Abstract:
A protection apparatus employed in the construction of aircraft can be collapsed to a small configuration to enable insertion of the apparatus to access openings in a structure of the aircraft, for example an access opening in a wing of the aircraft, to position the protection apparatus inside the aircraft structure. Once inside the aircraft structure, the protection apparatus can be expanded from its collapsed configuration and positioned over components in the aircraft structure, for example hydraulic tubing or electric wiring, to protect those components from damage by a worker working in the aircraft structure above the components.

Description:
FIELD 
       [0001]    This disclosure pertains to a protection apparatus employed in the construction of aircraft. In particular, this disclosure pertains to a protection apparatus that can be collapsed to a small configuration to enable its insertion through access openings in a structure of an aircraft, for example an access opening in a wing of an aircraft, to position the protection apparatus inside the aircraft structure. Inside the aircraft structure the protection apparatus can be expanded from its collapsed configuration and positioned over components in the aircraft structure, for example hydraulic tubing or electric wiring, to protect those components from damage by a worker working in the aircraft structure above the components. 
       BACKGROUND 
       [0002]    In the construction of aircraft it is often necessary to access an interior of a structure of the aircraft, for example a previously constructed aircraft wing in order to continue the construction of components inside the aircraft structure. Aircraft structures are typically constructed with access openings having panels covering the access openings. Each panel can be removed exposing the access opening and the interior of the structure. A worker can then pass through the access opening and continue to work on components of the aircraft located in the interior of the aircraft structure. 
         [0003]    Because there are previously constructed components inside the aircraft structure such as hydraulic tubing or electrical wiring, a worker entering the interior of the aircraft structure to continue work on other components must be careful to avoid damage to these previously constructed components. For example, the worker must be vigilant not to damage hydraulic tubing in an aircraft structure such as an aircraft wing by the worker dropping a tool on the tubing or by the worker unintentionally making damaging contact with the tubing while moving through the interior of the wing. The caution the worker must take when moving through the interior of the aircraft structure when continuing the construction of component parts inside the aircraft structure significantly contributes to the time needed to complete the construction of components in the aircraft structure. Furthermore, replacing internal components of an aircraft structure that have been inadvertently damaged by workers working inside the aircraft structure can add to the cost of the aircraft construction and the time required for the aircraft construction. 
       SUMMARY 
       [0004]    A protection apparatus disclosed herein can be used by a worker in the interior of an aircraft structure to avoid unintentionally damaging previously constructed components inside the aircraft structure. The apparatus can be collapsed by the worker to a reduced size configuration to enable insertion of the apparatus through an access opening in the aircraft structure. Once inside the aircraft structure, the apparatus can then be expanded by the worker to a larger configuration inside the aircraft structure. The apparatus is then positioned over previously constructed components of the aircraft inside the aircraft structure to protect those previously constructed components from potential damage by the worker working inside the aircraft structure in the vicinity of the previously constructed components. 
         [0005]    The protection apparatus is basically comprised of a first part and a second part that are mirror images of each other. The first and second parts can be constructed of rigid plastic or any other equivalent material that provides the parts with the structural strength the parts need for their intended function, yet is light weight to enable the apparatus to be easily manipulated. 
         [0006]    The first part of the apparatus has a support surface area on a top of the first part. The first part also has a bottom surface area opposite the support structure area. 
         [0007]    A first support leg is provided on the bottom surface area. The first support leg projects outwardly from the bottom surface to a distal end of the first support leg. 
         [0008]    The second part of the apparatus also has a support surface area on a top of the second part and a bottom surface area opposite the support surface area. 
         [0009]    A second support leg is also provided on the bottom surface area of the second part. The second support leg projects outwardly from the second bottom surface area to a distal end of the second support leg. 
         [0010]    A connection, for example a hinge connection connects the first part and the second part. The connection enables the first part and the second part to move between first relative positions and second relative positions of the first part and second part. In the first relative positions the first part and second part are moved or folded about the hinge connection to a collapsed, reduced size configuration. In the first relative positions the distal ends of the first support leg and the second support leg are moved toward each other to positions where they are adjacent. Additionally, the first support surface area and the second support surface area are moved toward each other and oriented at an angle. This collapsed configuration of the apparatus provides the apparatus with a reduced size configuration and enables the apparatus to be inserted through an access opening in an aircraft structure and into the interior of the aircraft structure. 
         [0011]    Once in the interior of the aircraft structure, a worker can move the collapsed apparatus to a work site location in the interior where the apparatus is used to protect previously constructed components of the aircraft structure while further construction is performed by the worker in the aircraft structure interior. 
