• 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:
    FLAT VEHICLE RETRACTABLE KING ARTICULATION AND FRAME. The present invention relates to a frame for a flight vehicle that supports a pair of wings in a manner that facilitates the articulation of the wings between an unfolded configuration and a retracted configuration. The frame includes top and bottom plates parallel with the gap between them. The wings have wing supports fixed to it with the wing supports articulably supported by the articulation assemblies to the upper plate and the bottom frame plate. The locking sets can be selectively operated to hold the wing and wing supports associated with the frame in, or in the unfolded configuration, or in the retracted configuration, so that loads between the wings and the frame are mainly transported through the locking sets preferably than through the joint sets. A pivot position on the frame and wing supports is selected to maximize the length of the wing end to end, while minimizing the contour required for the vehicle when the wings are fully retracted.
    公开号:BR112013002735B1
    申请号:R112013002735-5
    申请日:2011-08-02
    公开日:2021-02-02
    发明作者:Samuel Hall Bousfield；Robert N. Roberts；Matthew A. Brown；Willem A.J. Anemaat
    申请人:Samson Aip, Inc；
    IPC主号:
    专利说明:

    Technical Field
    [0001] The following invention relates to flight vehicles and, in particular, to aircraft-type vehicles with a fixed wing when in flight. More particularly, this invention relates to an aircraft that exhibits a fixed wing when in flight that can have the wings movable from an unfolded position to a stowed position when the wings are not in use, such as to facilitate the use of the vehicle as a highway vehicle. Background Technique
    [0002] Although flying automobiles have captured the imagination for generations, a viable flight car has not been successfully introduced. At present, although construction and materials have reduced the weight of the car, car safety and fog and smoke mixing regulations require a car that is heavier than a similarly sized aircraft. It seems a daunting task to produce a car that also has qualities suitable for flight. The construction and weight of a motorcycle is a better match for a flight vehicle or combined land / air vehicle, consequently the three-wheel approach described here.
    [0003] For the act of driving on the ground, the wings are harmful. The wings produce elevation, when such elevation undesirably destabilizes the vehicle on the ground. The wings are highly subjected to damage. Also, land vehicle traffic lanes are too narrow to accommodate vehicles with wings. Thus, it is desirable to have the transition of wings between an unfolded flight position and a retracted ground travel position. Numerous examples exist of articulated wings, especially for aircraft storage. Many of these projects date back to aircraft transport operations during World War II. An example would be the U.S. Navy Corsair.
    [0004] Additional examples have been shown on military and non-military aircraft since that time, including the F-111, Tomcat and Terrafugia. While the Tomcat and F-111 had flapping wings, Corsair and Terrafugia had folded wings. Each has articulation mechanisms that carry significant loads from the wing during flight, and therefore, must be very robust. Even so, there are maintenance problems with the F-111 and Tomcat's swinging wings.
    [0005] The present invention describes a wing articulation mechanism that allows the wing to swing from a retracted position to an unfolded position, but then has characteristics that allow the main forces of wing loading to overtake articulation while in flight . This keeps the joint regularly small and light, which is important for flying vehicles, and prevents extra maintenance of joints that suffer from wing load conditions during normal use. Description of the Invention
    [0006] With this invention, a vehicle configuration is provided that has a pair of wings that articulate over articulations relative to a central frame built into a vehicle structure. While the vehicle can be any form of flight vehicle that would benefit from having retractable wings in certain circumstances, the preferred embodiment is in the form of a vehicle convertible between a flight mode and a drive mode when it is configured as a vehicle three-wheel (ie, a motorcycle).
    [0007] The articulated wing structure generally includes a central frame, a left joint, a right joint and wing supports associated with a left wing and a right wing. In this embodiment, the frame is generally in the form of two substantially parallel plates. Each plate is formed of separate ribs as structural members to transmit loads of tension and compression through the entire frame. A primary objective of the frame is to have wing loads transmitted directly from the wings to the frame rather than having significant loads through the joints. In this way, the size and strength of the joints and the structure of the frame directly adjacent to the joints can be optimized.
    [0008] Another important feature of the articulated wing mechanism is to facilitate the wings to be as long as possible by extending in a lateral direction when in an unfolded position, but minimizing a length of the wings that need to be stored when in the stored position, such that the wings can fit fully inside a full contour of a vehicle's outer casing, and keep the vehicle to a minimum size. To accommodate such length optimization, the pivot point is preferably provided on the outermost rear portions of the left and right side edges of the central frame. In such a configuration, the width of the wing cord is accommodated on board the pivot points. The wings can thus be extended outwards laterally, and an overall width of the vehicle from the wingtip to the wingtip is substantially similar to a total length of the left wing, plus a total length of the right wing, plus a total length the central frame. When stored, the length of the total assembly including the left wing, right wing and central frame is substantially the same as only the length of the left wing (or right wing) from tip to joint. As an example, if the frame is five feet, and each wing has a rope width of 2.5 feet and a length of 12.5 feet, the end-to-end width of the pair of wings is thirty feet, while the wings collapse in a 12.5-foot stored packaging, which can be stored inside the vehicle's body outline.
