Abstract:
The system comprises an outer container which is fixed, directly and fully, in the hold of the transport aeroplane (AC), and in which there is an inner container that can be moved longitudinally and brought from a first or carrying position in which it is situated fully inside the outer container into a second or off-loading position (P 2 ) in which it is longitudinally offset towards the rear of the aircraft (AC) so that a part of the inner container is then situated outside the transport aeroplane (AC).

Description:
CROSS-REFERENCE TO RELATED APPLICATIONS 
     This is a national phase application under 35 U.S.C. §371 of PCT Application No. PCT/FR2011/000034 filed Jan. 19, 2011, which claims the benefit of French application No. 1050488, filed Jan. 26, 2010, the contents of each of which are expressly incorporated herein by reference. 
     FIELD OF ART 
     The present device, system, and method relate to a load-carrying system for a transport airplane. 
     BACKGROUND 
     In the framework of the present device, system, and method, the term load means any object being able to be carried by an airplane, and possibly to be dropped from such airplane. Can be involved particularly drones, freight, etc. Preferably, a load corresponds to a piece of ammunition which, in the framework of the present device, system, and method, represents a missile or bomb type projectile. Generally, such projectile is a part of a usual weapon system with a military load and is equipped with a propelling system and guiding means able to fly it and to guide it toward a target to be damaged or destroyed. It can in particular be a guided bomb or a cruising missile. 
     Although, non exclusively, the present device, system, and method apply more particularly to a carrying and dropping system in flight, for a military transport airplane, in which missile carrying is performed in the hold of the airplane and dropping is implemented through an opening provided at the rear of the airplane. 
     Generally, a load-carrying system comprises containers, each of which contains one of more loads. 
     Such containers are arranged in the hold of the aircraft, either on a fixed position, or on sliding means enabling to move them in the hold. Most frequently, these containers are adapted for the loads to be transported and possibly for the airplane type. Such a carrying system is thus complex with, in general, numerous different containers and numerous connecting means so as to fasten the containers to the airplane fuselage. The complexity is increased if such system must in addition enable a flight dropping of some loads. 
     This complexity presents numerous disadvantages, particularly a high cost and a large working load to install it and also to restore in the airplane the initial configuration thereof if necessary. 
     SUMMARY 
     The present device, system, and method relate to a load-carrying system for a transport airplane, having as an object to remedy the above-mentioned disadvantages. 
     With this end in view, according to the present device, system, and method, said system of the type comprising at least one so-called internal container which is able to receive at least one load, is remarkable in that it comprises in addition a so-called external container which is able to be fastened, directly and completely, in the hold of the transport airplane, and in that said internal container is arranged within said external container so as to be able to be moved longitudinally and to be brought from one to the other of the following positions:
         a first position, in which it is completely located inside said external container; and   a second position, in which it is longitudinally offset toward the rear of the aircraft with respect to said first position, so that a part of said internal container is then located outside said external container and outside the transport airplane through an opening at the rear of the hold.       

     Advantageously, said internal container is mounted inside said external container with the help of the first sliding means which are able to move said internal container between said first and second positions. 
     So, as thanks to the present device, system, and method, the load-carrying system comprises a single external container which is provided with all the necessary means for the carrying and the off-loading (particularly one or more internal containers and associated sliding means), it is sufficient to install such external container in the airplane to be able to implement the present device, system, and method. Consequently, the system according to the present device, system, and method is simple, it can be realized and installed rapidly, and it does not need a big modification of the transport airplane being used. 
     Moreover, the present device, system, and method can be envisaged on any type of transport airplane and is not limited to a particular load. 
     Furthermore, if connecting means of the external container on the internal fuselage of the transport airplane are contemplated, which are easy to be removed, it is possible to restore in the airplane, quickly and at a reduced cost, its initial configuration so that it can fill other types of missions, such as a troop and/or a vehicle transport. 
     Furthermore, advantageously, the system according to the present device, system, and method comprises in addition a second sliding means which are able to move said load from the load&#39;s resting place in one part of the internal container to the part of said internal container that is located outside the transport airplane in said second position. 
     Moreover, advantageously, said internal container comprises a cage equipped with compartments able to receive a plurality of loads, being identical or different, thereby enabling an operational flexibility. Such compartments can be arranged in rows and/or in columns. In addition, each compartment can longitudinally contain several loads if the respective sizes allow it. 
     Furthermore, advantageously, said system comprises in addition a control device which is able to control at least said (first and second) sliding means and which is arranged in a dedicated area of the transport airplane, which can be pressurized. 
     In a preferred embodiment, the system according to the present device, system, and method is provided for carrying, but also for dropping in flight, at least one load. In such preferred embodiment, the part of the internal container, which is located outside the transport airplane in said second position, and in which a load is able to be brought with the help of said second sliding means, is a so-called dropping part, whence the load can be dropped (in flight) from the transport airplane. 
     So, thanks to this preferred embodiment, the dropping part of the internal container, where a load can be brought, is moved outside the transport airplane, so that this load can then be dropped in flight without using any extraction means, and in particular, with no use of a parachute. The following advantages are then obtained in particular:
         no slowing down of the load after dropping, thereby enabling, in the case of a missile, to stay in the field of pilotability of the missile and of starting of the engine. In such situation, the integration of a missile re-acceleration system is not indispensable;   no equipment is dropped, unlike a dropping with a parachute, thereby enabling to obtain a certain operational discretion; and   as the dropping part of the internal container is located outside the transport airplane, the collision risks with the latter are strongly reduced, and a much more extended dropping field is obtained.       

