Patent Abstract:
An aircraft fuselage training device for training fire fighters to use fuselage penetration fire extinguishing devices includes a mounting frame and an aircraft fuselage simulation frame mounted on the mounting frame. At least one fuselage skin section sheet is releasably mounted on the aircraft fuselage simulation frame and the fuselage skin section sheet and the aircraft fuselage simulation frame are cooperatively operative to generally simulate an aircraft fuselage whereby fuselage penetration fire extinguishing devices are usable to penetrate the fuselage skin section sheet for firefighter training purposes.

Full Description:
CROSS-REFERENCE TO RELATED PROVISIONAL PATENT 
   This application claims priority based on a provisional patent, specifically on the Provisional Patent Application Ser. No. 60/602,286 filed Aug. 17, 2004. 

   BACKGROUND OF THE INVENTION 
   1. Technical Field 
   The present invention relates to training devices for fire fighters and, more particularly, to an aircraft fuselage simulation training device for fire fighters which includes at least one generally upright ground-mounted beam and a semi-cylindrical aircraft fuselage simulation frame mounted on and extending outwards from the ground-mounted beam, the aircraft fuselage simulation frame having a plurality of aluminum sheets mounted transversely thereon in general parallel alignment with the center longitudinal axis of the semi-cylindrical frame such that an aircraft fuselage is simulated for the fire fighters to use during training, particularly during training for use of aircraft skin penetration devices used in fire fighting. 
   2. Description of the Prior Art 
   Today&#39;s firefighters are equipped with many different types of specialized fire fighting devices for use in virtually any fire fighting situation. However, certain fire fighting situations require even more specialized equipment than others, and chief among these would be the situations encountered by those fire fighters who work at airports and must fight fires on, in, and around aircraft. Because of the confined space and limited access encountered in attempting to fight fires which are on aircraft, various specialized devices have been developed to permit the fire fighters to fight the fire without having to enter the aircraft. Among these are fuselage penetration devices such as the Snozzle® manufactured by Craft Rescue Equipment Service, Inc. of Dallas, Tex. Briefly, the Snozzle® is a water-delivery system which includes an aircraft skin penetration section having a metal piercing tip which is mounted on a truck-mounted boom which is connected to a water delivery system such as a pumping device. In operation, the Snozzle® would be extended through the outer wall of an aircraft until the forward end of the Snozzle® is within the aircraft. The water delivery system is then engaged and upwards of 300 gallons per minute are transferred through the Snozzle® into the interior of the aircraft without requiring the fire fighter to enter the dangerous interior of the aircraft. The Snozzle® system thus is designed to quickly and safely extinguish fires within the fuselage of the aircraft without requiring entry of the fuselage by a fire fighter. 
   One of the disadvantages, however, of the Snozzle® device is that it requires a good deal of practice to become proficient with the use of the Snozzle®. Clearly, it is impossible for a fire fighting unit in an airport to go around to various aircraft and stick the Snozzle® into the aircraft&#39;s skin to practice their technique, and there are very few other easily obtainable structures which provide an accurate simulation of the aircraft fuselage on which to practice. There is therefore a need for a training device for airport fire fighters which will permit them to practice the technique of penetrating the aircraft&#39;s skin with the Snozzle® in an accurate yet cost-effective manner. At the present time, no such training device exists. 
   Therefore, an object of the present invention is to provide an improved aircraft fuselage training device for firefighters. 
   Another object of the present invention is to provide an aircraft fuselage training device for firefighters which will permit firefighters to practice use of the aircraft skin penetration firefighting devices currently used by firefighters for putting out fires in airplanes. 
   Another object of the present invention is to provide an aircraft fuselage training device for firefighters which includes a generally upright ground-engaging frame on which is mounted a semi-cylindrical aircraft fuselage simulation frame on which a plurality of aluminum sheets are mounted thereon to simulate the outer skin and body of an aircraft fuselage. 
   Another object of the present invention is to provide an aircraft fuselage training device for firefighters which includes quick-release mounting devices for releasably securing the aluminum sheets on the aircraft fuselage simulation frame to permit the rapid removal and replacement of aluminum sheets to generally reduce interruptions in firefighting training. 