    [0009] A vehicle is thus provided, which has wings that can transition between an unfolded position and a collapsed position, and whose vehicle, when its wings are in the collapsed position, can adjust inside a parking space standard, such as with a total vehicle length of approximately twenty feet or less. However, when the wings are deployed, the wings are of sufficient length and other size characteristics that they can provide the required lift for a vehicle of this size and for a payload, such as a pair of typical weight passengers and a small amount of associated load, similar to that typically found in a two-fit general aviation aircraft.
    [00010] The portion of each joint that connects to the wings preferably interfaces with a wing support coupled to each wing at the ends of this opposite the tips. These wing supports and wing portions adjacent to these fit on board the two parallel plates of the central frame. These wing supports are produced from separate elements from the frame which are configured to effectively transmit loads from the wing in the central frame. These loads include lifting loads that act vertically, and gravity loads that act against that also act vertically.
    [00011] Other loads through this articulation joint include drag loads and acceleration loads from the vehicle's propulsion system that generally act in a forward and aft direction. Other loads, such as those induced by turbulence, or by performing aerobatic maneuvers, can act in other directions, and be either linear loads, or torsional loads on different axes of rotation, and are all effectively transmitted from the wings to the supports wing and then to the central frame with minimal loading and associated force on the actual articulation joints themselves. The wing supports can extend laterally within an external aerodynamic surface of an associated wing, if desired, to effectively transport loads from the wing to the wing support.
    [00012] A locking mechanism is also provided that is configured to lock an embodiment of this invention between an open position of the wing and a closed / stored position of the wing. An actuator can optionally be provided to adjust the latches for engaging holes, or other structures, between the wing supports and the frame. In the exemplary embodiment shown, the latches are provided as a set of four that are attached to the wing supports, and adjustably engage and disengage the frame in two separate locations for secure attachment in an unfolded wing configuration, or a retracted wing configuration. The latches are spaced from the joint to minimize stress on the joint, and provided as a set to distribute loads evenly to the frame without stress concentration. Brief Description of Drawings
    [00013] Figure 1 is a perspective view of a frame of this invention for secure mounting of wings in a mode articulable to a flight vehicle, with the wings shown in an unfolded configuration.
    [00014] Figure 2 is a perspective view similar to the one shown in Figure 1, but with the wings shown in a retracted position.
    [00015] Figure 3 is a perspective view similar to that shown in Figure 2, but also showing a general outline of a flight vehicle, and illustrating how the wings can be completely retracted within a vehicle outline.
    [00016] Figure 4 is a perspective view similar to the one shown in Figure 3, but with the wings unfolded.
    [00017] Figure 5 is a top plan view of a left end of the frame of Figures 1 and 2, and portions of the left wing pivotably attached to the frame, and with the wings shown in a retracted orientation relative to the frame, and with portions of frame shown in broken lines.
    [00018] Figure 6 is a top plan view similar to the one shown in Figure 5, but with the wing in an unfolded orientation. [00019] Figure 7 is a perspective view of what is shown in Figure 5, with both the frame and the wing structures shown in solid lines (except where the structures are hidden and then shown with hidden lines), and with an upper frame plate removed to better illustrate details of a wing support and articulation set, as well as sets of latches for joining, facilitating the articulation and holding of the left wing to the left side edge of the frame.
    [00020] Figure 8 is a perspective view similar to the one shown in Figure 7, but with the wing in an unfolded configuration.
    [00021] Figure 9 is a view of exploded parts of the left end of the frame of Figure 1 and portions of the left wing, shown in perspective and illustrating various parts comprising the wing supports, joint sets and sets of latches that articulate and they hold the left wing to the left side edge of the frame, and with the wing shown in an unfolded orientation.
    [00022] Figure 10 is a view of exploded parts in perspective similar to that shown in Figure 9, but with the wing retracted.
    [00023] Figure 11 is a perspective view of a wing support portion of this invention shown with an articulation assembly of this invention exploded from the wing support.
    [00024] Figure 12 is a perspective view of the wing support shown alone, and from a reverse angle to that shown in Figure 11.
    [00025] Figure 13 is a perspective view of an alternative embodiment frame to that shown in Figure 1, including a central plate for joining an upper plate and bottom plate of the frame together.
    [00026] Figure 14 is a perspective view of an alternative embodiment frame additional to that shown in Figure 1, and featuring a rear plate for joining the upper plate and bottom plate of the frame together.
