MUNITION LAUNCHER FOR AIRCRAFT AND AMMUNITION TRAY FOR A MUNITION LAUNCHER

Abstract

This Invention refers to a munition launcher for aircraft that comprises a chassis, which may be attached to an aircraft and with embedded smart electronics, a coupling mechanism attached to the chassis, and at least one ammunition tray coupled in a removable manner to the coupling mechanism. The ammunition tray comprises a plurality of munition openings configured to receive munitions, and at least one latch pin that attaches the tray to a munition launcher chassis. According to this invention, the ammunition tray may be detached from the chassis by releasing at least one latch pin.

Claims

1. An ammunition tray for a munition launcher, comprising: a plurality of munition openings configured to receive munitions, and at least one latch pin that attaches the ammunition tray to a chassis of the munition launcher, whereby the ammunition tray may be detached from the chassis by releasing the at least one latch pin.

2. The ammunition tray according to claim 1, wherein the ammunition tray comprises a plurality of latch pins.

3. The ammunition tray according to claim 2, wherein the latch pins have a configuration with a top that has a width that is greater than a width of a body of the latch pins.

4. The ammunition tray according to claim 1, further comprising handles.

5. The ammunition tray according to claim 1, further comprising a bolt receiver.

6. A munition launcher for aircraft, comprises: a chassis that can be attached to an aircraft and incorporating electronic intelligence, comprising: a coupling mechanism attached to the chassis, and at least one ammunition tray coupled in a removable manner to the coupling mechanism.

7. The munition launcher according to claim 6, wherein the at least one ammunition tray is provided with latch pins and a bolt receiver.

8. The munition launcher according to claim 7, wherein the coupling mechanism consists of two fitting structures comprising openings whose shape is compatible with the latch pins of the ammunition tray and a bolt groove.

9. The munition launcher according to claim 8, wherein the fitting structures are attached to the chassis in a movable manner by springs and bearings.

10. The munition launcher according to claim 9, wherein, in an unbolted position, the ammunition tray may be connected to the fitting structures through inserting the latch pins on the ammunition tray into the openings of the fitting structures.

11. The munition launcher according to claim 10, further comprising a bolt configured to run through the bolt groove and hold the fitting structure in a bolted position.

12. The munition launcher according to claim 11, wherein the actuation of the bolt returns the fitting structure to the unbolted position.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0011] The present invention is described below in greater detail through an example of its embodiment, as shown in the drawings. The Figures illustrate:

[0012] FIG. 1Top front view of a preferred embodiment of the munition launcher system of the present invention in the armed state.

[0013] FIG. 2Top perspective view of an embodiment of the ammunition tray.

[0014] FIG. 3Top perspective view of the bolt illustrated in the ammunition tray shown in FIG. 2.

[0015] FIG. 4Top perspective view of an embodiment of a fitting structure.

[0016] FIG. 5Top perspective view of a preferred embodiment wherein the fitting structures shown in FIG. 4 are mounted on the chassis, and the tray shown in FIG. 2 is aligned with the chassis.

[0017] FIG. 6Close-up view of the unbolted position of the tray with the fitting structures.

[0018] FIG. 7Close-up view of the bolted position of the tray with the fitting structures.

[0019] FIG. 8Close-up view of the bolt arranged on the fitting structure.

[0020] FIG. 9Flowchart of the main launcher firing and operating control states.

DETAILED DESCRIPTION OF THE INVENTION

[0021] The munition launcher for aircraft of the present invention comprises at least one chassis that may be attached to an aircraft and with embedded smart electronics, at least one coupling mechanism attached to the chassis and configured for coupling an ammunition tray, at least one removable ammunition tray, and a bolt that holds the tray in the bolted position on the coupling mechanism. The launcher is preferably made from high-resistance polymer material.

[0022] FIG. 1 Illustrates an example of a preferred embodiment of the invention in the armed state. On munition launcher 10 of the present invention, the chassis 11 has attachment mechanisms for attaching the launcher to an aircraft and embedding all the smart electronics needed to control its operations and launcher shots. A coupling mechanism is attached to the chassis 11 for coupling a removable ammunition tray 20.

[0023] According to a preferred embodiment of the invention, the coupling mechanism is comprised of two fitting structures 30 that comprise slots for holding the ammunition tray 20. The tray is bolted into the fitting structure 30 by a bolt 41.

[0024] In a preferred embodiment of the invention, two ammunition trays can be coupled to the munition launcher 10 as shown in FIG. 1.

[0025] The munition launcher 10 of the present invention optionally comprises power and data feed connectors 12, provided to form the interface between the munition launcher 10 and the aircraft. Through these connectors, the launch platform can be powered by electricity and exchange information with the aircraft.

[0026] FIG. 2 illustrates a preferred embodiment of a configuration for the tray 20. The tray 20 of the present invention comprises a plurality of munition openings 24 wherein the munitions are placed. The tray 20 is also provided with at least one latch pin 22 that allows the tray 20 to be coupled to the chassis 11 of the munition launcher 10. The tray 20 also comprises a bolt receiver 21, configured to receive a bolt 41. Preferably, the at least one latch pin 22 on the tray 20 consists of a plurality of latch pins 22 arrayed along the length of the tray in order to support it during aircraft operations.

[0027] Optionally, the ammunition tray 20 is provided with handles 23 that allow easier handling of the tray 20 during the coupling, uncoupling, and handling operations of the tray 20.

