Abstract:
An unmanned air vehicle designed for reconnaissance, surveillance, data acquisition, and general research. The vehicle is a monoplane that is comprised of several pieces that can easily be assembled using a minimal amount of tools. The aircraft consists of a forward and aft fuselage section, two identical horizontal stabilizers, and four identical wing sections. The aircraft can fly with all four wing sections, or with just two wing sections (the short wing configuration). This makes the aircraft usable for missions requiring short takeoff and landing and high endurance (long wing), or missions requiring higher speed and range (short wing). No other UAV (or other aircraft) has this unique feature. Another novel aspect of the present invention is the wing control can be specially designed to increase the effectiveness of the wing control surface while minimizing the effect the control surface has on the overall aerodynamics of the wing, namely drag.

Description:
BACKGROUND OF INVENTION 
       [0001]    1. Field of Invention 
         [0002]    This invention relates generally to unmanned air vehicles (UAVs) and, more particularly, to engine powered unmanned air vehicles. 
         [0003]    2. Background Art 
         [0004]    Unmanned air vehicles are utilized to perform various tasks such as, for example, reconnaissance and surveillance, data acquisition, and general research such as the study of weather patterns. Unmanned air vehicles can take on various forms from gas filled inflatables such as helium balloons, to gliders, to engine powered aircraft. Engine powered aircraft certainly have their advantages in that they can typically fly over and cover long ranges more quickly, fly at higher altitudes, carry heavier payloads to higher altitudes and over longer distances, can typically be controlled with greater agility over a larger flight envelope, and can typically be designed with more versatile all-weather capability. 
         [0005]    However, engine powered unmanned air vehicles have their shortcomings. For example, engine powered unmanned vehicles are typically more difficult to stow and transport than other unmanned air vehicles such as, for example, a gas filled inflatable. Also, an engine powered air vehicle will likely have a higher initial cost to build or purchase. There is also likely a greater cost to maintain and repair, particularly in the case of the air vehicle&#39;s airframe. Further, the takeoff or launch area for the air vehicle may be limited such that some air vehicles may have problems taking off. 
         [0006]    A more versatile engine powered unmanned air vehicle design is needed that captures the benefits of an engine powered air vehicle while overcoming the shortcomings, thus providing a more versatile and capable vehicle. 
       BRIEF SUMMARY OF INVENTION 
       [0007]    The invention is a modular unmanned air vehicle designed for reconnaissance, surveillance, data acquisition, and general research. The air vehicle can be a monoplane design that is comprised of several pieces or modular components that can easily be assembled using a minimal amount of tools. The aircraft can comprise of a forward and aft fuselage section, two identical horizontal stabilizers, and four identical wing sections. 
         [0008]    The aircraft can be designed so that it can be disassembled into several small pieces or modular components, which provides several advantages. First, the modular design makes transporting the aircraft much easier because it can be disassembled into its modular components for ease of stowing and transporting. Second, if the aircraft incurs any local damage to one or more of the modular components, the damaged part can simply be replaced rather than repaired. This decreases the life-cycle cost of the aircraft, as repairing fiberglass can be a difficult and costly process. Lastly, this can allow the user to fly the aircraft with all four wing sections (the long wing configuration) or with just two wing sections (the short wing configuration). This makes the aircraft usable for missions requiring short takeoff and landing and high endurance (long wing), or missions requiring higher speed and range (short wing). No other UAV (or other aircraft) has this unique feature. 
         [0009]    Another novel aspect of the present invention is the wing control can be specially designed to increase the effectiveness of the wing control surface while minimizing the effect the control surface has on the overall aerodynamics of the wing, namely drag. The upper skin of the wing can be used as the hinge for the control surface. This allows for a seamless upper wing surface, which increases the lift to drag of the wing. Thus the wing and the control surface can be one piece, which is unique. This one piece is also interchangeable with the other three wing pieces, which is also unique. 
         [0010]    The usable payload bay can be designed to be capable of carrying two standard —volume—weight boxes, which is much more than the capacity of a typical UAV of this size. Also, the hatch for the payload bay can be designed to be extremely large, which allows easy access to, and loading of, the payload bay. This can be accomplished by designing the sub-structure so that the load that is received when the payload is loaded through the top of the fuselage can be transferred down to the sides of the fuselage. 
         [0011]    The aircraft can be designed with a very long engine mount, which can extend the engine well beyond the firewall. This can be done so that the aircraft can accommodate several different engines. Also, if a heavier engine is used, then the length of the engine mount could be modified so the center of gravity of the aircraft remains the same. This is also a unique feature of this design. 