    [00027] Figure 15 is a perspective view of a vehicle with which the frame and wings of the embodiments of the invention shown here can be used. Best Ways to Make the Invention
    [00028] Referring to the drawings, in which similar reference numerals represent similar parts throughout all the drawing figures, the reference numeral 10 (Figures 1-4) is directed to a frame that articulately supports a left wing 6 and right wing 8 of a flight vehicle 1. The frame 10 carries loads from the wings 6, 8 to a structure and body of the vehicle 1 when the wings are deployed. In addition, the frame 10 facilitates the articulation of the wings 6, 8 relative to the frame 10 and associated body of the vehicle 1, when the wings 6, 8 are to be retracted, as well as to allow the vehicle 1 to operate as a road vehicle without wing in an operating mode.
    [00029] In essence, and with particular reference to Figures 1 and 2, basic details of the frame 10 and associated structures for joining the wings 6, 8 to the frame 10, are described, according to an exemplary embodiment. The frame 10 includes at least one plate and, typically, a pair of plates including an upper plate 12 and bottom plate 14 spaced apart by a gap between them. Each wing 6, 8 has a wing support 20 secured to a portion of each wing 6, 8 adjacent to the frame 10. These wing supports 20 interface with a pair of hinge assemblies 30 that allow wing supports 20 and wing associated 6, 8 articulate relative to the frame 10. Separate lock sets 40 are also provided, which removably secure and secure the wing supports 20 to the frame 10 so that a majority of loads between the wings 6, 8 and the frame 10 they are not carried by the hinge assemblies 30, but preferably carried by the latch assemblies 40 directly from the wing supports 20 to the frame 10, and on the other portions of the vehicle.
    [00030] More specifically, and with particular reference to Figures 3, 4 and 15, basic details of an exemplary vehicle 1 with which the frame 10 of this invention and associated wings 6, 8 can be used, are described according to this embodiment exemplary. Vehicle 1 includes a front 2 opposite a rear 4. The frame 10 is oriented with side edges 18 that define a lateral extension of the frame 10 transverse to a center line CL (Figures 5-8) of the vehicle 1 extending to from the front end 2 of the vehicle 1 to the rear end 4 of the vehicle 1.
    [00031] While vehicle 1 may have a variety of different configurations, in a preferred embodiment, an engine provides a driving force for the vehicle, and is located adjacent to the rear 4 of vehicle 1. The front 2 of vehicle 1 defines a nose of vehicle 1 which includes compartments within which wings 6, 8 can be stored when in its retracted position, such as when vehicle 1 is to be driven on a road. Vehicle 1 typically includes wheels suitable for allowing vehicle 1 to be driven on the wheels, with these wheels typically including a pair of wheels at the rear 4, and a single center wheel at the front 2. Vehicle 1 is wider than two times a chord length of the wings so that the wings 6, 8 can reside adjacent to each other and fully fit within the outline of the vehicle 1. Alternatively, the wings 6, 8 may overlap slightly when retracted, or the wings 6, 8 can protrude slightly from the contour of the vehicle 1, in less than optimal embodiments of the invention.
    [00032] Vehicle 1 would also typically include control surfaces including a rudder and vertical stabilizer which are preferably located in a spray set adjacent to the rear 4 of vehicle 1. This spray set can be telescoped substantially horizontally later (and, optionally) , also upwards) from the rear 4 in one embodiment of the invention. Preferably, doors cover the wings 6, 8 when they are retracted into a contour of the vehicle 1. These doors can be hinged doors that automatically articulate open and closed relative to the movement of the wings 6, 8, or can otherwise be manually or automatically opened and closed. A vehicle cab would also typically be provided in a part of the vehicle between the front 2 and the rear 4, and typically above and immediately in front of the frame10.
    [00033] With particular reference to Figures 1 and 2, basic details of the frame 10 are described, according to this exemplary embodiment. Frame 10 is a rigid structure that provides a general function of attaching wings 6, 8 to vehicle 1 jointly, and transferring loads from 6, 8 to vehicle 1 in a way where a majority of these loads are transferred through other structures than the hinge assemblies 30, and, more preferably, in the form of wing supports 20 and latch assemblies 40 spaced from the hinges 30. In this exemplary embodiment, the frame 10 includes a substantially planar top plate 12 substantially parallel to and spaced of a substantially planar bottom plate 14. Each plate 12, 14 has rear edges 16 defining a total rear edge of the frame 10. These rear edges 16 can be attached together, such as by a rear frame plate (see Figure 14). Each of the plates 12, 14 also includes side edges 18 on the left and right side edges 18 of the plates 12, 14. These side edges 19 are spaced apart by a distance that defines a width of the frame 10. This width is preferably similar to twice a rope width for the wings.
    [00034] The plates 12, 14 each include hinge holes 13 that pass through them which can receive portions of the hinge assemblies 30. The plates 12, 14, more preferably, include a plurality of ribs 15 and openings. The ribs 15 provide structural strength to the plates 12, 14, while the openings minimize the total weight of the frame 10. A pattern for these ribs 15 may vary, but is more preferably similar to the pattern shown in Figures 1 and 2. The plates 12 , 14 are spaced by a clearance height similar to, but greater than, a thickness of the wing 6, 8, so that the wings 6, 8 can be retracted at least partially in this clearance.
