Patent Document

BACKGROUND OF THE INVENTION 
     1. Field of the Invention 
     The present invention relates to missile systems. More specifically, the present invention relates to apparatus for launching a missile from an airborne platform. 
     2. Description of the Related Art 
     The Maverick missile is well-known in the art as are launchers for same. As used herein, the following Government designations LAU, AGM and BRU are believed to mean ‘Launcher Aircraft Unit’, ‘Air-to-Ground Missile’ and ‘Bomb Rack Unit’, respectively. The LAU-88 launcher is being used to carry the conventional Maverick missile (AGM A-D). Although the LAU-88 features the capability to carry three missiles, it is heavy, has a high drag coefficient, is not authorized to carry the new and heavy Blast penetrator warhead (AGM-65E, F, G or K), and requires the AGM-65D infrared (IR) missile to be rotated. In addition, the LAU-88 suspends the Maverick missiles is both the horizontal and vertical plane which requires the use of peculiar loading equipment and makes loading difficult. 
     Many of these shortcomings are addressed by the LAU-117 launcher, however, the LAU-117 launcher is capable of carrying only one missile at a time. 
     Accordingly, a need remains in the art for a launcher capable of carrying more than one of all versions of the Maverick missile (including (AGM-65D, F, G, or K)), which minimizes weight, aerodynamic drag, and simplifies loading procedures. 
     SUMMARY OF THE INVENTION 
     The need in the art is addressed by the system and method of the present invention. In accordance with the present teachings, a bomb rack is adapted to carry a missile launcher. 
     In the illustrative embodiment, a BRU-33, 55 or 57 is adapted to carry two LAU-117 missile launchers. However, other missile launcher/missile combinations may be used as well. The missile launchers are secured to the bomb rack with a suspension unit of unique and novel design. This new multiple missile launcher configuration allows for releasable engagement of the missile launchers in the vertical plane. This allows for different missile packages to be deployed in the field. 
     Hence, the need in the art is addressed by the provision of a lightweight multiple missile launch assembly adapted to carry two LAU-117 launchers and all versions of the Maverick missiles (including AGM-65D, E, F, G or K) with improved aerodynamic properties and simplified missile loading procedures. 
    
    
     BRIEF DESCRIPTION OF THE DRAWINGS 
     FIG. 1 is a side view showing the multiple missile launcher of the present invention loaded with LAU-117 missile launchers with missiles. 
     FIG. 2 is a top view showing the multiple missile launcher of the present invention loaded with LAU-117 missile launchers and missiles. 
     FIG. 3 is a front view showing the multiple missile launcher of the present invention loaded with LAU-117 missile launchers and missiles. 
     FIG. 4 is a perspective view of an illustrative embodiment of a multiple missile launcher implemented in accordance with the teachings of the present invention with LAU-117 missile launchers. The arrows illustrate vertical loading of the LAU-117 launcher onto the multiple missile launcher. 
     FIG. 5 is a perspective view of an illustrative embodiment of the multiple missile launcher implemented in accordance with the teachings of the present invention. 
     FIG. 6 is a disassembled perspective view of the illustrative embodiment of the of the multiple missile launcher implemented in accordance with the teachings of the present invention. 
     FIG. 7 is a side view of a suspension unit of the support assembly utilized in the illustrative embodiment of a multiple missile launcher implemented in accordance with the teachings of the present invention. 
    