         [0012]    The horizontal tail can be designed as an all moving control surface so that the aircraft can easily be controlled in both configurations—long and short wing. Although not unique, this is unusual and provides a unique capability for this configuration. 
         [0013]    These and other advantageous features of the present invention will be in part apparent and in part pointed out herein. 
     
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS  
         [0014]    For a better understanding of the present invention, reference may be made to the accompanying drawings in which: 
           [0015]      FIG. 1  is a partially exploded isometric view of an unmanned air vehicle; 
           [0016]      FIG. 1  contains an isometric view of the joint for the wing sections; 
           [0017]      FIG. 2  is a side view of the unmanned vehicle; 
           [0018]      FIG. 3  is a top plan view of the unmanned vehicle; 
           [0019]      FIG. 4  is a bottom plan view of the unmanned vehicle; and 
           [0020]      FIG. 5  is a front view of the unmanned vehicle. 
       
    
    
     DETAILED DESCRIPTION OF INVENTION 
       [0021]    According to the embodiment(s) of the present invention, various views are illustrated in  FIG. 1-5  and like reference numerals are being used consistently throughout to refer to like and corresponding parts of the invention for all of the various views and figures of the drawing. Also, please note that the first digit(s) of the reference number for a given item or part of the invention should correspond to the FIG. number in which the item or part is first identified. 
         [0022]    One embodiment of the present invention comprising a monoplane airframe including various modular components including modular wing sections and forward and aft fuselage sections figures a novel apparatus for a modular unmanned vehicle. 
         [0023]    The details of the invention and various embodiments can be better understood by referring to the figures of the drawing. Referring to  FIG. 1 , a partially exploded isometric view of an unmanned air vehicle is shown. The modular structure of the airframe is illustrated by this exploded view. The modular airframe  100  includes a left modular wing  102  and a right modular wing  104 . Each of the modular wings,  102  and  104 , each comprise primary wing sections  106  and  108  and extension wing sections  110  and  112 . Modular sections  102  and  104  of the wing are utilized without the extensions for the short wing configuration of the UAV. The modular airframe structure also includes forward and aft fuselage sections  114  and  116  respectively. The aft fuselage section  116  includes left and right all moving horizontal tail wings  118  and  120 . The entire wing surface of the tail wing can act as a moving control surface to allow for better maneuverability when utilizing the short wing configuration. The aft fuselage also includes a vertical stabilizer  122  having a rear vertical aileron  124 . 
         [0024]    However, unlike the horizontal tail wings  118  and  120 , the left and right modular wings include the left and right primary ailerons and the left and right extended ailerons. The ailerons or control surfaces for the left and right wings can be designed such that the upper skin of the wing is utilized as a hinge for the controlled surface or the aileron. This design increases the effectiveness of the control surface while minimizing the effect the control surface has on the overall aerodynamics of the wing, namely drag. The upper skin of the wing is utilized as a hinge for the control surface. This design provides for a seamless upper wing surface which increases the lift to drag ratio of the wing. 
         [0025]    The control surfaces can be controlled or manipulated with hydraulics or other appropriate systems such as, for example, electrical and/or electromechanical systems. 
         [0026]    Therefore, the wing and the control surface are manufactured in one piece. A given modular wing section such as wing section  106  is interchangeable with all other wing sections as indicated as  108 ,  110  and  112 . End cap pieces (not shown) can also be installed on the end of the wing for aesthetic purposes. 
         [0027]    The forward fuselage section  114  includes a payload bay that is capable of carrying various items of greater capacity than what is typically carried by unmanned air vehicles of the same size. The hatch for the payload bay can be designed such that it is extremely large, allowing for easy access and loading and unloading of the payload bay. The payload bay can be designed with a substructure so that the load can go through the top of the forward fuselage and lowered down into the fuselage payload bay. A nose section  126  can be mounted forward of the forward fuselage. The nose section can have a propeller operably and rotatably mounted thereto and a front landing gear. The forward fuselage can have a wing mount  128  attached to the lower portion of its side. The primary wing section is mounted to the wing mount  128 . The extension portion of wing  110  can then be mounted to the primary section  106  by the wing joint interface  130 . 