    [00035] The plates 12, 14 preferably include rear holes 17 adjacent to the rear edges 16, and side holes 19 adjacent to the side edges 18. The rear holes 17 are preferably provided as a single hole in the upper plate 12 and a single hole in the plate bottom 14 for each side of the plates 12, 14 on opposite sides of the centerline CL (Figures 5-8). In contrast, a greater number of side holes 19 is preferably provided in the top plate 12 and bottom plate 14 adjacent to the side edges 18 thereof. In a more preferred embodiment, four such side holes 19 are provided in each plate 12, 14 adjacent to each side edge 18.
    [00036] The pair of single rear holes 17 interacts with the lock set 40 to keep the wings 6, 8 in their stowed position. Because the forces on the wings 6, 8 are preferably low when the wings are in their retracted position, only a pair of rear holes 17 are required in the plates 12, 14 to hold the wings 6, 8 in the retracted position for this embodiment. In contrast, a larger number, and preferably four side holes 19, are provided on each of the plates 12, 14 on each side edge of the plates 12, 14 of the frame 10. These side holes 19 each interface with sets of locks separated 40 and also with locking holes 26 in the wing supports 20 so that actuating stops 48 of the locking sets 40 extend through these holes 26, and in the side holes 19, to hold the wings 6, 8 to the frame 10 through them locking sets 40, preferably than through hinge sets 30.
    [00037] By providing a larger number of side holes 19 and spacing these side holes 19 from the hinge holes 13, the wings 6, 8 can have unfolded flight loads transferred to the frame 10 at a variety of separate points. Not only are these separate points that separate from each other to avoid stress configurations, but they are also spaced from the hinge assembly 30. By providing multiple of such side holes 19, and multiple sets of associated latches 40, the loads are distributed so that each lock set 40 does not need to be as robust, while still providing redundant locking safely. With the spacing out of the hinge holes 13, the forces are transported in spaced locations from the hinge assemblies 30 so that a minimum of forces are transferred through the hinge assemblies 30 from the wings 6, 8 to the frame 10.
    [00038] With particular reference to Figures 9-12, basic details of the wing supports 20 and joint sets 30 are described, according to a more preferred embodiment. The wing supports 20 define portions of each wing 6, 8 that are securely attached to the wings 6, 8, and pivotable to the frame 10. These supports 20 thereby provide at least a portion of a means for pivotally coupling the wings 6, 8 to the frame 10, and to the vehicle structure 1. The drawing figures depict in detail a left one of a pair of wing supports 20 for use with the left wing 6. A corresponding wing support would also be provided for the right wing that would be a mirror image of the wing support 20.
    [00039] The wing support 20 is a rigid structure that is configured so that it can be securely attached to the left wing 6. This wing support 20 can be incorporated in the wing 6, or be a separate structure fixable to the wing 6. In this embodiment, the wing support 20 is separated from the left wing 6, but securely attached to the left wing 6. The wing support 20 includes a base plate 22 oriented substantially perpendicular to an end plate 23, and with an upper plate 24 and lower plate 25 spaced apart by a width of the base plate 22, and end plate 23 and with the upper plate 24 and lower plate 25 generally parallel to each other.
    [00040] A contour of these upper and lower plates 24, 25 is preferably similar to that shown in the drawing figures, and having a height similar to the thickness of the wings 6, 8, so that the wing supports 20 can adjust inside the clearance between the plates 12, 14 of the frame 10. The wing supports 20 are configured with the upper plate 24 and the lower plate 25 having a specific geometry that facilitates the provision of a large number of locking holes 26 in these, and not entirely within a line, but preferably with at least one of the lock holes 26 at a far end from the hinge assembly 30 being outside the plane in which the other three lock holes 26 are provided.
    [00041] Preferably, an interface plate 27 is provided adjacent to the base plate 22 which provides a separate structure that can be attached to the wing supports 20, and portions of the wing 6 to distribute loads and hold the left wing 6 to the wing support. 20. The upper and lower plates 24, 25 each include hinge lobes 28 at one end thereof with an eye 29 passing through each hinge lobe 28. This eye 29 of each plate 12, 14 defines a cylindrical recess in which a center pivot 32 of the hinge assembly 30 can be placed. The center pivot 32 preferably includes ends 33 with grooves 34 adjacent thereto. A sleeve 35 can traverse an external surface of the central pivot 32 and provides a balancing function that keeps the plates 12, 14 of the frame 10 very close together, and blocks the movement of the wings 6, 8 in and out of the gap between the plates 12 , 14.