   Another object of the present invention is to provide an aircraft fuselage training device for firefighters which includes a full cylinder aircraft fuselage simulation frame having a plurality of aluminum sheets mounted on the outer circumference of the fuselage simulation frame to provide an accurate and useful training device for firefighters. 
   Finally, an object of the present invention is to provide an aircraft fuselage training device for firefighters which is relatively simple and durable in construction and is safe, efficient and effective in use. 
   SUMMARY OF THE INVENTION 
   The present invention provides an aircraft fuselage training device for training fire fighters to use fuselage penetration fire extinguishing devices which includes a mounting frame and an at least partially cylindrical aircraft fuselage simulation frame mounted on the mounting frame. At least one fuselage skin section sheet is releasably mounted on the aircraft fuselage simulation frame and the at least one fuselage skin section sheet and the aircraft fuselage simulation frame are cooperatively operative to generally simulate an aircraft fuselage whereby fuselage penetration fire extinguishing devices are usable to penetrate the at least one fuselage skin section sheet for training purposes. 
   The present invention further includes a method of training fire fighters in the use of fuselage penetration fire extinguishing devices which includes the steps of providing a mounting frame, an at least partially cylindrical aircraft fuselage simulation frame mounted on the mounting frame and at least two fuselage skin section sheets releasably mounted on the aircraft fuselage simulation frame. A fuselage penetration fire extinguishing device is also provided which includes a metal piercing tip operative to extend into and through the at least two fuselage skin section sheets releasably mounted on the aircraft fuselage simulation frame. The fuselage penetration fire extinguishing device is then engaged to move the metal piercing tip into and through a selected one of the at least two fuselage skin section sheets and the engaging step is then repeated in one of a different location on the selected one of the at least two fuselage skin section sheets and a second one of the at least two fuselage skin section sheets thereby practicing use of the fuselage penetration fire extinguishing device to gain competence in the use thereof. 
   The aircraft fuselage training device for firefighters as described above provides numerous advantages for firefighter training which are not found in many of the training devices and methods found in the prior art. For example, because the aluminum sheets mounted on the semi-cylindrical aircraft fuselage simulation frame generally replicate the position and penetration resistance of a real aircraft fuselage, firefighters training with penetration firefighting devices can accurately simulate the specific procedures required to properly fight fires within aircraft, without having to actually use the penetration firefighting devices on an actual aircraft. Furthermore, because the aluminum sheets are relatively inexpensive and may be quickly and easily replaced on the aircraft fuselage simulation frame, an increased amount of training is permitted without having to use different locations on the fuselage which have not yet been penetrated. The correct procedure for extinguishing fires within an aircraft may thus be practiced, without having to make concessions to the previously available inadequate simulation devices. Finally, because the positioning of the aircraft fuselage simulation frame on the ground-engaging upright frame may be adjusted, the heights and angles required for penetration of various types of aircraft may be practiced while using the same aircraft fuselage simulation training device of the present invention, instead of having to have available examples of each and every aircraft which might be encountered at an air field. The aircraft fuselage training device for firefighters of the present invention thus provides a substantial improvement over those devices and methods found in the prior art. 

   
     BRIEF DESCRIPTION OF THE DRAWINGS 
       FIG. 1  is a perspective view of the aircraft fuselage training device for fire fighters of the present invention; 
       FIG. 2  is a perspective view of the aircraft fuselage training device for fire fighters showing the device in use during training; 
       FIG. 3  is a perspective view of the present invention showing one of the aluminum panels being replaced after use; and 
       FIG. 4  is a perspective view of an alternative embodiment of the aircraft fuselage training device for fire fighters of the present invention. 
