Abstract:
An aerial seeding system that may be installed in an aircraft in a modular form with minimal modification to the existing aircraft configuration, and, in particular, without any structural modifications that would adversely impact the integrity of the aircraft structure or its overall air worthiness. Exemplary embodiments disclosed provide an active and controllable seed distribution mechanism to ensure continuously controllable and even distribution of seeds. Basic system components include a modular seed hopper, a seed broadcasting head and a hydraulic system driven by a pump connected to an aircraft accessory drive.

Description:
RELATED APPLICATION DATA 
       [0001]    This application claims the benefit of priority of U.S. Provisional Patent Application Ser. No. 62/199,688, filed on Jul. 31, 2015, and titled “Aircraft Seed Broadcasting Apparatus,” which is incorporated by reference herein in its entirety. 
     
    
     FIELD OF THE INVENTION 
       [0002]    The present disclosure relates to aircraft seed broadcasting, and, more particularly, to modularized systems, and related apparatus and methods to provide aircraft mounted seed broadcasting without structural modifications to the aircraft. 
       BACKGROUND 
       [0003]    Potential advantages associated with aerial seeding or sowing are well-known in the agricultural industry. However, in spite of the potential, systems for aerial seeding are not well designed to exploit those advantages. Existing systems fall into generally two categories: systems based on crop dusting technology utilizing modifications to nozzle/sprayer systems intended primarily for liquids/pesticide application, and passive systems that utilize buckets, chutes or similar structures and which rely primarily on the turbulence surrounding the aircraft in motion to distribute the seeds. 
         [0004]    One challenge in creating an effective aerial seeding system is that in most countries modifications to licensed aircraft, such as airplanes and helicopters, must be approved by a governmental agency to ensure safety and airworthiness. In the United States, the agency is the Federal Aviation Administration (FAA). Under FAA regulations, not just modification, but also addition of equipment must meet stringent approval requirements. Thus, while the patent literature contains numerous different design proposals for seeding systems, few of these are practical or even useable due to the fact that they require either an entirely new aircraft or extensive changes, additions or modifications to be mounted and flown in an existing aircraft. 
       SUMMARY OF THE DISCLOSURE 
       [0005]    In one implementation, the present disclosure is directed to an aircraft seed broadcasting system that includes a seed hopper configured and dimensioned to be insertable through a door frame of an aircraft and mountable to pre-existing aircraft mounting points; a broadcasting head configured and dimensioned to be mounted to an underside of the aircraft fuselage below the seed hopper to broadcast seeds received from hopper; and a power supply system configured to drive the broadcasting head. 
         [0006]    In another implementation, the present disclosure is directed to an aircraft seed broadcasting system that includes a seed hopper comprising plural separable members each configured and dimensioned to be insertable individually through a passenger door frame of an aircraft, assembled into the seed hopper within the aircraft and mounted to existing passenger seat and seatbelt attachment points; a broadcasting head comprising a body defining a seed plenum leading to a motor driven rotating distribution disk, the body configured and dimensioned to be mounted along a centerline on an underside of the aircraft fuselage below the assembled and mounted seed hopper to receive seeds from the hopper; and power supply components configured to provide aircraft supplied power to the motor driven rotating distribution disk. 
         [0007]    In yet another implementation, the present disclosure is directed to a method of installing a seed broadcasting system in an aircraft. The method includes removing an aircraft passenger seat from a passenger space; inserting a seed hopper through an aircraft passenger door into the passenger space; forming at least one hole through a non-structural fuselage skin portion on the bottom of the aircraft in the passenger space; mounting the seed hopper to pre-existing mounting points in the passenger space with a feed chute extending through the at least one hole in the fuselage skin; mounting a seed broadcasting head including a motor driven rotating distribution disk on an underside of the aircraft fuselage in a position to communicate with the feed chute through the at least one hole to receive seeds therefrom; and connecting a broadcasting hydraulic system to a hydraulic pump driven by an accessory drive to power the motor driven rotating head. 