    [00042] The hinge assembly 30 includes the eye 29 formed inside each hinge lobe 28. This eye 29 receives the central pivot 32 which passes substantially vertically through it. The ends 33 of the center pivot 32 preferably include horizontal grooves 34 which can receive locking rings 38 therein. Washers 36 can also be located between locking rings 38 and hinge lobes 28 to complete the construction of each hinge assembly 30. Sleeve 35 surrounds central pivot 32 between plates 12, 14 of frame 10. This set of single hinge 30 is preferably kept unique by having wing loads between the wings 6, 8 and the frame 10 transferred through the latch assemblies 40 rather than through the hinge assemblies 30.
    [00043] The wings 6, 8 articulate on substantially associated vertical axes that pass through central pivots 32 of each articulation set 30. While the vertical articulation axes are preferably truly tilted inward and forward slightly so that the wings 6, 8 exhibit some dihedral (or anhedral) when unfolded, still being horizontal when retracted. In one embodiment, this substantially vertical but slightly inclined orientation is six to eight degrees outside the vertical inward (towards each other) and six to eight degrees outside the vertical forwards to accommodate a six to eight degree dihedral for the wings 6, 8.
    [00044] With particular reference to Figures 9-11, specific details of the lock sets 40 are described, according to this exemplary embodiment. The locking sets 40, while they can be integrated together, are, in this embodiment, separate insulated structures that are positioned to selectively lock the wing supports 20 and wings 6, 8 associated with the frame portions 10. Each locking set 40 includes a mounting plate 42 which, in this embodiment, is configured to allow the locking sets 40 to be fastened by means of fasteners 44 to the wing supports 20, and, more particularly, to the base plate 22 of the wing supports 20.
    [00045] Each lock set 40 includes a cylindrical body 46 that extends substantially vertically, and has a height similar to a distance between the top plate 24 and bottom plate 25 of the wing supports 20. These lock sets 40 are positioned directly aligned with the locking holes 26 in the wing brackets 20.
    [00046] The driven stops 48 extend from the upper and lower ends of the cylindrical body 46 and through the locking holes 26 in the wing supports 20. The stops 48 move up and down (along the arrows C and D of the Figures 7 and 8). Such movement can be manual or automatic. If automatic, in one embodiment, the cylindrical bodies 46 are configured as solenoids. When an appropriate electrical signal is distributed to the assemblies, the stops are driven to move up or down, depending on whether the lock assemblies are to be engaged or disengaged. As an alternative, the sets of locks can be manually activated, with such manual actuation occurring through the sliding of a lever, or another mechanism associated with the stops 48.
    [00047] If required, power assistance for movement of the stops 48 can be provided by a spring or other element for adding force for movement of the stops 48. These stops 48 move upwards in the holes in the frame 10, including side holes 19, or the rear holes 17. The side holes 19 are engaged by the stops 48 when the wings 6, 8 are secured in their unfolded configuration. Preferably, all four stops 48 are used to engage parts of the wing supports 20 with the side edges 18 of the frame 10 through the side holes 19 in the plates 12, 14. When the wings are in their retracted position, only one of the stops 48 is used and moved to engage the rear holes 17 in the frame 10 to hold the wings 6, 8 in their stowed position. Optionally, the rear holes 17 can be omitted and the wings 6, 8 secured in their retracted position by structures close to the front 2 that engage the wing tips 6, 8, or anywhere, as the wings 6, 8 do not encounter high loads when retracted.
    [00048] If desired, sensors can be associated with stops 48 and lock sets 40 generally, whose sensors ensure that stops 48 fully engage the holes in frame 10 to ensure that wings 6, 8 have been properly locked in their unfolded position to frame 10. This system can be integrated with lights on a display inside the cab that indicates the status of the lock set 40.
    [00049] These stops can be perfectly cylindrical if desired. Tolerance can be provided to allow the stops 48 to fit inside the holes in the frame 10, including the rear holes 17 and side holes 19. Alternatively, the stops 48 can have a few degrees of taper so that the stops 48 can fit extend until interference with the surfaces of the side holes 19 or rear holes 17 occurs. With such a taper, no tolerance is required, and a secure fit is always achieved. Some combination of tolerance and geometric configuration of the stops 48 can be appropriately selected to optimize secure attachment and convenient movement of the stops 48 to achieve the benefits of secure attachment and the benefits of convenient movement of the stops 48.
    [00050] Figure 13 represents an alternative frame 110 which is similar to the frame 10 of Figures 1-4, except that it only includes a central plate 150 that joins the upper plate 12 and the bottom plate 14 together. Such a central plate 150 adds strength to the frame 110, and can be added to the frame 10 if desired. The plate 150 is positioned along the center line to keep the clearance in the wing frame 6, 8 in positioning it open.
    [00051] Figure 14 represents an alternative frame 210 that includes only a rear plate 250 that joins the rear edges of the frame 210 together. This back plate 250 features ribs 255 in this embodiment that provide resistance to this back plate 250, while minimizing weight.