   

   DESCRIPTION OF THE PREFERRED EMBODIMENT 
   The aircraft fuselage training device  10  for fire fighters of the present invention is shown best in  FIGS. 1-3  as including a generally upright mounting frame section  12  and an aircraft fuselage simulation frame section  40  which is mounted on the generally upright mounting frame section  12 . In the preferred embodiment, generally upright mounting frame section  12  would include a pair of upright main frame beams  14   a  and  14   b  which extend upwards generally parallel to one another and are spaced approximately 4 to 6 feet apart. Main frame beams  14   a  and  14   b  would be securely mounted on a foundation  30  which, in the preferred embodiment, would likely be a pair of concrete footings or another such extremely sturdy and solid mounting foundation for the main frame beams  14   a  and  14   b . While it is expected that foundation  30  will provide sufficient vertical force stability for the main frame beams  14   a  and  14   b , it may be preferable to provide additional horizontal force support for each of the main frame beams  14   a  and  14   b , and therefore a pair of generally diagonal main frame support struts  16   a  and  16   b  would be mounted to the main frame beams  14   a  and  14   b , as shown best in  FIGS. 1 and 2 , with the main frame support struts  16   a  and  16   b  extending downwards to be secured to the foundation  30  to generally prevent horizontal movement of the main frame beams  14   a  and  14   b  in response to horizontal forces being applied thereto. In the preferred embodiment, the main frame beams  14   a  and  14   b  and main frame support struts  16   a  and  16   b  would be constructed of heavy-duty steel I-beams, and the main frame beams  14   a  and  14   b  would have heights of approximately 10 to 16 feet. Additional features which may be found on the generally upright mounting frame section  12  may include one or more spacing struts  18  which extend between and connect main frame beams  14   a  and  14   b  for additional structural stability of the mounting frame section  12 , although the inclusion of such spacing struts is not critical to the present invention. Also, it may be preferable to mount the main frame beams  14   a  and  14   b  and main frame support struts  16   a  and  16   b  to a respective one of a pair of base beams  20   a  and  20   b  instead of being mounted to the foundation  30  directly, and such modifications would be understood by one skilled in the art of metal fabrication and foundation construction. 
   The aircraft fuselage simulation frame section  40  is shown best in  FIGS. 1-3  as including three generally semi-cylindrical fuselage frame bars  42   a ,  42   b , and  42   c , each of which extend from generally adjacent the topmost portion of main frame beams  14   a  and  14   b  outwards, downwards, and inwards to connect to the main frame beams  14   a  and  14   b , and cross braces  18  at a point approximately 6 to 12 feet below the topmost portion of main frame beams  14   a  and  14   b . Extending generally perpendicular to and connecting each of the fuselage frame bars  42   a - c  are a plurality of fuselage frame cross beams  44   a ,  44   b , and  44   c  which provide additional structural stability to the fuselage frame bars  42   a - c , as shown best in  FIGS. 1-3 . Also, to provide additional structural stability for the aircraft fuselage simulation frame section  40 , each of the outer fuselage frame bars  42   a  and  42   c  would be further connected to the adjacent main frame beam  14   a  and  14   b  by upper and lower diagonal support struts  46   a ,  46   b ,  48   a , and  48   b  and middle frame bar support strut  50   a  and  50   b , which extend generally horizontally between the outermost section of the fuselage frame bar  42   a  and  42   c  and the adjacent main frame beam  14   a  and  14   b . Of course, it is preferred that each of the frame elements of the mounting frame section  12  and aircraft fuselage simulation frame section  40  be connected to one another via welding or the like in order to ensure that the resulting frame is extremely sturdy and able to withstand the forces that will be applied to it. Also, it is expected that the length of the circumference of fuselage frame bars  42   a - c  would be approximately 10 to 20 feet, depending on the desired size for the trainer and the intended use thereof. 
