Abstract:
A quick connect-disconnect mount assembly is provided having
   a first dove tailed mounting bracket;   a second dove tailed mounting bracket;   wherein said first and second mounting bracket is constructed and arranged with male/female dove tail channels and further whereby said brackets are secured one to another using a single securing bolt that provides tension to effectuate said securing.

Description:
BACKGROUND OF THE INVENTION 
     Field of the Invention 
       [0001]    It is often desired to securely fasten one component to another in a manner that provides a secure connected relationship that is able to withstand various external forces. Those that operate aircraft face a special challenge due to a plurality of wind and vibrational forces that can act upon an externally mounted device. Additionally, although securing might be effectuated by permanent mountings, these are not suitable when it is desired to quickly remove and change externally mounted components. It is desired to find a system by which externally mounted components are secured efficiently to withstand various wind and vibrational forces of an aircraft and further whereby said externally mounted component can be quickly and easily removed and/or changed for another component. The present invention has addressed these difficulties by providing an article that quickly and easily secures onto an aircraft and provides a removable portion whereby an externally mounted article can be quickly and easily changed. 
       SUMMARY OF THE INVENTION 
       [0002]    The present invention is a mounting system whereby a quick connect-disconnect mount assembly comprising:
       a first dove tailed mounting bracket;   a second dove tailed mounting bracket;
 
wherein said first and second mounting bracket is constructed and arranged with male/female dove tail channels and further whereby said brackets are secured one to another using a single securing bolt that provides tension to effectuate said securing is used.
       
 
         [0005]    The assembly has a first mounting plate is constructed and arranged to secure to a mounting arm and a said second mounting plate is constructed and arranged to hold a desired component and to slidibly attach to said first mount plate. 
         [0006]    The assembly of claim  1  comprising an assembled configuration of each of said mounting plates and a disassembled configuration whereby said mounting plates are separated. 
     
    
     
       BRIEF DESCRIPTION OF THE SEVERAL VIEWS OF THE DRAWING 
         [0007]      FIG. 1  is a side view showing the quick disconnect component mount assembly of the present invention. 
           [0008]      FIG. 2  is an exploded isometric of the quick disconnect mount of the present invention. 
           [0009]      FIG. 3  is a partially exploded plan view of the quick disconnect mount of the present invention. 
           [0010]      FIG. 4  is a plan view of the assembled quick disconnect mount of the present invention. 
       
    
    
     DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT 
       [0011]    In a preferred embodiment the assembly  10  is constructed and arranged to secure to an airframe  29  of an aircraft. The aircraft can be an airplane, helicopter, dirigible, and the like. It is contemplated that a component  30  is easily attached and subsequently detached using assembly  10  of the present invention. Component  30  typically is some type of camera or photographic device. However, component  30  is not limited to such devices. The components are constructed and arranged with a male mount plate  11  constructed and arranged to interact with a female mount plate  12 . Male mount plate  11  is constructed and arranged with a pair of dovetail groove surface  19  along each of two longitudinal sides on female mount plate  11 . Male mount plate  12  is constructed and arranged with corresponding dovetail groove surfaces  20  along each of two longitudinal sides corresponding to and constructed and arranged to interact with dovetail surface groove  19  of female mount plate  11 . 
         [0012]    As best demonstrated in  FIG. 3 , female mount plate  11  is constructed and arranged such that it slidibly attaches along corresponding dove tail surfaces to the configuration demonstrated in  FIG. 4 . 
         [0013]    Bracket  12  is constructed and arranged to mount on rear mount arm  25  and rear mount  25  subsequently is constructed and arranged to attach at attaching point  31  to air frame  29 . Article  30  is mounted on female mount plate  11  such that the removal of article  30  being a typical component is quickly and efficiently accomplished by separation of female mount plate  11  from male mount plate  12 . The system can also include a second bracket assembly whereby forward mount arm  23  holds the component  30 . 
         [0014]    As best seen in  FIG. 2 , the quick removal procedure involves removal of nose bolt  15 . Nose bolt bracket  13  and a nose bolt bracket key  14  are secured onto male mount bracket  12  using nose bolt  15 . Furthermore female mount plate  11  when positioned within male mount plate  12  is constructed and arranged such that nose bolt  15  secures into female mount plate  11  as indicated by directional arrow in  FIG. 2 . To ensure attachment, a screw retaining wire  17  is passed through a wire-receiving cavity each of nose bolt  15  and nose bolt bracket mounting screws  16 . Each of nose bolt bracket mounting screws  16  secures nose bolt bracket  13  to threaded orifice  34  of female plate  11 . 
         [0015]    Thus a typical component  30  mounted on female mount plate  11  is slidably detached by the single action of removing nose bolt  15 . Thus, in combination it can be seen male mount plate  12  is attached to forward mount  23 . A desired component  30  is attached to female mount plate  11 . When female mount plate  11  is slid into position such that it mates with male mount plate  12 , female mount plate  11  is secured using the aforementioned nose bolt  15 . In order to quickly remove and/or change desired component  30  to a different desired component, nose bolt  15  is removed, female mount plate  11  is slidably removed from male mount plate  12  a second female mount plate  11  is slid into position and secured into place with male mount plate  12  by replacing nose bolt  15 . It has been discovered that the matching dove tail configurations provides increased stability and strength to mounting components of the present invention due to an increase of surface area contact. Furthermore, tapering the dove tails maximizes the surface contact. Additionally, the mounting of the present invention is advantageous because nose bolt  15  is utilized as a tension bolt rather than in shear. 
         [0016]    Shear force, as is known, is defined as the component of stress coplanar with a material cross section. Shear stress, or shear force arises from the force vector component parallel to the cross section. Tension force is measured along the direction of the force. The arrangement of slidable attachment, and mounting bolt applied in a generally coplanar direction with the slidable attachment, imparts a closure system where tension force secures each of plates  11  and  12  in position. In this arrangement, tension force is a force less than shear force or other forces that would be required in a different arrangement. 
         [0017]    While the invention has been described in its preferred form or embodiment with some degree of particularity, it is understood that this description has been given only by way of example and that numerous changes in the details of construction, fabrication, and use, including the combination and arrangement of parts, may be made without departing from the spirit and scope of the invention.