    [00052] The central plate 150 of the alternative frame 110 (Figure 15) can be combined with the alternative frame 210 and associated rear plate 250, and with these structures integrated into the frame 10 of Figures 1-4 in a form of the invention so that the plates 12, 14 of the frame 10 can be safely held together and kept from distortion, while carrying the loads between the wings 6, 8 and a vehicle frame 1 to which the frame 10 is attached. Such fixation of the structure between the frame 10 and the vehicle 1 can occur in a variety of different portions of the frame 10, provided that they avoid interference with the movement of the wings 6, 8. In one embodiment, the frame 10 is integrated into the total frame structure. vehicle, rather than as a separate structure.
    [00053] From a geometric point of view, the frame 10 has flat dimensions that are generally twice as wide as the rope length of the wings 6, 8. In this way, the wings 6, 8 can fit within the clearance when wings 6, 8 are retracted. The frame 10 has a height similar to the thickness of the wings 6, 8 so that the wings can adjust within the clearance. Vehicle 1 extends from the location of the frame 10 close to a center of gravity of the vehicle 1 in front of the front 2 a distance similar to the length of each wing 6, 8. Through the articulation of the wings 6, 8 to the frame 10 rear side corners of the frame and rear root ends of 6, 8, this 6, 8 wing forward extension is kept to a minimum, so that the length of the wing 6, 8 can be maximized, while the length of the vehicle formed from frame 10 can be minimized.
    [00054] This description is provided to reveal a preferred embodiment of the invention and a better way to practice the invention. Having thus described the invention in this way, it should be apparent that several different modifications can be made to the preferred embodiment without departing from the scope and spirit of this disclosure of the invention. When structures are identified as a means to perform a function, identification is intended to include all structures that can perform the specified function. When the structures of this invention are identified as being coupled together, such language must be broadly interpreted to include the structures being directly coupled together, or coupled together through the intervention of the structures. Such coupling can be permanent or temporary, and either in a rigid mode, or in a mode that allows articulation, sliding or other relative movement, while still providing some form of attachment, unless specifically restricted. Industrial Applicability
    [00055] This invention exhibits industrial applicability in that it provides an articulation and wing frame that oscillate the wing partially or totally out of the body for unfolding the wing or within the body of the vehicle for retraction of the wing.
    [00056] Another objective of the invention is to swing the wing out of the body and to be able to lock the wing to the body in a way that transfers the loading of the wing to the vehicle, and out of the joint to a greater degree.
    [00057] Another objective of the invention is to provide a retractable wing that has increased wing extension over the existing state of the oscillating wings of the technique.
    [00058] Another objective of the present invention is to provide a method and apparatus for transferring loads from a wing to a central frame of a vehicle.
    [00059] Another objective of the present invention is to provide an articulated wing whose articulation has a minimum of wing loads acting on them.
    [00060] Another objective of the present invention is to provide a vehicle that can have a wing transition from an unfolded configuration to a retracted configuration quickly, easily and safely.
    [00061] Other additional objectives of this invention, which demonstrate its industrial applicability, will become apparent from a careful reading of the detailed description included, from a review of the attached drawings, and from the review of the claims included herein.
    权利要求:
    Claims (21)
    [0001]
    1. Flight vehicle (1) with retractable wings, comprising in combination: a vehicle structure that supports a vehicle body and flight vehicle control surfaces; a left wing (6); a right wing (8); a rigid frame (10), said frame (10) attached to said structure; said frame (10) having a left pivot axis spaced from a right pivot axis, said vertically oriented and spaced pivot axes; said frame (10) includes side edges (18); said left wing (6) pivotally attached to said frame (10), and adapted to articulate with respect to said frame (10) on said left articulation axis; said right wing (8) pivotally attached to said frame (10), and adapted to articulate with respect to said frame (10) on said right pivot axis; said wings (6, 8) adapted to pivot from an unfolded position more spaced apart from each other to a retracted position closer to each other; and said retracted position for said left wing (6) and said right wing (8) in front of said unfolded position, and in which a wing support (20) is attached to each wing (6, 8), said support wing (20) pivotally attached to said structure; in which joints (30) are interposed between said frame (10) and each of said wing supports (20), said joints (30) adapted to allow said wing supports (20) and said wings ( 6, 8) attached to these are articulated in relation to said frame (10); characterized by the fact that it additionally comprises: at least one lock (40) for each side edge (18) of said frame (10), each said lock (40) spaced from each said joint (30), said lock (40) adapted to releasably couple one of said wing supports (20) to said frame (10), said locks (40) having a locked configuration and an unlocked configuration with a movement preventing the locked configuration of said wing support (20) relative to said frame (10), and an unlocked position that allows said wing supports (20) to articulate on said articulation (30) relative to said frame (10).
