Abstract:
A rotary drive assembly is provided. The assembly includes a tip hinge box, a body hinge box pivotably coupled to the tip hinge box, a rotary actuator positioned within the body hinge box, and a linkage mechanism coupled between the rotary actuator and the tip hinge box, the linkage mechanism including a first linkage fixedly coupled to the rotary actuator, and a second linkage coupled between the first linkage and the tip hinge box, wherein rotation of the rotary actuator causes the tip hinge box to rotate relative to the body hinge box.

Description:
BACKGROUND 
       [0001]    The field of the disclosure relates generally to wing assemblies, and, more particularly, to rotary drive assemblies for rotating a wing tip relative to a wing body. 
         [0002]    The number of available airports that an aircraft is able to operate out of is typically limited, at least in part, by the size of the aircraft. Specifically, hanger and runway dimensions may prevent relatively large aircraft from operating out of smaller airports. For example, airports may be classified into different groups based on the permitted wingspans. 
         [0003]    Accordingly, at least some known wing assemblies enable an aircraft to decrease its wingspan once the aircraft has landed, allowing to aircraft to operate out of smaller airports. For example, at least some known wing assemblies facilitate rotating a wing tip relatively to the remainder of the wing to shorten the overall length of the wing. However, known assemblies may include a direct drive system that places relatively large strains on the rotation mechanism. Further, known assemblies may require relatively large and/or complex components that may be too large to fit within the wing. 
       BRIEF DESCRIPTION 
       [0004]    In one aspect a rotary drive assembly is provided. The assembly includes a tip hinge box, a body hinge box pivotably coupled to the tip hinge box, a rotary actuator positioned within the body hinge box, and a linkage mechanism coupled between the rotary actuator and the tip hinge box, the linkage mechanism including a first linkage fixedly coupled to the rotary actuator, and a second linkage coupled between the first linkage and the tip hinge box, wherein rotation of the rotary actuator causes the tip hinge box to rotate relative to the body hinge box. 
         [0005]    In another aspect, a wing assembly for an aircraft is provided. The wing assembly includes a wing body, a wing tip, and a rotary drive assembly coupling the wing body to the wing tip such that the wing tip is rotatable with respect to the wing body. The rotary drive assembly includes a tip hinge box extending from the wing tip, a body hinge box extending from the wing body and pivotably coupled to the tip hinge box, a rotary actuator positioned within the body hinge box, and a linkage mechanism coupled between the rotary actuator and the tip hinge box, said linkage mechanism including a first linkage fixedly coupled to the rotary actuator, and a second linkage coupled between the first linkage and the tip hinge box, wherein rotation of the rotary actuator causes the wing tip to rotate relative to the wing body. 
         [0006]    In yet another aspect a method of assembling a rotary drive assembly configured to rotate a wing tip relative to a wing body is provided. The method includes coupling a body hinge box extending from the wing body to a tip hinge box extending from the wing tip, positioning a rotary actuator within the body hinge box, and coupling a linkage mechanism between the rotary actuator and the tip hinge box, the linkage mechanism including a first linkage fixedly coupled to the rotary actuator and a second linkage coupled between the first linkage and the tip hinge box such that rotation of the rotary actuator causes the tip hinge box to rotate relative to the body hinge box. 
     
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         [0007]      FIG. 1  is a flow diagram of an exemplary aircraft production and service methodology. 
           [0008]      FIG. 2  is a block diagram of an aircraft. 
           [0009]      FIG. 3  is a perspective view of a wing assembly that may be used with the aircraft shown in  FIG. 2 . 
           [0010]      FIGS. 4-6  are perspective views of an exemplary rotary drive assembly that may be used with the wing assembly shown in  FIG. 3 . 
           [0011]      FIG. 7  is a perspective partial cut-away view of the rotary drive assembly shown in  FIG. 4 . 
           [0012]      FIGS. 8-10  are side views of the rotary drive assembly shown in  FIG. 4 . 
       
    
    
     DETAILED DESCRIPTION 
       [0013]    The systems and methods described herein provide a rotary drive assembly for a wing tip. The assembly includes a body hinge box coupled to a tip hinge box. A rotary actuator rotates the tip hinge box via a linkage mechanism. Notably, the linkage mechanism provides a mechanical advantage, putting less stress on the rotary actuator and facilitating the use of a relatively small rotary actuator. 
         [0014]    Referring more particularly to the drawings, implementations of the disclosure may be described in the context of an aircraft manufacturing and service method  100  as shown in  FIG. 1  and an aircraft  102  as shown in  FIG. 2 . During pre-production, exemplary method  100  may include specification and design  104  of aircraft  102  and material procurement  106 . During production, component and subassembly manufacturing  108  and system integration  110  of aircraft  102  takes place. Thereafter, aircraft  102  may go through certification and delivery  112  in order to be placed in service  114 . While in service by a customer, aircraft  102  is scheduled for routine maintenance and service  116  (which may also include modification, reconfiguration, refurbishment, and so on). 