   The remaining major section of the aircraft fuselage training device  10  for fire fighters of the present invention is shown best in  FIGS. 1-3  and includes the aircraft fuselage simulation skin  60  and mounting devices  62  therefor which permit the skin  60  to be mounted on the aircraft fuselage simulation frame section  40  and specifically on fuselage frame bars  42   a - c . In the preferred embodiment, the fuselage skin  60  would consist of four (4) generally rectangular skin sections  64   a ,  64   b ,  64   c  and  64   d , which would be mounted on the outer circumference of the fuselage frame bars  42   a - c  with small gaps between each of the skin sections  64   a - d , as shown best in  FIGS. 2 and 3 , which may generally align with the fuselage frame cross beams  44   a ,  44   b , and  44   c  so that the user of the present invention can see the location of each of the fuselage frame cross beams  44   a ,  44   b , and  44   c  to prevent unintentional damage thereto. It is preferred that each of the fuselage skin sections  64   a - d  be constructed of aluminum which is similar in thickness to the thickness of the actual aluminum skin used in connection with aircraft fuselages in order to provide a very accurate and reliable simulation of the actual act of penetration of an aircraft fuselage. In the preferred embodiment, each of the fuselage skin sections  64   a - d  would have a width of approximately the same width as the fuselage simulation frame section  40  and a height of approximately 2 to 5 feet, which will generally be determined by the size of the aircraft fuselage training device  10  and the circumference of the fuselage frame bars  42   a - c . In any event, it is preferred that the fuselage skin  60  be comprised of at least three separate fuselage skin sections  64   a - d  so that the use of any one of the fuselage skin sections  64   a - d  during training will not require the entire fuselage skin  60  to be replaced to permit continued practice of the penetration process. 
   Regarding the mounting devices  62 , it is expected that any number of different mounting devices, such as bolts and nuts or quick mount fasteners, may be used with the fuselage skin  60  of the present invention so long as the mounting devices  62  are relatively simple to use and safely secure the fuselage skin  60  to the fuselage frame bars  42   a - c . It is expected, however, that some type of quick-mount mounting device will be used with the aircraft fuselage training device  10  of the present invention in order to permit a user of the present invention to quickly and easily swap fuselage skin sections  64   a - d  to permit continued training on the device. 
   To ensure that a user of the present invention does not penetrate the fuselage skin sections  64   a - d  over the center fuselage frame bar  42   b , it is preferable to use some sort of marking indicia such as a center marking tape  66  which would be affixed to the fuselage skin section  64   a - d  and would extend in generally parallel alignment with the fuselage frame bar  42   b  when the fuselage skin section  64   a - d  is mounted on the aircraft fuselage simulation frame section  40 . Of course, other marking devices may be used to highlight the center fuselage frame bar  42   b , any of which would be usable in connection with the present invention so long as the functional features of the aircraft fuselage simulation device  10  are neither degraded nor destroyed. 
   The aircraft fuselage training device  10  of the present invention is shown in use in  FIG. 2 . Specifically, a user of the device would approach the device with the Snozzle®  80  and by moving the boom  82  forward on which the Snozzle®  80  is mounted, would penetrate one of the fuselage skin sections  64   b  with the Snozzle®  80  and would then engage the water delivery system for the Snozzle®  80  to spray water within the aircraft fuselage simulation frame section  40 . Because of the thickness of the fuselage skin sections  64   a - d , the amount of force required to penetrate the fuselage skin section  64   b  with the Snozzle®  80  is very similar to the amount of force needed for the Snozzle®  80  to penetrate an actual aircraft fuselage, and therefore the fire fighting crews will increase their confidence and become more and more proficient with repeated piercing training as exhibited in  FIG. 2 . 
   Another advantage of the present invention is that the size of the fuselage skin sections  64   a - d  permit the users of the aircraft fuselage training device  10  to perform many penetrations of the fuselage skin section  64   a - d  before the fuselage skin section  64   a - d  must be replaced. However, a further advantage of the present invention is that when one of the fuselage skin sections  64   b  needs to be replaced due to its having been penetrated numerous times, the user merely accesses the mounting device  62  and removes the used fuselage skin section  64   b  and replaces it with either a new fuselage skin section or he or she may move one of the other fuselage skin sections  64   d  upwards to replace the removed fuselage skin section  64   b . Also, because the fuselage skin sections  64   a - d  are relatively inexpensive, the fire fighters that are training with the aircraft fuselage training device  10  of the present invention may conduct numerous training sessions for a relatively low price, thus substantially increasing their proficiency and rendering it more likely they will be able to perform the penetration process on an actual aircraft if and when the time comes where such penetration is necessary. 