         [0028]    The wing joint interface  130  is further detailed in  FIG. 1  which shows a mounting shaft  132  extending from the primary wing section  106  which is inserted through a receptacle within the wing section  110 . The receptacle for receiving the mounting shaft  132  is not shown in this view. One or more set screws  134  can be utilized to affix the mounting shaft  132  into the receptacle of the wing extension portion  110 .  FIG. 1  further details the wing control surface. As can be seen from this view, the wing section  106  and the aileron section  140  can be designed to share a common and continuous upper skin  136  that is flexible such that a hinge strip  138  is formed along the juncture of the wing and the aileron. Other mounting interfaces can be utilized that do not require set screws. 
         [0029]    Referring to  FIG. 2 , a side view of the unmanned vehicle is shown. This side view reveals the interface between the nose section  126  and the forward fuselage section  114 . The engine mounting assembly  202  is shown mounted on the front portion of the forward fuselage  114 . The nose section is mounted over the engine mounting assembly  202 . A propeller can be inserted and rotatably mounted through an opening  204  of the nose section having a shaft operably connected between the propeller and the engine (not shown) mounted on the engine mounting assembly. The payload area is shown in dotted lines within the forward fuselage. The forward fuselage also has landing gear  206 . The aft fuselage section  116  can be designed with mounting appendages  208  and  210  such that the forward fuselage section can be mounted to the aft fuselage section. 
         [0030]    Referring to  FIG. 3 , a top plan view of the unmanned vehicle is shown. This top plan view further illustrates the modular sections of the unmanned air vehicle airframe. The airframe can be separated into its primary modular components such as, for example, the aft fuselage  116 , the forward fuselage  114 , the nose section  126 , the left and right primary wing sections  106  and  108  and the extended wing sections  110  and  112 . 
         [0031]    The airframe can be disassembled and shipped in these separate components. The modular components can be standardized such that replacement components can be utilized if any one of the modular components fail or are damaged during use or shipment. Further, each of the wing sections  106 ,  108 , 110  and  112  can all be interchangeable. This modular design can also allow a user to have multiple forward fuselages where each fuselage is configured differently with various different electronic components such as various surveillance equipment. A user can have multiple pre-configured fuselage sections with preinstalled payloads while only having one set of the other modular components, such as the wing sections and the nose and aft fuselage sections. 
         [0032]    Referring to  FIG. 4 , a bottom plan view of the unmanned vehicle is shown. This bottom plan view illustrates the position of the forward and aft landing gear. As shown, the aft landing gear can be designed such that the width of the aft landing gear does not extend beyond the width of the left and right wing mounts. The landing gear can be designed to be fixed and non-retractable as shown. The modular aircraft can be configured such that only the primary left and right wing sections are installed which can be referred to as the short wing configuration. The short wing configuration makes the aircraft usable for missions requiring higher speed and shorter range. When all four wing sections are installed, which can be referred to as the long wing configuration, the aircraft is usable for missions requiring short takeoff and landing and high endurance. 
         [0033]    Referring to  FIG. 5 , a front view of the unmanned vehicle is shown. This front view illustrates the position of the tail wings relative to the primary wings. This view also reveals a slight upward cantation of the left and right wings. The position of the propeller mounting is further illustrated in this frontal view. 
         [0034]    The unmanned air vehicle could be designed to be equipped with a typical transceiver for remotely transmitting control signals from the ground to control and maneuver the air vehicle from the ground. Another alternative is to have an on-board computerized control system that can be preprogrammed with a flight pattern that executes the flight pattern. 
         [0035]    The unmanned air vehicle can be powered by a combustion engine typical for the size of the air vehicle and payload capacity. Other power sources could also be utilized such as, for example, an electric motor. The airframe could be constructed of a light weight material typical for such an air vehicle, such as, for example, fiberglass or a light weight alloy or carbon fiber. The size of the overall air vehicle can also vary as well as the size of the modular sections, such as the size of the modular wing sections. 
         [0036]    The various modular unmanned vehicle design examples shown illustrate a novel apparatus that solves many of the shortcomings of engine powered unmanned air vehicles. A user of the present invention may choose any of the above unmanned air vehicle embodiments, or an equivalent thereof, depending upon the desired application. In this regard, it is recognized that various forms of the subject modular unmanned air vehicle could be utilized without departing from the spirit and scope of the present invention. 
         [0037]    As is evident from the foregoing description, certain aspects of the present invention are not limited by the particular details of the examples illustrated herein, and it is therefore contemplated that other modifications and applications, or equivalents thereof, will occur to those skilled in the art. It is accordingly intended that the claims shall cover all such modifications and applications that do not depart from the spirit and scope of the present invention. 
         [0038]    Other aspects, objects and advantages of the present invention can be obtained from a study of the drawings, the disclosure and the appended claims.