         [0015]    Each of the processes of method  100  may be performed or carried out by a system integrator, a third party, and/or an operator (e.g., a customer). For the purposes of this description, a system integrator may include without limitation any number of aircraft manufacturers and major-system subcontractors; a third party may include without limitation any number of venders, subcontractors, and suppliers; and an operator may be an airline, leasing company, military entity, service organization, and so on. 
         [0016]    As shown in  FIG. 2 , aircraft  102  produced by exemplary method  100  may include an airframe  118  with a plurality of systems  120  and an interior  122 . Examples of high-level systems  120  include one or more of a propulsion system  124 , an electrical system  126 , a hydraulic system  128 , and an environmental system  130 . Any number of other systems may be included. Although an aerospace example is shown, the principles of the disclosure may be applied to other industries, such as the automotive industry. 
         [0017]    Apparatuses and methods implemented herein may be employed during any one or more of the stages of production and service method  100 . For example, components or subassemblies corresponding to production process  108  may be fabricated or manufactured in a manner similar to components or subassemblies produced while aircraft  102  is in service. Also, one or more apparatus implementations, method implementations, or a combination thereof may be utilized during production stages  108  and  110 , for example, by substantially expediting assembly of or reducing the cost of aircraft  102 . Similarly, one or more of apparatus implementations, method implementations, or a combination thereof may be utilized while the aircraft  102  is in service, for example and without limitation, to maintenance and service  116 . 
         [0018]      FIG. 3  is a perspective view of an exemplary wing assembly  300  that includes a wing body  302  and a wing tip  304 . Wing assembly  300  may be included, for example, on aircraft  102  (shown in  FIG. 2 ). Wing body  302  extends from a first end  306  to a second end  308 , and wing tip extends from a first end  310  to a second end  312 . Wing body second end  308  is rotatably coupled to wing tip first end  310  using a rotary drive assembly  320 , as described in detail. More specifically, wing tip  304  is selectively rotatable between a first position (shown in  FIG. 3 ), in which wing tip  304  is oriented substantially parallel to wing body  302 , and a second position, in which wing tip  304  is oriented upright and substantially orthogonal to wing body  302 . 
         [0019]    Accordingly, by rotating wing tip  304  from the first position to the second position, an overall length, L, of wing assembly  300  is reduced. During flight, wing tip  304  is fixed in the first position. However, once aircraft  102  lands, wing tip  304  may be switched to the second position. Thus, the overall profile of aircraft  102  can be reduced during ground maneuvers (e.g., taxiing, parking, etc.). Accordingly, because the profile of aircraft  102  is reducible upon landing, aircraft  102  may be certified to operate out of smaller airports (e.g., airports that aircraft  102  would be too large to operate out of without rotating wing tip  304 ). 
         [0020]      FIGS. 4-6  are perspective views of rotary drive assembly  320 . In the exemplary implementation, rotary drive assembly  320  includes a body hinge box  402  that extends from wing body  302  and a tip hinge box  404  that extends from wing tip  304 . As shown in  FIG. 4 , body hinge box  402  is coupled to tip hinge box  404  in an interlocking relationship. Specifically, in the exemplary implementation body hinge box  402  is coupled to tip hinge box  404  using bushings  410 . Each bushing  410  extends through apertures formed in body hinge box  402  and tip hinge box  404 . Alternatively, body hinge box  402  may be coupled to tip hinge box  404  using any connection mechanism(s) that enables rotary drive assembly  320  to function as described herein. A skin (not shown) of aircraft  102  covers components of rotary drive assembly  320  to protect rotary drive assembly  320 . 
         [0021]    To rotate wing tip  304  between first and second positions, body hinge box  402  rotates with respect to tip hinge box  404 , as described herein. In  FIG. 4 , wing tip  304  is in the first position, in  FIG. 5 , wing tip  304  is in an intermediate position between the first and second positions, and in  FIG. 6 , wing tip  304  is in the second position. 
         [0022]    As seen best in  FIGS. 5 and 6 , in the exemplary implementation, a pair of fittings  414  are coupled to tip hinge box  404 . Each fitting  414  includes two apertures  416  defined therein. When wing tip  304  is placed in the first position, four latch pins (not shown) extend from wing body  302  and are received in respective apertures  416 , locking wing tip  304  in the first position. 