     
    
     
       DESCRIPTION OF THE DRAWINGS 
         [0008]    For the purpose of illustrating the invention, the drawings show aspects of one or more embodiments disclosed herein. However, it should be understood that the inventions embodied in this disclosure are not limited to the precise arrangements and instrumentalities shown in the drawings, wherein: 
           [0009]      FIG. 1  is a partial starboard side view of an aircraft with an exemplary embodiment of an aerial seed broadcasting system installed therein. 
           [0010]      FIG. 2  is a partial port side view of the aircraft shown in  FIG. 1  with the embodiment of the disclosed system. 
           [0011]      FIG. 3  is a detailed view of the rear seat area where portions of the exemplary broadcasting system are installed. 
           [0012]      FIG. 4  is a view of a hopper bottom installed in an aircraft in accordance with an exemplary embodiment disclosed herein. 
           [0013]      FIG. 5  is a view of a partially assembled hopper, with hopper walls mounted on the hopper bottom shown in  FIG. 4 . 
           [0014]      FIG. 6  is a detailed view of a seed broadcasting head according to an exemplary embodiment of the present disclosure, mounted on the underside of the aircraft fuselage. 
           [0015]      FIG. 7  is a close view of the broadcasting head shown in  FIG. 6  with a seed delivery duct removed for illustration purposes. 
           [0016]      FIG. 8  is a detailed plan view of internal components of the broadcasting head shown in  FIG. 6 . 
       
    
    
     DETAILED DESCRIPTION 
       [0017]    Embodiments disclosed herein provide a system for aerial broadcasting of seeds or other similar materials in modular form to facilitate installation and removal from the aircraft. Also disclosed are methods for installing such a modular system without altering airworthiness. Modules may generally comprise a seed hopper, broadcasting head and hydraulic supply components. In one embodiment disclosed herein, as shown in  FIGS. 1 and 2 , an aircraft seed broadcasting system includes a seed hopper  10  mountable in a passenger space or rear seat area of the aircraft, and a broadcasting head  12  mounted to the underside of the aircraft fuselage to broadcast seeds received from hopper  10 . A seed input port  14  is provided in an upper portion of the hopper wall, and sight gage  16  allows an operator to visually determine the fill level of the hopper. Vents  18 ,  20  are provided at the top of hopper  10 . 
         [0018]    Components of disclosed embodiments may be readily fabricated from aviation quality materials and incorporated into the aircraft with a minimum of alteration to the aircraft. In one illustrative example, an embodiment of the disclosed system is installed in a four-place R-44 series helicopter by the Robinson Helicopter Company as shown in the present figures. As will be appreciated by those skilled in the art, the disclosed system may be readily adapted to other aircraft types without significant changes. While persons of ordinary skill may adapt embodiments disclosed herein to virtually any aircraft, aircraft most suited for use with embodiments of the invention include fixed wing or helicopter aircraft with a passenger space/seat positioned behind the pilot position, enterable by at least one passenger door. To facilitate installation and minimize aircraft alterations, attachment points for system components may solely comprise preexisting aircraft mounting points, such as seat support structure and seatbelt attachments. In the illustrated example, hopper  10  is mounted in the rear passenger compartment with attachment points encompassing all six of the seat belt hard points to secure the unit. 
         [0019]    As described in more detail below and shown in  FIG. 2 , broadcasting head  12  is powered by a hydraulic motor which receives hydraulic fluid pressure generated by an existing aircraft system, such as the air conditioning system. In the illustrated Robinson R-44 embodiment, system power is provided by a factory-approved air conditioning drive mounted to the left-hand, rear drive pad of the O-540 engine. A separate hydraulic tank  22  is provided for the broadcasting head hydraulic system. Tank  22  has a tank vent  24  and hydraulic supply and return lines  28 ,  25 . The hydraulic lines are routed to broadcasting head  12  via conduit  26 . 
         [0020]    As illustrated in  FIG. 2 , hydraulic tank  22  may be attached to the left side of the R-44 helicopter using two 0.75×0.040 stainless steel band clamps fastened to 0.050 plate of 2024 T3 aluminum with four MS27039-1-20 screws, four AN970-3 washers and four MS21042L3 nuts. The 0.050 plate is attached to the helicopter using five preexisting MS21069L08 nut plates and five MS27039-0808 screws along the forward facing and top edge of the plate. Two additional MS27039-1-14 screws, two MS21042L3 nuts and two MS21919WDG16 clamps attach the middle and aft ledge of the plate to the C046-19 Robinson lower-left frame assembly. 