   An alternative embodiment of the present invention is shown in  FIG. 4  as including a generally upright mounting frame section  12 ′ and an aircraft fuselage simulation frame section  40 ′, similar to those shown in connection with the preferred embodiment of  FIGS. 1-3 . However, in the embodiment of  FIG. 4 , the aircraft fuselage simulation frame section  40 ′ would include a full cylinder design which includes a full cylinder fuselage section  90  on which the fuselage skin sections  92   a ,  92   b ,  92   c ,  92   d ,  92   e ,  92   f ,  92   g , and  92   h  are mounted. It has been found that for some training exercises, the use of the full cylinder fuselage section  90  is preferable to the aircraft fuselage simulation frame section  40  in that 360 degree access to the full cylinder fuselage section  90  on the aircraft fuselage training device  10 ′ is prevented. This feature enables the user of the present invention to train for additional eventualities such as simultaneous penetration of the aircraft fuselage by multiple Snozzle® devices, as may be necessary in the event of extreme fire situations. It should be noted, however, that the mounting of fuselage skin sections  92   a - h  to the full cylinder fuselage section  90  would likely be accomplished using mounting devices  62 ′ similar to those described previously and therefore the functionality of the second embodiment of the aircraft fuselage training device  10 ′ would be similar to that described in connection with the preferred embodiment of aircraft fuselage training device  10  shown in  FIGS. 1-3 . 
   Also, as shown on  FIG. 4 , it is preferred that the aircraft fuselage simulation frame section  40 ′ be movably mounted on the generally upright mounting frame section  12 ′ such that vertical movement of the aircraft fuselage simulation frame section  40 ′ relative to the generally upright mounting frame section  12 ′ is permitted. The up and down arrows shown in  FIG. 4  illustrate the preferred movement of the aircraft fuselage simulation frame section  40 ′ relative to the generally upright mounting frame section  12 ′ and it should be noted that the aircraft fuselage training device  10  shown in  FIGS. 1-3  may also include such vertical adjustment capability. The specific nature of the vertical adjustment capability is not critical to the present invention so long as the functional capabilities are neither degraded nor destroyed. It has also been found that the providing of such vertical adjustment capability broadens the usefulness of the present invention and permits the aircraft fuselage training device  10  to be used to replicate a broader range of aircraft and fuselage types. 
   The advantages of the aircraft fuselage training device  10  of the present invention are therefore clear, and include the fact that aircraft and airport fire fighting crews now have the opportunity to hone their skills when using penetration tools without damaging the penetration devices or aircraft during training. Also, because the curvature of the aircraft fuselage simulation frame section  40  and therefore the fuselage skin  60  is similar to that of an actual aircraft fuselage, the crew undergoing training will feel confident that their training is an accurate representation of the actual penetration process. Finally, because the fuselage skin sections  64   a - d  may be quickly and easily replaced, the fire fighter&#39;s training may proceed without significant interruption. When using any of those devices found in the prior art, significant interruptions are par for the course. 
   It is to be noted that numerous additions, modifications, and substitutions may be made to the aircraft fuselage training device  10  of the present invention which fall within the intended broad scope of the above description. For example, the specific size, shape and construction materials used in connection with the generally upright mounting frame section  12  and aircraft fuselage simulation frame section  40  are not critical so long as the intended functionality of the present invention is neither degraded nor destroyed. Also, although the fuselage skin  60  of the present invention has been described as including several rectangular panels, it should be noted that the specific size and shape of the fuselage skin sections  64   a - d  may be modified so long as the fuselage skin  60  provides an accurate and easily used representation of an aircraft fuselage. Finally, although the mounting devices  62  have been described with some degree of particularity, it should be noted that numerous other types of mounting devices may be used to connect the fuselage skin sections  64   a - d  to the fuselage frame bars  42   a - c , any of which would be understood by one skilled in the art of affixing metal panels to an underlying frame. 
   There has therefore been shown and described an aircraft fuselage training device  10  for fire fighters which accomplishes at least all of its intended objectives.

Technology Classification (CPC): 0