPACE VEHICLES|
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