         [0021]    To install hopper  10 , the rear seat of the aircraft is removed and hopper mounting stringer  30  is bolted to the existing seat support structure as shown in  FIG. 3 . In one exemplary embodiment as illustrated, stringer  30  may be constructed out of 0.032 2024 T3 aluminum and fitted with 12 MS21075-08L nut plates where 12 MS27039-0808 screws attach the stringer to the vertical forward face of the seat bottom using the pre-existing holes that the seat cushions utilize when the seat bottoms are installed. Stringer  30 , once installed, provides twenty MS21075-08L nut plates to which the hopper bottom can be attached to the airframe. 
         [0022]    Hopper  10  may be constructed from six sub-panels. Hopper bottom  32 , including generally pyramid-shaped feed chutes  34 A,  34 B, is bolted to stringer  30  through bolt holes  36  as shown in  FIG. 4 . In an exemplary embodiment, twenty bolt holes  36  are provided to accommodate twenty MS27039-0808 screws that pass down through the hopper bottom  32  and attach to stringer  30 . Mounting brackets  38  provide for connection to middle rear seat seatbelt attachment points. 
         [0023]    Hopper bottom  32  may be constructed out of 0.040 2024-T3 aluminum and riveted together with MS20470AD4-4 rivets. The attachment points and the four angles that encompass the perimeter of the panel are constructed from 6061T6 aluminum. There are four one inch angles which have twenty-two MS21075-08L nut plates riveted in place on a five inch spacing pattern to provide attachment points for the four vertical side panels of the hopper to attach to. Three panels, rear wall  40 , forward wall  42  and starboard wall  44 , are shown in  FIG. 5 . The port wall is removed to permit viewing of the interior of the hopper. The side panels making up the four hopper vertical walls may be constructed from 0.032 2024-T3 aluminum. The forward and aft walls  42 ,  40 , may have three one inch angles constructed from 6061T6 aluminum and riveted to these panels using MS20470AD4-4 rivets with eighteen MS21075-08L nut plates riveted in place on a five inch spacing pattern. The left and right walls may be constructed out of 0.032 2024-T3 aluminum and have one 6061T6 aluminum one inch angle attached to the top edge of these panels which holds 5 MS21075-08L nut plates on a five inch spacing pattern. The hopper top (not shown in the figures) may be constructed from 0.020 2024-T3 aluminum. Each hopper sidewall is provided with an interior stiffening member  48 ,  50 ,  54 . All six hopper panels are attached together utilizing the MS21075-08L nut plates and MS27039-0808 screws. All the panels are removable in order to fit hopper  10  into the aircraft one panel at a time so that the hopper may be assembled within the passenger space. 
         [0024]    Attachment brackets  55 A,  55 B are each attached to hopper  10  and to the aircraft rear seatbelt top attachment points. As best seen in  FIG. 5  (also  FIGS. 1 and 2 ), bracket  55 A is located on the left-hand side of the aircraft and the head of the NAS6604-18 bolt that the OEM uses to attach to the shoulder harness guide assembly of the seatbelt to the airframe can be seen. 
         [0025]    In order to provide communication between hopper  10  within the aircraft cabin, and broadcasting head  12  located under the fuselage, two holes are cut in a non-structural portion of the fuselage belly skin under each passenger rear seat to receive the outlets of each of feed chutes  34 A,  34 B ( FIG. 4 ). The shape of the feed chutes and position of the broadcasting head directly under the feed chutes allows for gravity feed of materials to be broadcast from hopper  10  directly into broadcasting head  12 . In one exemplary embodiment, the two holes may be four inches in diameter and strengthened with an aluminum 2024-T3 0.032 ring doubler and fitted with six nut plates and riveted in place in accordance with FAA Reg. 43.13. As illustrated by  FIGS. 6-8 , seeds or other material to be broadcast is delivered to rotating distribution disk  56  of broadcast head  12  from feed chutes  34 A,  34 B via delivery ducts  62 A,  62 B and then through head body  60 . The delivery ducts may have a flat, angled bottom to direct materials to the head body. In one embodiment, the delivery duct bottom angle may be at about 12°. 
