Abstract:
A downrange wind measurement system includes an aerial vehicle with a global positioning system and a communication device; and a remote computer with a display for viewing access and a transceiver. A method to assist a shooter adjust for a wind speed and a wind angle of a wind prior to make a downrange shot includes creating a flight path for an aerial vehicle to fly alongside a projectile path; determining locations for a circular flight path via the flight path; measuring the wind speed and the wind angle along the circular flight path; transmitting the wind speed and the wind angle to a remote computer; and computing via the remote computer scope adjustments with the wind speed and wind angle.

Description:
BACKGROUND 
     1. Field of the Invention 
     The present invention relates generally to downrange measurement systems and methods of use. 
     2. Description of Related Art 
     Shooting rifles and/or other types of firearms downrange is well known in the art. To increase accuracy of the shot, the firearms are generally equipped with a magnifying scope that allows the shooter to view the target at the far distance and to thereafter align the firearm within the proper position to make the shot. 
       FIG. 1  depicts a simplified schematic of a conventional process  101  to manipulate a rifle  105  to shoot a projectile at a target  107  along a projectile path  109 . During use, the shooter adjusts the scope  103  and/or other magnification viewing means to view the target  107  prior to taking the shot. 
     It is commonly known that the greater the distance between points A to B, the greater the difficulty in accurately hitting the target. It should be understood that various factors exist when taking a shot, for example, changes in wind speeds and angles along the projectile path  109 . In the exemplary embodiment, three different wind speeds  111 ,  113 , and  115  are depicted with arrows indicating variations in wind velocities and angles relative to the projectile path  109 . 
     One of the problems commonly associated with conventional shooting methods includes the changes in wind speeds and angles along the projectile path, which in turn affects the ability of the shooter to accurately hit the target. The problem is magnified as the distance between A and B increases. 
     Although great strides have been made in the area to help assisted shooters in the process of accurately hitting downrange targets, many shortcomings remain. 
    
    
     
       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 shooting process; 
         FIG. 2  is a simplified schematic of a target shooting system and method of use in accordance with a preferred embodiment of the present application; 
         FIG. 3  is a simplified schematic of a communication system of the shooting system of  FIG. 2 ; 
         FIG. 4  is a top view of a flight path of the system of  FIG. 2 ; 
         FIG. 5  is a computer system of the system of  FIG. 2 ; 
         FIG. 6  is a flowchart depicting the preferred method of use; 
         FIG. 7  is a simplified schematic of a target shooting system and method of use in accordance with an alternative embodiment of the present application; 
         FIG. 8  is a vector diagram of the wind speed utilizing the method of  FIG. 7 ; and 
         FIG. 9  is a flowchart depicting the alternative method of use. 
     
    
    