    [0002]
    2. Flight vehicle (1) according to claim 1, characterized in that said frame (10) includes a pair of side edges (18) spaced by a width of said frame (10), and with a posterior edge extending between said lateral edges (18), said left articulation axis located closer to said posterior edge of said frame (10) than front portions of said frame (10), said articulation axis left located closer to a left of said lateral edges (18) than to a center line (CL) of said frame (10), said right pivot axis located closest to said rear edge of said frame (10) than front portions of said frame (10), said right pivot axis located closer to the right of said side edges (18) than to a center line (CL) of said frame (10).
    [0003]
    3. Flight vehicle according to claim 2, characterized by the fact that said left pivot axis and said right pivot axis are spaced by a distance similar to the width of said frame (10) between said edges sides (18).
    [0004]
    4. Flight vehicle according to claim 1, characterized by the fact that said frame (10) includes an upper plate (12) and a bottom plate (14), with said upper plate (12) parallel with said bottom plate (14), and with a gap between said top plate (12) and said bottom plate (14), said gap being at least as high as a thickness of said left wing (6) and of said right wing (8), such that said left wing (6) and said right wing (8) can adjust within said clearance when said wings (6, 8) are in said retracted position.
    [0005]
    5. Flight vehicle, according to claim 4, characterized by the fact that the front portions of said frame (10) opposite to said rear edge are open at said clearance, such that said wings (6, 8) can be to at least partially articulate in said clearance through portions of said frame (10) opposite said rear edge of said frame (10).
    [0006]
    6. Flight vehicle according to claim 5, characterized by the fact that said upper plate (12) and said bottom plate (14) include openings spaced in these spaced apart by ribs (15); and in which a rear plate (250) joins said upper plate (12) and said bottom plate (14) together adjacent said rear edge of said frame (10).
    [0007]
    7. Flight vehicle according to claim 1, characterized by the fact that said articulations (30) include a left articulation (30) and a right articulation (30), said left articulation located on said left articulation axis , said right pivot located on said right pivot axis, and in which said latches (40) include at least one latch (40) carried on said left wing support (20) (6) and at least one latch (40) ) carried on said right wing support (20) (8), each said latch (40) adapted to engage said frame (10) in at least one position on said corresponding frame (10) with an unfolded position for each said wing (6, 8).
    [0008]
    Flight vehicle according to claim 7, characterized in that said left wing support (20) (6) and said right wing support (20) (8) each support a plurality of locks (40) therein, each of said plurality of latches (40) spaced from said hinges (30), said plurality of latches (40) oriented vertically with a pair of stops (48) on each latch (40), with a stop (48) extending upwards, and the other stop (48) extending downwards, and in which said frame (10) includes holes (17, 19) in it selectively align with said stops (48) of said latches (40), said holes (17, 19) including a plurality of side holes (19) located adjacent the side edges (18) of said frame (10), and in which a plurality of said stops (48) engage the said side holes (19) of said frame (10) when said wing (6, 8) is in said unfolded position .
    [0009]
    9. Flight vehicle according to claim 8, characterized by the fact that said stops (48) of said locks (40) are manually activated to engage and disengage said holes (17, 19) in said frame (10).
    [0010]
    10. Flight vehicle according to claim 8, characterized by the fact that said stops (48) of said locks (40) are automatically activated to engage and disengage said holes (17, 19) in said frame (10) .
    [0011]
    11. Wing and frame assembly (10) for a flight vehicle (1) that defines retractable wings (6, 8), the assembly comprising in combination: a left wing (6); a right wing (8); a rigid frame (10); said frame (10) having a left pivot axis spaced from a right pivot axis, said vertically oriented and spaced pivot axes; said left wing (6) pivotally attached to said frame (10) and adapted to articulate with respect to said frame (10) on said left pivot axis; said right wing (8) pivotally attached to said frame (10) and adapted to articulate with respect to said frame (10) on said right pivot axis; and said wings (6, 8) adapted to articulate from an unfolded position more spaced from one another to a retracted position closer to each other, wherein said rigid frame (10) includes a left articulation (30) and a articulation (30) ) right, said left articulation (30) adapted to facilitate the articulation of said left wing (6) in relation to said structure, and the right articulation (30) adapted to facilitate the articulation of said right wing (8) in relation to said structure; characterized by the fact that it additionally comprises: at least one left latch (40) and at least one right latch (40), said latches (40) spaced from said joints (30), said latches (40) adapted to hold reliably said wings (6, 8) to said frame (10), especially in said deployed positions for said wings (6, 8).
    [0012]
    12. Assembly according to claim 11, characterized by the fact that said retracted position for said wings (6, 8) is located ahead of said deployed position of said wings (6, 8).
    [0013]
    13. Assembly according to claim 11, characterized in that said rigid frame (10) includes at least one plate oriented perpendicular to said left pivot axis and said right pivot axis, said at least one plate including side edges (18) spaced from each other and a rear edge extending between said side edges (18), said frame (10) configured to have said left wing (6) and said right wing (8) by at least partially superimposing said at least one plate vertically when said wings (6, 8) are in said retracted position.