         [0026]    As shown in  FIG. 7 , in which delivery duct  62 B is removed to facilitate view of other parts, connector duct  64 B connects the outlet of feed chute  34 B with delivery duct  62 B. Gasket  66 B prevents leakage of materials passing therethrough. Materials delivery into head body  60  is through door  68 B, controlled by remotely controlled slide gate  70 B. It should be noted that the structure shown in  FIG. 7  corresponds to the starboard side of broadcasting head  12  and that the same structure is mirrored on the port side. 
         [0027]    Materials passing through doors  68 A,  68 B are received in head body  60  and delivered to distribution disk  56  through plenum  72  as shown in  FIG. 8 . Doors  68 A,  68 B are driven by actuator servo  74 , which connect to each door through actuator arm  76 . Rotation of servo  74  delivers forward and aft linear motion, guided by linear slide bearings  78 A,B, for each of doors  68 A,  68 B, respectively. A switch for turning linear actuator servo  74  on and off may be conveniently located in the cockpit within the pilot&#39;s easy reach. 
         [0028]    In one exemplary embodiment, the components of broadcasting head  12  may be constructed out of 6061 aluminum and fastened together with grade 5 hardware. Hydraulic motor  58  that drives distribution disc  56  ( FIG. 6 ) may be selected by persons of ordinary skill for compatibility with a hydraulic system including a pump driven off of the aircraft accessory drive pad. In the example of the Robinson R-44 helicopter as shown in the figures, a Parker gear pump, part number MGG20016 BB1B3 (not shown), was used. This is the same motor/pump that drives the distribution pump off of the OEM air conditioning drive. 
         [0029]    Provision of electrical controls for the system disclosed may create as few as two electrical impacts to the aircraft. The first electrical impact is a solenoid-type switch controlling the flow of the hydraulic fluid from pump to pump and pump to tank. The second electrical impact is actuator  74  that opens and closes the gravity-fed doors  68 A,  68 B. In the R-44 exemplary embodiment shown, the solenoid switch may be a 12 volt solenoid-type switch with a 5 amp circuit breaker, and the actuator may be a 12 volt linear actuator with a 10 amp circuit breaker. 
         [0030]    With a system thus designed, it is possible to maintain weight and balance within the standard limits aircraft CG and gross weight parameters, both with the system fully loaded and completely empty. In the exemplary embodiment of the R-44 helicopter shown in the figures, the entire system installed weighs approximately 91.0 pounds. 
         [0031]    The foregoing has been a detailed description of illustrative embodiments of the invention. It is noted that in the present specification and claims appended hereto, conjunctive language such as is used in the phrases “at least one of X, Y and Z” and “one or more of X, Y, and Z,” unless specifically stated or indicated otherwise, shall be taken to mean that each item in the conjunctive list can be present in any number exclusive of every other item in the list or in any number in combination with any or all other item(s) in the conjunctive list, each of which may also be present in any number. Applying this general rule, the conjunctive phrases in the foregoing examples in which the conjunctive list consists of X, Y, and Z shall each encompass: one or more of X; one or more of Y; one or more of Z; one or more of X and one or more of Y; one or more of Y and one or more of Z; one or more of X and one or more of Z; and one or more of X, one or more of Y and one or more of Z. 
         [0032]    Various modifications and additions can be made without departing from the spirit and scope of this invention. Features of each of the various embodiments described above may be combined with features of other described embodiments as appropriate in order to provide a multiplicity of feature combinations in associated new embodiments. Furthermore, while the foregoing describes a number of separate embodiments, what has been described herein is merely illustrative of the application of the principles of the present invention. Additionally, although particular methods herein may be illustrated and/or described as being performed in a specific order, the ordering is highly variable within ordinary skill to achieve aspects of the present disclosure. Accordingly, this description is meant to be taken only by way of example, and not to otherwise limit the scope of this invention. 
         [0033]    Exemplary embodiments have been disclosed above and illustrated in the accompanying drawings. It will be understood by those skilled in the art that various changes, omissions and additions may be made to that which is specifically disclosed herein without departing from the spirit and scope of this disclosure.