         [0012]    Once at the work site in the aircraft structure interior, the apparatus can then be unfolded to its enlarged configuration where the first part and the second part are moved to their second relative positions. In the second relative positions of the first part and second part, the distal ends of the first support leg and the second support leg are spaced from each other. The spacing between the distal ends of the first support leg and second support leg enables the legs to be positioned on an interior surface of the aircraft structure on opposite sides of a previously constructed component to be protected by the apparatus. Additionally, the distance between the distal ends of the first support leg and second support leg enables the support legs to be positioned against adjacent stringers in the interior of the aircraft structure. This engagement of the support legs with the adjacent stringers provides further support to the apparatus. In the second relative positions of the first part and second part, the first support area and second support area form a continuous support surface over the previously constructed components in the interior of the aircraft structure. This continuous support surface protects the previously constructed components from potential damage by the worker working at the work site, for example from a dropped tool or a worker inadvertently exerting a force against the previously constructed component. 
         [0013]    The features, functions, and advantages that have been discussed can be achieved independently in various embodiments or may be combined in yet other embodiments, further details of which can be seen with reference to the following description and drawings. 
     
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         [0014]      FIG. 1  is a perspective view of the protection apparatus. 
           [0015]      FIG. 2  is a top plan view of the protection apparatus. 
           [0016]      FIG. 3  is a bottom plan view of the protection apparatus. 
           [0017]      FIG. 4  is a side elevation view of a first side of the protection apparatus, with the opposite side elevation view of the second side of the protection apparatus being a mirror image thereof. 
           [0018]      FIG. 5  is an end elevation view of a first end of the protection apparatus, with the opposite end elevation view of the second end of the protection apparatus being a mirror image thereof. 
           [0019]      FIG. 6  is an end elevation view of the protection apparatus folded or moved to its collapsed configuration. 
           [0020]      FIG. 7  is a representation of access openings in an aircraft structure. 
           [0021]      FIG. 8  is a representation of use of the apparatus in the interior of an aircraft structure. 
       
    
    
     DESCRIPTION 
       [0022]      FIG. 1  is a perspective view of the protection apparatus  10  of this disclosure in an expanded, enlarged configuration of the apparatus  10 . As stated earlier, the apparatus  10  is constructed of two parts  12 ,  14  that are mirror images of each other. Both the first part  12  and the second part  14  are constructed of materials that provide the apparatus  10  with sufficient strength for its intended purpose, without significantly increasing the weight of the apparatus. This enables the apparatus  10  to be easily manipulated and moved by a worker. For example, the first part  12  and the second part  14  could be constructed of rigid plastic, or other equivalent materials. Because the first part  12  and the second part  14  are mirror images of each other, only the first part  12  will be described in detail herein. The reference numbers used to label the first part  12  will also be used to label corresponding portions of the second part  14 , but with the reference number followed by a prime (′). 
         [0023]    The first part  12  of the apparatus  10  has a support surface area  16  on a top of the first part. The first part  12  also has a bottom surface  18  opposite the top surface area  16 . The support surface areas  16 ,  16 ′ of both the respective first part  12  and second part  14  make up the support surface on the top of the apparatus  10 . The first support surface area  16  is planar and has a general rectangular configuration. The rectangular configuration of the first surface area  16  is defined by an inboard edge  20  and an opposite outboard edge  22  of the surface area, and a first end edge  24  and an opposite second end edge  26  of the surface area. The first surface area  16  has a width dimension between the inboard edge  20  and the outboard edge  22  and a length dimension between the first end edge  24  and the second end edge  26 . 
         [0024]    The inboard edge  20  of the first part  12  is formed with a plurality of hinge knuckles  32 . The hinge knuckles  32  of the first part  12  are positioned to alternate with the hinge knuckles  32 ′ of the second part  14 . A pivot pin  34  is inserted through center holes (not shown) of the interleaved hinge knuckles  32 ,  32 ′ forming a connection  36  between the first part  12  and the second part  14 . The connection  36  enables the first part  12  and the second part  14  to be moved between first and second relative positions. 
         [0025]    A first support leg  38  is provided on the bottom surface area  18  of the first part  12 . The support leg  38  is fixed at an angle relative to the support surface area  16 . As best seen in  FIG. 4 , the first support leg  38  is constructed with three sections  38 ,  40 ,  42  with open voids  44 ,  46  between adjacent sections. The three sections  38 ,  40 ,  42  are arranged in line and are spaced across the entire length dimension of the first part  12 . In other embodiments the first part  12  could have more than the three leg sections  38 ,  40 ,  42  shown, or fewer leg sections. Each of the leg sections  38 ,  40 ,  42  projects outwardly from the bottom surface  18  of the first part  12  to respective distal ends  48 ,  50 ,  52  of the leg sections. 