     In the dropping position, the load is dropped preferably by a simple release. However, in the framework of the present device, system, and method, dropping can also be performed (in such dropping position) by ejection or by ejection and release. 
     Advantageously, said second sliding means comprises rails fastened on the internal container and provided with an ejection device which is able to slide on said rails and which is able to support the load upon carrying and to release it (by release and/or ejection) upon dropping. So, an ejection device can be used, which is similar to a usual ejection device being used upon carrying and dropping of a piece of ammunition on a fighter. This enables to use the carrying points usually existing on the ammunition and thus limits the modifications to be made to the latter. 
     Moreover, advantageously:
         the rails are fastened on the internal sides of the internal container so as not to disturb load dropping from an upper stage when the internal container comprises several superposed stages; and   the system according to the present device, system, and method comprises, for each load, dedicated second sliding means. So, by providing second sliding means adapted for the load type being used, it is possible to carry and drop different types of load with the help of one same internal container, thereby allowing in particular the operational capacities to be increased.       

     The present device, system, and method also relate to a (military) transport airplane comprising a carrying (and possibly dropping) system such as the one above mentioned. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       The figures of the accompanying drawings will facilitate the understanding of how the present device, system, and method can be implemented. On such figures, identical references designate similar elements. 
         FIGS. 1 and 2  schematically show a system according to the present device, system, and method, which is arranged on a transport airplane, respectively in a carrying position and in an off-loading position, particularly for a flight dropping. 
     
    
    
     DETAILED DESCRIPTION 
     The system  1  according to the present device, system, and method and schematically represented on  FIGS. 1 and 2  is adapted to be arranged in the hold  2  of a transport airplane AC, in particular a heavy military transport airplane, and it is used to carry (and possibly to drop in flight) loads representing, as a preferred example, ammunition  3  in the following description. 
     A piece of ammunition  3  correspond to a projectile which is part of a usual weapon system with a military load and which is equipped with usual propelling means and usual guiding means being able to flight it and to guide it toward a target to be damaged or destroyed. It can be in particular a guided bomb or a cruising missile. 
     Said system  1  comprises at least one internal container  4  being located in the hold  2  of the transport airplane AC and which is able to receive at least one piece of ammunition  3 . In the example of  FIGS. 1 and 2 , said internal container  4  comprises eight ammunition  3 , namely two groups of four ammunition  3 , arranged side by side, one only group of which is visible on such  FIGS. 1 and 2 . Each piece of ammunition  3  is arranged inside the internal container  4  so as to be able to slide with the help of the second sliding means  5  to be detailed more precisely hereinunder. 
     According to the present device, system, and method, said load-carrying system comprises in addition an external container  15  which is able to be fastened, directly and completely, in the hold  2  of the transport airplane AC. Moreover, according to the present device, system, and method, said internal container  4  is arranged inside said external container  15 , and this, to be able to be moved longitudinally in the latter with the help of first sliding means  6  comprising, for example, rails fastened on the external container  15 , cooperating with means being integral with the internal container  4 . 
     More precisely, said internal container  4  is able to be brought, with the help of said sliding means  6 , from a first or front position P 1 , which may also be termed a carrying position, represented on  FIG. 1 , to a second or rear position P 2 , which may also be termed an off-loading position represented on  FIG. 2 , in the direction illustrated by an arrow F 1 , and from such second position P 2  again to the first position P 1  in the direction illustrated by an arrow F 2 . Such positions P 1  and P 2  correspond respectively to:
         a carrying position P 1 , in which the internal container  4  is completely located inside the external container  15  and thus inside the hold  2 ; and   an off-loading position P 2 , in which the internal container  4  is longitudinally offset toward the rear of the aircraft AC with respect to the first position P 1 , so that a part  7  of said internal container  4  is then located outside said external container  15  and outside the transport airplane AC through an opening  8  at the rear of the hold  2 .       

