Abstract:
A rotary aircraft includes a cylindrical enclosure configured to form an open housing with a top opening and a bottom opening; a hover disc disposed within the open housing of the cylindrical enclosure and configured to direct airflow entering through the top opening, the hover disc forming a center opening; and a fan extending through the center opening of the hover disc and configured to direct airflow through the hover disc.

Description:
BACKGROUND 
     1. Field of the Invention 
     The present invention relates generally to rotary aircraft, and more specifically, to a vertical take-off and landing (VTOL) aircraft. 
     2. Description of Related Art 
     VTOL rotary aircraft are well known in the art and are effective means to provide vertical and horizontal lift capabilities during flight. For example,  FIG. 1  depicts a VTOL rotary aircraft  101  in accordance with a well-known embodiment. In the exemplary embodiment, aircraft  101  is a helicopter having a fuselage  103  and a rotor system  105  with a plurality of rotor blades  107  to create vertical and horizontal flight movement. 
     One problem commonly associated with aircraft  101  is the limited use. For example, it should be understood that rotor blades are exposed, thereby creating a potentially harmful situation to persons nearby. These features make the aircraft undesirable in scenarios wherein aircraft  101  is used as a drone. 
     Accordingly, there is a long-felt need for a safer rotary aircraft providing vertical and horizontal flight. 
    
    
     
       DESCRIPTION OF THE DRAWINGS 
       The novel features believed characteristic of the embodiments of the present application are set forth in the appended claims. However, the embodiments themselves, as well as a preferred mode of use, and further objectives and advantages thereof, will best be understood by reference to the following detailed description when read in conjunction with the accompanying drawings, wherein: 
         FIG. 1  is a simplified schematic of a conventional rotary aircraft; 
         FIG. 2  is an oblique view of a VTOL aircraft in accordance with a preferred embodiment of the present application; 
         FIG. 3  is a simplified schematic of a VTOL aircraft system; 
         FIG. 4  is a disassembled view of the VTOL aircraft of  FIG. 2 ; 
         FIG. 5  is a cross-sectional view of the VTOL aircraft of  FIG. 2 ; and 
         FIG. 6  is a cross-sectional view of a VTOL aircraft in accordance with an alternative embodiment of the present application. 
     
    
    
     While the system and method of use of the present application is susceptible to various modifications and alternative forms, specific embodiments thereof have been shown by way of example in the drawings and are herein described in detail. It should be understood, however, that the description herein of specific embodiments is not intended to limit the invention to the particular embodiment disclosed, but on the contrary, the intention is to cover all modifications, equivalents, and alternatives falling within the spirit and scope of the present application as defined by the appended claims. 
     DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT 
     Illustrative embodiments of the system and method of use of the present application are provided below. It will of course be appreciated that in the development of any actual embodiment, numerous implementation-specific decisions will be made to achieve the developer&#39;s specific goals, such as compliance with system-related and business-related constraints, which will vary from one implementation to another. Moreover, it will be appreciated that such a development effort might be complex and time-consuming, but would nevertheless be a routine undertaking for those of ordinary skill in the art having the benefit of this disclosure. 
     The system and method of use in accordance with the present application overcomes one or more of the above-discussed problems commonly associated with conventional VTOL aircraft. Specifically, the VTOL aircraft of the present application provides rapid and effective means maneuver horizontal and vertical flight motion without the fear of being struck by an impeller. These and other unique features of the system and method of use are discussed below and illustrated in the accompanying drawings. 
     The system and method of use will be understood, both as to its structure and operation, from the accompanying drawings, taken in conjunction with the accompanying description. Several embodiments of the system are presented herein. It should be understood that various components, parts, and features of the different embodiments may be combined together and/or interchanged with one another, all of which are within the scope of the present application, even though not all variations and particular embodiments are shown in the drawings. It should also be understood that the mixing and matching of features, elements, and/or functions between various embodiments is expressly contemplated herein so that one of ordinary skill in the art would appreciate from this disclosure that the features, elements, and/or functions of one embodiment may be incorporated into another embodiment as appropriate, unless described otherwise. 
     The preferred embodiment herein described is not intended to be exhaustive or to limit the invention to the precise form disclosed. It is chosen and described to explain the principles of the invention and its application and practical use to enable others skilled in the art to follow its teachings. 
     Referring now to the drawings wherein like reference characters identify corresponding or similar elements throughout the several views,  FIG. 2  depicts an oblique view of an aircraft  201  in accordance with a preferred embodiment of the present application. It will be appreciated that aircraft  201  overcomes the problems commonly associated with conventional aircraft. 
     Aircraft  201  could be utilized with a control system  301 , as depicted in  FIG. 3 , wherein the aircraft  201  is a drone manipulated by a controller  303  by user  305  and/or by a computer  309  via a wireless means, e.g., a cloud service provider  307 . Accordingly, it is contemplated autonomously and manually controlling the aircraft  201  during flight. It will also be appreciated that the system could further include sensors, cameras, and/or other devices carried by aircraft  201  for collecting and relaying data information to controller  303  and/or computer  309 . 
     In  FIG. 4 , an exploded detailed front view of the components of aircraft  201  are shown. Aircraft  201  includes one or more of a top plate  501  having a body  509  that forms an opening  511 , an enclosure  503  having a body  513  configured to secure to top plate  509  and forms an opening  515 , an exhaust vent  517  that fits within enclosure  513  and forms an opening  519 , a hover disc  504  having a body  521  that forms an opening  523  and includes a plurality of vertical vanes  525  extending therefrom a contoured surface  506 , a driver  508  having a motor  510  rotatably attached to a centrifugal fan  505  and a bottom plate  507 . 
     In the contemplated embodiment, a centrifugal fan is used; however, it will be appreciated that other types of propulsion device could be used in lieu of a fan. For example, a rotary system having a plurality of blades, a jet turbine, and the like are also contemplated in an alternative embodiment. 
     When assembled, the fan  505  extends through opening  523  and  511 , and as shown in  FIG. 5 , directs airflow through opening  511  to the top contoured surfaces  506  of body  521 , as depicted with a plurality of arrows. It will be appreciated that the fan  505  forces the air flow over the contoured surfaces  506 , which in turn creates lift. The airflow is further manipulated with the exhaust vents  517  for vertical and horizontal movement. 
     It will be appreciated that enclosure  513 , top plate  501 , vents  517 , and bottom plate  507  prevent fingers and other appendages of the user from coming into contact with the rotating members of aircraft  201 , thus preventing harm to the user. 
     Referring now to  FIG. 6 , a cross-sectional view of a hover disc  601  is shown in accordance with an alternative embodiment of the present application. It will be appreciate that system  201  could utilizes the features of disc  601 . In this contemplated embodiment, disc  601  includes a single body  603  having opposing contoured surfaces  605 ,  607  for creating lift. A bottom surface  609  is configured to run relatively parallel to the bottom plate. 
     The particular embodiments disclosed above are illustrative only, as the embodiments may be modified and practiced in different but equivalent manners apparent to those skilled in the art having the benefit of the teachings herein. It is therefore evident that the particular embodiments disclosed above may be altered or modified, and all such variations are considered within the scope and spirit of the application. Accordingly, the protection sought herein is as set forth in the description. Although the present embodiments are shown above, they are not limited to just these embodiments, but are amenable to various changes and modifications without departing from the spirit thereof.