     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 systems and method to manipulate, aim, and shoot a firearm. Specifically, the system and method of the present application provides rapid and effective means to determine and assist the shooter in compensating for wind speed and angle along the projectile path. This feature is achieved via an aerial vehicle that measures wind speed and angle at selected locations along the projectile path and is achieved by relaying the measured wind speed(s) and angle(s) to a remote computer proximate to the shooter for computing adjustments for the scope sight. 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 a simplified schematic of a downrange wind profile measurement system and method of use in accordance with a preferred embodiment of the present application. It will be appreciated that system  201  overcomes one or more of the above-listed problems commonly associated with the conventional methods to shoot a firearm downrange. 
     In the contemplated embodiment, system  201  includes one or more of an aerial vehicle  203  with a communication device  205  configured to transmit wind speed and wind angle data to a remote computer  207 . During use, the aerial vehicle  203  is preferably preprogrammed to fly along a flight path  209  that includes a first section  211  preferably extending along the projectile path  109 , a second section  213  extending a predetermined distance away from the target location  107 , and a third section  215  that returns the aerial vehicle back to either the shooter or a selected location. 
     The flight path section  211  includes elliptical or circular paths  217 ,  219 , and  221  for flight where the wind speeds and angles, as depicted with arrows  111 ,  113 , and  115  are determined at positions C, D, and E along the projectile path  109 . It will be appreciated that one or more additional or less circular paths could be flown along the fight path. Further, it should be understood that the flight paths do not need to be circular in shape, but could include other geometric flight paths. 
     After the aerial vehicle has obtained wind speeds and angles at locations C, D, and E, the aerial vehicle  203  starts a new flight path along section  213  away from the target position. Shortly thereafter, the aerial vehicle  203  returns along flight path  215  and transmits the wind speed and angle data to the remote computer  207  during this section via communication device  205 . The turn away from the ballistic path includes any combination of turn or change in altitude to clear the path so the shot can be taken without interference. 
     One of the unique features believed characteristic of the present invention is the use of an aerial vehicle  203  to measure wind speed and angle along the projectile path  109 . As depicted in  FIG. 2 , it should be understood that the projectile path has an altitude relative to the ground surface and travel along an arc. Accordingly, the aerial vehicle  203  is also configured to travel along the anticipated projectile arc path to measure wind field information to provide a more accurate calculation. The wind speed and angle data allows the shooter to adjust the scope to more accurately compensate for wind along the projectile path. Thus, system  201  provides effective means for accurate shooting downrange. 
     Referring now to  FIG. 3 , a simplified schematic of the communication system between the aerial vehicle  203  and computer  207  is shown. It will be appreciated that aerial vehicle  203  includes a communication device  205  that transmits and receives data to a transceiver  301  of computer  207 . The computer  207  includes the necessary software, hardware, and algorithms to assist the shooter in aligning the scope to make an accurate shot in accordance with the wind speeds and angles taken along the projectile path. In the preferred embodiment, the computer  207  provides the shooter with required adjustment movements of the scope to make an accurate shot. 
     It should be understood that aerial vehicle  203  is also provided with a computer system  303  that determines the position, speed and angle of the aircraft during flight. Discussion of these features are shown in  FIG. 5  and discussed below. 
     In  FIG. 4 , a schematic of the circular flight pattern  217  is shown. The schematic further illustrates the features of the process of measuring wind speed “Vwind” and angle “A 1 ” while flying in the circular pattern  217 . 
     At position  401 , the aerial vehicle moves into the wind at an angle A 2  with a measured Velocity. It should be understood that the aerial vehicle travels at a constant air speed around path  217 —a feature critical to achieving the desired results. The total velocity (ground velocity) of the aerial vehicle at position  401  is the velocity of air “Vair”, as indicated by arrow  409 , less the velocity of the wind “Vwind”, as indicated by arrow  411 . 
     At position  403 , the aerial vehicle moves away from the wind at an angle A 3 , which is equal to 180 degrees minus A 2 . The total velocity at this position is Vair, as indicated by arrow  407  plus Vwind, as indicated by arrow  405 . 
     At positions  401 ,  403  respective maximum ground velocity “Vg_max” and minimum ground velocity “Vg_min” are measured to determine Vwind. At position  403 , the Vg_max=Vair+Vwind; while at position  401 , the Vg_min=Vair−Vwind. Taking wind and ground speed measurements at these locations provides means to determine wind speed with equation Vwind=(Vg_max−Vg_min)/2. The angle of the wind is determined by (A 1 +A 2 )/2. For example, if the angle A 2 =240 degrees, while A 3 =60 degrees, the wind speed angle would equal 150 degrees relative to the projectile path. It should be understood that the roll angle and the air speed of the aerial vehicle must remain constant to utilize the above-referenced equations. 
     In  FIG. 5 , the onboard computer system  303  is shown with one or more of a control unit  501  operably associated with a GPS device  503 , a database  505 , and an optional compass device  505 . During use, the system  303  is configured to determined wind speed and angle via the compass and/or GPS device as discussed above. The measured wind speed and angle data are stored in the database and thereafter transmitted to the transceiver  301  via the communication device  205 . 
     In the preferred embodiment, communication device  205  is a laser configured to transmit the data to the transceiver. This feature allows the aircraft to communicate the data without the fear interception from one or more third parties. However, it will be appreciated that alternative embodiments could utilize other forms of wireless communication means in lieu of the preferred laser embodiment. 
     In  FIG. 6 , a flowchart  601  depicting the preferred process is shown. The process includes programming the aerial vehicle with a flight path along a projectile path of an initial, no wind ballistic computation, as depicted in box  603 . A predetermined set of flight elliptical paths are preferably preprogramed along the flight path along determined distances relative to each other. It will be appreciated that that aerial vehicle can also be adapted to determine the number of circular paths along the flight path in real-time in accordance with an alternative embodiment. It will also be appreciated that the aerial vehicle can be controlled by the shooter and/or third party in lieu of being preprogrammed, as discussed above. 
     The next step includes activating and flying the aircraft along the flight path. During flight, the aerial vehicle is configured to measure wind velocities and angles at selected locations, as depicted in boxes  605 ,  607 . The aerial vehicle has an onboard flight control computer configured to determine wind speed by sensing ground speed and at selected locations along a circular flight path. Thereafter, the data from the onboard flight control computer is relayed to a remote computer via a communication device, as depicted in box  609 . 
     Referring now to an alternative embodiment of the present invention.  FIGS. 7-9  depict various views and a flowchart of an alternative system  701  configured to achieve the same results as system  201 ; however, in the contemplated embodiment, the aerial vehicle  203  is configured to crab at positions C, D, and E to determine the wind speed and angle. 
       FIG. 8  illustrates a vector diagram  801  of the aircraft and wind velocities. Arrow  111  indicates the wind speed vector; arrow  803  indicates the known velocity of the aerial vehicle; arrow  805  indicates the measured velocity of the aerial vehicle; arrow  807  indicates the component of the wind at a right angle to arrow  803 ; arrow  809  indicates a component of the wind at a parallel angle to arrow  805 . Accordingly, knowing the angle of travel A 5  from the GPS and/or compass, the wind speed and angle are calculated with simple geometry equations. 
     It should be understood that the known velocity, as indicated by arrow  803 , is predetermined by measuring the velocity of the aircraft in a wind tunnel and/or other suitable means to determine the speed of the aircraft relative to a ground position during a flight condition. 
     In  FIG. 9 , a flowchart  901  depicts the process of the alternative process, which includes the steps similar to flowchart  601 , as indicated by boxes  903 - 909 . However, in the alternative embodiment, the wind speed and angle are determined by flying the aerial vehicle at a crab angle relative to the wind direction. 
     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.