         [0023]      FIG. 7  is a perspective partial cut-away view of rotary drive assembly  320 . Further, in  FIG. 7 , wing tip  304  and tip hinge box  404  have been removed for clarity. As shown in  FIG. 7 , rotary drive assembly  320  includes a rotary actuator  430  housed within body hinge box  402 . In the exemplary implementation, rotary actuator  430  is a geared rotary actuator (GRA). Alternatively, rotary actuator  430  may be any type of actuator that enables rotary drive assembly  320  to function as described herein. 
         [0024]    Rotary actuator  430  enables rotary drive assembly  320  to move wing tip  304  between the first and second positions. Specifically, a drive shaft  432  extends into wing body  302  and is coupled to rotary actuator  430 . Further, a linkage mechanism  434  is coupled between rotary actuator  430  and tip hinge box  404 . When drive shaft  432  drives rotary actuator  430 , rotary actuator  430  rotates linkage mechanism  434 , rotating tip hinge box  404 , and accordingly, wing tip  304 . 
         [0025]    In the exemplary implementation, linkage mechanism  434  includes a first linkage  440  and a second linkage  442 . First linkage  440  is fixedly coupled to rotary actuator  430  such that first linkage  440  rotates when rotary actuator  430  rotates. In the exemplary implementation, as shown in  FIG. 7 , first linkage  440  includes a pin  450  that extends between two parallel arms  452  at a first end  456  of first linkage  440 . Pin  450  is coupled to rotary actuator  430  also extends into an aperture  458  formed in body hinge box  402 . Pin  450  rotates freely within aperture  458  such that first linkage  440  rotates with respect to body hinge box  402 . Alternatively, first linkage  440  may have any configuration that enables rotary drive assembly  320  to function as described herein. 
         [0026]    A first end  470  of second linkage  442  is rotatably coupled to a second end  460  of first linkage  440 . Specifically, second linkage  442  includes a pin  472  that is received in apertures  462  formed in arms  452  of first linkage  440 . Pin  472  rotates freely within apertures  462  such that second linkage  442  rotates with respect to first linkage  440 . A second end  474  of second linkage  442  is rotatably coupled to tip hinge box  404 , such that tip hinge box  404  rotates when second linkage  442  rotates. 
         [0027]      FIGS. 8-10  are side views of rotary drive assembly  320 . In  FIG. 8 , tip hinge box  404  is in the first position (corresponding to  FIG. 4 ), in  FIG. 9 , tip hinge box  404  is in the intermediate position between the first and second positions (corresponding to  FIG. 5 ), and in  FIG. 10 , tip hinge box  404  is in the second position (corresponding to  FIG. 6 ). 
         [0028]    As shown in  FIGS. 8-10 , rotating first linkage  440  with respect to body hinge box  402  causes tip hinge box  404  to rotate with respect to body hinge box  402 . Specifically, first linkage  440  rotates, causing second linkage  442 , which in turn causes tip hinge box  404  to rotate. 
         [0029]    As shown in  FIG. 8 , rotary actuator  430  rotates about a first axis  800 , and tip hinge box  404  rotates with respect to body hinge box  402  about a second axis  802 . Notably, first axis  800  is offset with respect to second axis  802 . Accordingly, rotary drive assembly  320  provides a mechanical advantage. For example, in one implementation for every 160 degrees that rotary actuator  430  rotates, tip hinge box  404 , and consequently, tip  304 , rotates 80 degrees. This requires less force from rotary actuator  430  than if rotary actuator  430  operated on second axis  802  to directly rotate tip  402 . Accordingly, rotary actuator  430  may be smaller than a direct-drive rotary actuator, which enables rotary actuator  430  to fit within body hinge box  402 . 
         [0030]    The implementations described herein provide a rotary drive assembly for a wing tip. The assembly includes a body hinge box coupled to a tip hinge box. A rotary actuator rotates the tip hinge box via a linkage mechanism. Notably, the linkage mechanism provides a mechanical advantage, putting less stress on the rotary actuator and facilitating the use of a relatively small rotary actuator. 
         [0031]    The implementations described herein provide improvements over at least some known wing assemblies. As compared to at least some known wing assemblies, the rotary drive assembly described herein includes a configuration that provides a mechanical advantage for a rotary actuator. Accordingly, while at least some known wing assemblies utilize a direct drive configuration (i.e., with little or no mechanical advantage), the systems and methods described herein facilitate reducing strain on the rotary actuator. Further, because of the linkage mechanism described herein, the size of the rotary actuator can be reduced, as compared to at least some known wing assemblies. 
         [0032]    This written description uses examples to disclose various implementations, which include the best mode, to enable any person skilled in the art to practice those implementations, including making and using any devices or systems and performing any incorporated methods. The patentable scope is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they have structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal language of the claims.