         [0026]    A first support surface extension  56  is provided on the top surface area  16  of the first part  12 . The first support surface extension  56  could be an integral part of the first part  12 , or be attached to the first part top surface area  16  by a plurality of threaded fasteners  58  as represented in the drawing figures. The first support surface extension  56  is planar and has a general rectangular configuration. The rectangular configuration is defined by an inboard edge  62  and an opposite outboard edge  64  on opposite sides of the width of the first support surface extension  56 , and a first end edge  66  and an opposite second end edge  68  on opposite ends of the length of the first support surface extension  56 . As represented in the drawing figures, the first end edge  66  of the first support surface extension  56  is aligned with the first end edge  24  of the top surface area  16  of the first part  12 , and the second end edge  68  of the first support surface extension  56  is aligned with the second end edge  26  of the top surface area  16  of the first part  12 . The first support surface extension  56  is attached to the top surface area  16  of the first part  12  along the inboard edge  62  of the first support surface extension  56 . The width of the first support surface extension  56  projects outwardly from the outboard edge  22  of the first part  12  to the outboard edge  64  of the first support surface extension  56 . Thus, the width of the first support surface extension  56  positions the extension outboard edge  64  outwardly from the outboard edge  22  of the top surface area  16  of the first part  12 . 
         [0027]    The connection  36  formed between the first part  12  and the second part  14  by the hinge knuckles  32 ,  32 ′ and the pivot pin  34  enables the first part  12  and second part  14  to move between first relative positions and second relative positions. In the first relative positions, the first part  12  and second part  14  are moved or folded about the hinge connection  36  to a collapsed, reduced size configuration represented in  FIG. 6 . In the first relative positions, the distal ends  48 ,  50 ,  52 ,  48 ′,  50 ′,  52 ′ of the support legs are moved toward each other to positions where they are adjacent and contact as represented in  FIG. 6 . Additionally, the first support surface area  16  of the first part  12  and the first support surface area  16 ′ of the second part  14  are oriented at an angle as represented in  FIG. 6 . This collapsed configuration of the apparatus  10  provides the apparatus  10  with a reduced size configuration that enables a worker  76  to insert the apparatus  10  end first through an access opening  78  in an aircraft structure  80  and into the interior of the aircraft structure as represented in  FIG. 7 . 
         [0028]    Once the apparatus  10  is in the interior of the aircraft structure, a worker can move the collapsed apparatus  10  to a work site location in the interior where the apparatus  10  is used to protect previously constructed components of the aircraft structure while further construction is performed by the worker in the aircraft structure interior. 
         [0029]    Once at the work site in the aircraft structure interior, the apparatus  10  can then be unfolded to its enlarged configuration where the first part  12  and the second part  14  are moved to their second relative positions. In the second relative positions of the first part  12  and the second part  14 , the distal ends of the first support leg  48 ,  50 ,  52  and the distal ends of the second support leg  48 ′,  50 ′,  52 ′ are spaced from each other as represented in  FIGS. 1 and 5 . The spacing between the first leg distal ends  48 ,  50 ,  52  and the second leg distal ends  48 ′,  50 ′,  52 ′ enables the legs to be positioned on an interior surface of the aircraft structure on opposite sides of a previously constructed component to be protected by the apparatus as represented in  FIG. 8 . Additionally, the distance between the first leg distal ends  48 ,  50 ,  52  and the second leg distal ends  48 ′,  50 ′,  52 ′ enables the support legs to be positioned against adjacent stringers  82 ,  84  in the interior of the aircraft structure as represented in  FIG. 8 . This engagement of the support legs  38 ,  40 ,  42 ,  38 ′,  40 ′,  42 ′ with the adjacent stringers  82 ,  84  provides further support to the apparatus  10 . In the second relative positions of the first part  12  and the second part  14 , the first support surface area  16  and the second support surface area  16 ′ form a continuous support surface over the previously constructed components in the interior of the aircraft structure. The continuous support surface protects the previously constructed components from potential damage by the worker working at the work site, for example from a dropped tool or a worker inadvertently exerting a force against the previously constructed component. 
         [0030]    As various modifications could be made in the construction of the apparatus and its method of operation herein described and illustrated without departing from the scope of the invention, it is intended that all matter contained in the foregoing description or shown in the accompanying drawings shall be interpreted as illustrative rather than limiting. Thus, the breadth and scope of the present disclosure should not be limited by any of the above described exemplary embodiments, but should be defined only in accordance with the following claims appended hereto and their equivalents.