     So, as the system  1  according to the present device, system, and method comprises a single external container  15  being equipped with all the means being necessary for the carrying and the off-loading (particularly one or more internal containers  4  and associated first sliding means  6 ), it is sufficient to install such an external container  15  in the airplane AC to be able to implement the present device, system, and method. Consequently, a system  1  is obtained, which is simple, which can be realized and installed quickly and which does not need a big modification of the transport airplane AC being used. 
     Moreover, it can be arranged on any transport airplane type and is not limited to a particular type of ammunition or load. 
     Furthermore, if connecting means  14  (schematically represented) are provided to fasten the external container  15  on the internal fuselage on the transport airplane AC, which means are easy to remove, the airplane AC can be restored, quickly and at reduced cost, in its initial configuration so that it can fill other types of missions, such as troop and/or vehicle transport. 
     Moreover, said second sliding means  5  are formed so as to be able to bring the ammunition  3  which is located in the internal container  4 , from a resting place to said part  7  of the internal container  4 . 
     Furthermore, said system  1  comprises in addition a dropping control device  31 , which is able to control, in particular, said first sliding means  6  and said second sliding means  5 , further to controls generated by an operator, and which is arranged in a dedicated area of the transport airplane AC, which can be pressurized. 
     In a particular embodiment, said internal container  4  comprises a cage  16  equipped with compartments  17  which are able to receive each one or more pieces of ammunition  3 . Such compartments  17  can be arranged in rows and/or in columns. In the example of  FIGS. 1 and 1  the internal container  4  comprises two sets of compartments arranged in row one above the other. 
     In a preferred embodiment, the system  1  according to the present device, system, and method is adapted not only for carrying, but also for flight dropping, at least one piece of ammunition  3 . In such particular embodiment, the part  7  of the internal container  4 , which is located outside the transport airplane AC in the position P 2  and in which one piece of ammunition  3  is able to be brought with the help of said second sliding means  5 , is a so-called dropping part, whence the piece of ammunition  3  can be dropped in flight from the transport plane AC. 
     In such a preferred embodiment, said second sliding means  5  comprise rails  10  fastened on the internal container  4  and providing with an ejection device  11 , which is able to slide on said rails  10  and which is able to support the ammunition  3  upon carrying and to release it upon dropping. 
     Consequently, to perform dropping in flight of ammunition  3  carried by the system  1  according to the present device, system, and method, the following operations are implemented:
         from the carrying position P 1 , i.e. the position which is used upon flight phases (take-off, cruising phase, etc.) other than the dropping phase, for which the internal container  4  is located completely inside the external container  15  and the doors  12  and  13  at the rear of the airplane are closed, an opening of said doors  12  and  13  is usually controlled (pivoting them as illustrated by arrows E 1  and E 2  on  FIG. 1  to bring them in the positions represented in broken lines on this  FIG. 1  and forming the opening  8 ) and, with the help of the dropping control device, the first sliding means  6  are controlled for generating a movement of the whole internal container  4  longitudinally toward the rear of the airplane AC in the direction illustrated by the arrow F 1 ;   when the internal container  4  is in the position P 2 , for which the dropping part  7  is located outside the airplane AC, one piece of ammunition  3  is brought in such dropping part  7 , with the help of the sliding means  5  (and the dropping control device) and, in such a position, the ejection device  11  is controlled so that it releases (by release and/or ejection) the piece of ammunition  3 ;   the former step can be performed for a single piece of ammunition  3  or can be repeated for some or the totality of the ammunition  3  contained in the internal container  4 ; and   when the ammunition  3  which was required to be released have been released, the internal container  4  can be restored in its position P 1  in the direction illustrated by the arrow F 2  and the doors  12  and  13  can be closed again.       

     So, as in such a preferred embodiment, the dropping part  7  of the internal container  4  can be moved outside the transport airplane AC, a piece of ammunition  3  (brought in that dropping part  7 ) can be dropped without having to use any extraction means, such as a parachute for example. 
     Consequently, thanks to such preferred embodiment of the system  1  according to the present device, system, and method, the following advantages are particularly obtained:
         no slowing down of the piece of ammunition  3  after dropping, thereby enabling, in the case of a missile, to stay in the field of pilotability of the missile and starting of the engine thereof. In such a situation, the integration of a missile re-acceleration system is not indispensable;   no equipment is dropped, unlike a dropping with a parachute, thereby allowing a certain operational discretion; and   as upon dropping, the dropping part  7  of the internal container  4  is located outside the transport airplane AC, the collision risks of the ammunition  3  with the latter are strongly reduced, and a much more extended dropping field than the usual solution is obtained.       

     Moreover, the rear end  18  of the internal container  4  including the dropping part  7  is formed such that the lower stage  19  does not disturb the dropping of one piece of ammunition from the upper stage  20 , as represented on  FIG. 2 . To do so, the rails  10  are fastened on the sides of the compartments  17  of the internal container  4 . 
     On the other side, said ejection device  11  stays on the rails  10  after dropping. Consequently, the system  1  comprises a set of rails  10  per piece of ammunition  3 . Moreover, an ejection device  11  can be used, which is similar to a usual ejection device being employed on a fighter. This enables in particular to use the carrying points usually existing on the ammunition and thus limits the modification to be made to the latter.