    [0014]
    14. Assembly according to claim 11, characterized by the fact that said joints (30) include a left joint and a right joint, said left joint located on said left articulation axis, said right joint located on said right pivot axis, and in which said latches (40) include at least one latch (40) carried on said left wing support (20) (6), and at least one latch (40) carried on said support (20 ) of the right wing (8), each said latch (40) adapted to engage said frame (10) in at least one position on said corresponding frame (10) with an unfolded position for each said wing (6, 8).
    [0015]
    15. Assembly according to claim 14, characterized in that said left wing support (20) (6) and said right wing support (20) (8) each support a plurality of latches (40) ) in these, each of said plurality of latches (40) spaced from an adjacent one of said joints (30), said plurality of latches (40) each oriented vertically with a pair of stops (48) on each latch (40) , with one stop (48) extending upwards and the other stop (48) extending downwards, and in which said frame (10) includes holes (17, 19) in these selectively alignable with said stops (48 ) of said locks (40), said holes including a plurality of side holes (19) located adjacent to the lateral edges (18) of said frame (10), and in which a plurality of said stops (48) engage with said holes sides (19) of said frame (10) when said wing (6, 8) is in said position not unfolded.
    [0016]
    16. Assembly according to claim 15, characterized in that said frame (10) includes a pair of plates, said pair of plates spaced by a gap, said clearance having a height greater than a height of said left wing (6) and said right wing (8), such that said left wing (6) and said right wing (8) can articulate at least partially in said clearance.
    [0017]
    17. Assembly according to claim 16, characterized in that said frame (10) includes a pair of side edges (18) spaced by a width of said frame (10), and with a rear edge extending between said lateral edges (18), said left pivot axis located closer to said rear edge of said frame (10) than the front portions of said frame (10), said left pivot axis located closest to a left of said side edges (18) than to a center line (CL) of said frame (10), said right pivot axis located closer to said rear edge of said frame (10) than more front portions of said frame (10), said right pivot axis located closer to the right of said side edges (18) than to a center line (CL) of said frame (10); and in which said left pivot axis and said right pivot axis are spaced by a distance similar to a width of said frame (10) between said side edges (18).
    [0018]
    18. Flight vehicle with an oscillating wing, comprising in combination: a body supported on at least three wheels; a motor coupled to the body and adapted to provide forward thrust forces on the vehicle; a pair of wings (6, 8); a rigid frame (10) attached to said body; said wings (6, 8) pivotally attached to said frame (10) on joints (30) interposed between said wings (6, 8) and said frame (10); characterized by the fact that it also comprises: at least one latch (40) interposed between each of said pair of wings (6, 8) and said frame (10), said latches (40) spaced from said joints (30) said locks (40) adapted to hold said wings (6, 8) on said frame (10) when said wings (6, 8) are in an unfolded position.
    [0019]
    19. Vehicle according to claim 18, characterized in that said frame (10) includes a pair of opposite side edges (18), each of said side edges (18) of said frame (10) adapted for engaging a plurality of said latches (40) with said plurality of latches (40) interposed between each said wing and each said side edge (18) of said frame (10), with each of said plurality of latches (40) spaced of said joints (30), with said latches (40) carrying a majority of loads between said wing, adjacent to said side edge (18) of said frame (10), and said frame (10).
    [0020]
    20. Vehicle according to claim 19, characterized by the fact that said articulation is located behind a midline of said wings (6, 8) between a leading edge and a trailing edge of said wings (6, 8).
    [0021]
    21. Vehicle according to claim 18, characterized by the fact that said pair of wings (6, 8) are adapted to articulate joints and within a contour of said body when said wings (6, 8) are articulated on said joints (30) and related to said structure in a retracted position.
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    同族专利:
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    WO2012018382A3|2012-06-14|
    JP5960139B2|2016-08-02|
    US20120032023A1|2012-02-09|
    WO2012018382A2|2012-02-09|
    JP2014503400A|2014-02-13|
    US10293935B2|2019-05-21|
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    US20190300170A1|2019-10-03|
    ZA201301527B|2013-11-27|
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    法律状态:
    2018-12-26| B06F| Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]|
    2019-11-26| B06U| Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette]|
    2020-08-04| B06A| Patent application procedure suspended [chapter 6.1 patent gazette]|
    2020-11-17| B09A| Decision: intention to grant [chapter 9.1 patent gazette]|
    2021-02-02| B16A| Patent or certificate of addition of invention granted [chapter 16.1 patent gazette]|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 02/08/2011, OBSERVADAS AS CONDICOES LEGAIS. |
    优先权:
    申请号 | 申请日 | 专利标题
    US40089610P| true| 2010-08-03|2010-08-03|
    US61/400,896|2010-08-03|
    PCT/US2011/001355|WO2012018382A2|2010-08-03|2011-08-02|Flying vehicle retractable wing hinge and truss|
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