    
     DESCRIPTION OF THE INVENTION 
     Illustrative embodiments and exemplary applications will now be described with reference to the accompanying drawings to disclose the advantageous teachings of the present invention. 
     While the present invention is described herein with reference to illustrative embodiments for particular applications, it should be understood that the invention is not limited thereto. Those having ordinary skill in the art and access to the teachings provided herein will recognize additional modifications, applications, and embodiments within the scope thereof and additional fields in which the present invention would be of significant utility. 
     FIG. 1 is a side view, FIG. 2 is a top view and FIG. 3 is a front view showing the multiple missile launcher of the present invention loaded with two LAU-117 launchers and missiles. As shown in FIGS. 1-3, in the illustrative embodiment, the multiple missile launcher  10  of the present invention is adapted to carry first and second LAU-117 missile launchers  24  and  26  with missiles  27  and  29 . A novel feature of the invention is the capability to carry more than one of the newer Maverick air-to-ground missiles (i.e., AGM-65D, E, F, G or K) simultaneously. Nonetheless, the launcher  10  of the present invention may carry other missile launcher with missiles and dissimlar missile launcher and missile combinations. The launcher  10  of the present invention is shown more clearly in FIG.  4 . 
     FIG. 4 is an exploded view of an illustrative embodiment of a multiple missile launcher and two LAU-117 launchers implemented in accordance with the teachings of the present invention. In the illustrative embodiment, the multiple missile launcher is constructed by modifying a conventional BRU 33, 55 or 57 bomb rack to carry a LAU-117 missile launcher. However, those of ordinary skill in the art will appreciate that other designs may be employed to carry the other launcher and missile combinations without departing from the scope of the present teachings. 
     FIG. 5 is a perspective view of an illustrative embodiment of the multiple missile launcher implemented in accordance with the teachings of the present invention. FIG. 6 is a disassembled perspective view of the illustrative embodiment of the multiple missile launcher implemented in accordance with the teachings of the present invention. As shown in FIGS. 5 and 6, the multiple missile launcher has a strong back  14 , two lower covers  12 , two lugs  13 ,  15 , and associated hardware. The strong back  14  is made of aluminum or other suitable material. The strong back is the primary structural member which provides a mounting for the release units on either side, provides appropriate spacing for carriage of two missile launchers and missiles, and lugs  13  and  15  for mounting the launcher  10  to the undercarriage of an aircraft. The launcher  10  further includes a forward nose cone  16  and an aft nose cone  18 . An electronics unit  19  is disposed within the aft nose cone  18  and/or the forward nose cone  16 . In a BRU-55 or 57 implementation, a second electronics unit (not shown) may be stored in the forward nose cone  16 . In accordance with the present teachings, the electronics unit  19  is designed to provide an electrical interface between a single electrical interface at the aircraft pylon and two LAU-117 electrical interfaces to allow the host aircraft to carry and launch two missiles from a single aircraft pylon. The aircraft pylon (not shown) is electrically connected to the electronics unit  19  via a connector  17  on the aft nose cone  18 . First and second electrical harnesses  25  and  28  are provided to communicate electrical signals from the electronics unit  19  to each of the missiles  27  and  29  (FIG.  1 ). 
     Affixed to the strong back  14  between the forward and aft nose cones  16  and  18  are first and second suspension units  20  and  22  designed in accordance with the present teachings. Each suspension unit  20 ,  22  is mounted on the lower cover  12  with a number (e.g.  6 ) attachment bolts  35 . In the illustrative embodiment, each suspension unit  20  or  22  is designed to provide carriage and release of a missile launcher (e.g., an LAU-117 launcher)  24  or  26  by the launcher  10 . 
     FIG. 7 is a side view of a suspension unit of the support assembly utilized in the illustrative embodiment of a multiple missile launcher implemented in accordance with the teachings of the present invention The suspension unit interfaces with the lugs  21  and  23  and support fittings of the launchers  24  and  26  (FIG.  1 ). As shown in FIG. 7, the suspension units  20  and  22  include forward and aft swaybrace assemblies  30  and  32 , respectively, two suspension hooks  34  and  36 , and linkages and associated hardware to allow carriage and release of the missile launchers. The mechanical operation of the suspension units encompasses  3  major conditions: Store loaded, manual release and ground safety lock. 
     Store Loaded Condition 
     As the LAU-117 launcher  24  is loaded, the top of LAU-117 lug  21 ,  23  (shown in phantom) pushes up on the suspension hooks  34  and  36 , rotating the suspension hook toward the closed position. As the suspension hooks  34  and  36  rotate, cam followers (not shown) slide in the cam tracks (not shown) until the hook self-closing position (over center position) is reached. As the hook latch cam  38  or  40  is rotated past the over center position, the hook latch spring  42  or  44  provides the torque that rotates the suspension hooks  34  or  36  to the closed position. As the hook latch cam  38  or  40  is being rotated toward the closed position, the hook release rod  46  is being pulled, rotating the hook release lever  48 . Hook release lever rotation moves the hook release sleeves  50  upward, sliding on the hook release guide  52 . With the suspension hooks  34  and  36  closed, the safety selector handle  54  can be rotated to the locked position. After the LAU-117 is loaded, the swaybrace screws  31  and  33  are tightened and secured with a jam nut (not shown) to prevent movement of the LAU-117 during flight. 
     Manual Release 
     Manual release provisions are provided for opening the suspension hooks by maintenance/loading personnel. When the manual release shaft  39  is turned, the hook release lever  48  is pulled by the manual release rotating the hook latch cam  38 . When the hook release lever  48  is turned, it pulls the hook release sleeves  50  down, which are free to slide on the hook release guide  52 . As the hook latch cam  38  is rotated by the hook release rod  46 , cam followers (not shown) slide in the cam tracks (not shown) until the hook self-opening point (over center position) is reached. The hook latch spring  42  is compressed during hook latch cam rotation. Suspension hooks  34 ,  36  opening past the over center position is accomplished by continued turning on the manual release shaft  39 , tension of the compressed hook latch spring  42 , and (if installed) weight of the stores on the suspension hooks  34  and  36 . 
     Ground Safety Lock 
     A ground safety lock is provided to prevent inadvertent release of the stores from the suspension unit. When the safety selector handle  54  is in the locked position, the safety rod prevents downward movement of the hook manual release guide  52 . The safety selector handle  54  provides a visual indication as to whether or not the suspension unit  20  is locked. Returning to FIGS. 1-3, the Maverick missiles,  27  and  29  are typically pre-loaded onto the LAU-117 launchers. The multiple missile launcher,  10 , is fitted to the aircraft (not shown). Then the LAU-117 launchers with preloaded missiles are loaded onto the multiple missile launcher. 
     Thus, a multiple missile launcher is provided that doubles the loadout of AGM-65E, F, G and K Maverick and other missiles. No rotation joint is required and the invention is adapted to launch the entire Maverick missile family. The invention offers reduced weight and simplified loading procedures relative to the conventional solution. The loadout may be mixed and matched as per a variety of mission profiles. 
     The present invention has been described herein with reference to a particular embodiment for a particular application. Those having ordinary skill in the art and access to the present teachings will recognize additional modifications, applications and embodiments within the scope thereof. 
     It is therefore intended by the appended claims to cover any and all such applications, modifications and embodiments within the scope of the present invention. 
     Accordingly,

Technology Category: f