[0028] The embodiment illustrated in FIG. 2 shows twelve munition openings 24. However, different configurations, dimensions and quantities of munition openings 24 and latch pins 22 may be used to hold different types of munitions, without departing from the scope of the invention. For example, the number of latch pins 22 may depend on factors such as the weight and size of the tray 20.

[0029] FIG. 3 presents an expanded view of an embodiment of a latch pin 22 as shown in FIG. 2. In this exemplificatory embodiment, the latch pin 22 has a larger top measurement A than its body measurement B.

[0030] FIG. 4 shows a preferred configuration of the fitting structure 30 that is compatible with the embodiment illustrated in FIGS. 2 and 3. The fitting structure 30 comprises fitting openings 32 that are compatible with the latch pins 22, whereby the configuration of the fitting opening 32 is wider at one end, compatible with the top of the latch pin 22 on the tray 20 and is narrower at the other end, compatible with the body of the latch pin 22.

[0031] The fitting structure 30 preferably comprises a handle 33 compatible with the handle 23 on the tray 20. Furthermore, the fitting structure 30 also comprises a bolt groove 31 configured to allow the movement of the bolt 41 from the bolted position wherein the tray 20 remains coupled on the chassis 11, to the unbolted position wherein the tray 20 is uncoupled from the chassis 11.

[0032] FIG. 5 illustrates the fitting structure 30 mounted on the chassis 11 in a preferred embodiment of the invention. In this embodiment, two fitting structures 30 are used to couple a tray 20. The fitting structure 30 is held on the chassis 11 of the launcher 10 by a set of bearings 12 that allow the sideways movement of the fitting structure 30 in a linear manner.

[0033] Furthermore, springs 34 are used between the fitting structure 30 and the chassis 11, in order to keep the launcher 10 unbolted, meaning, with the fitting structure 30 in the position that allows the insertion or removal of the latch pins 22 on the tray 20. In other words, when the spring 34 is in a resting state, the tray 20 may be coupled or uncoupled.

[0034] Furthermore, the munition launcher 10 optionally comprises firing pins 15, which are electro-mechanical contacts that send an electrical signal to the munitions. These contacts are located on the lower part of the chassis.

[0035] FIG. 6 shows the moment that the tray 20 is fitted into the fitting structure 30 in the unbolted position. With the fitting structure 30 in the unbolted position, the tray 20 may be easily inserted into and removed from the launcher 10. When the tray 20 is coupled to the launcher 10, the latch pins 22 run through the openings in the chassis 11 and the fitting openings 32 arranged in the fitting structure 30, as the measurements of the openings in these two parts are compatible with the measurements of the top of the latch pin 22 on the tray 20, in the unbolted position.

[0036] FIG. 6 shows that, in this unbolted state, the central opening in the bolt groove 31 is out of alignment with the bolt receiver on the chassis. Consequently, the bolt 41 is not bolted onto the tray 20 on the chassis 11.

[0037] FIG. 7 shows the bolted state of the tray 20 on the chassis 11. In order to attain the bolted state, the fitting structure 30 must be slid sideways, extending the springs 34 and resulting in the fitting openings 32 also sliding along to a point wherein their diameter is less than that of the top of the latch pin 22. Sliding the fitting structure 30 sideways may take place by pulling laterally on the handles 34 of the fitting structure 30, whereby the dimensions of the fitting openings 32 in contact with the latch pins 22 become smaller, creating an obstacle. In other words, dimensions that were formerly compatible with the top of the latch pin 22, now prevent it passing through the fitting structure 30, thus avoiding the tray 20 uncoupling vertically from the launcher 10.

[0038] In order to keep the fitting structure 30 in the bolted position, the bolt 41 automatically locks the tray 20 when the fitting structure 30 reaches the sideways movement needed to align the central opening of the bolt groove 31 with the bolt receiver of the chassis. In the bolted state, the bolt 41 prevents the springs 34 from pulling the fitting structure 30 into the resting position.

[0039] Releasing the bolt 41 results in the springs 34 returning immediately to the resting position, pulling the fitting structure 30 into alignment with the fitting openings 32 at the section compatible with the top of the latch pin 22, thus releasing the tray 20.

[0040] The bolt 41 is shown as a retaining device in FIG. 8, according to a preferred embodiment of the invention. However, a key or any other mechanism securing the fitting structure in the desired lateral position may also be used.

[0041] As explained above in a preferred embodiment, a munition launcher 10 may comprise two ammunition trays 20, each supported by two fitting structure 30 and held in place by two bolts 41, thus ensuring safety and redundancy for the launcher 10.

[0042] According to a preferred embodiment of the invention, the tray 20 is the only part of the launcher 10 that must be handled during the loading operation, needing only to position the munitions. Particularly for removing the ammunition tray 20 from the launcher 10 the user must: a) grip both handles 23 of the ammunition trays 20; b) actuate the bolts 41 with their thumbs, for example; and c) remove the tray 20 from the launcher 10. To insert the ammunition tray 20, the user must: a) grip the handles 23 on the tray 20 and align the tray 20 with the launcher 10; b) lift the tray 20 until the handles 23 onto the tray 20 come into contact with the handles 33 of the fitting structure 30; and c) pull both bolts 41 until they click into place.

[0043] This simplified process allows the user to have only spare trays 20 in order to complete the process of positioning new munitions on the tray 20 with the aircraft still in flight. Thus, when the aircraft comes in for loading, the trays 20 with spent munitions will be removed for reloading with new munitions, and the spare trays 20 will be positioned immediately on the launcher.

[0044] Optionally, the munition launcher 10 according to this invention may additionally comprise a magnetic sensor (not illustrated) and magnets positioned close to the fitting structure 30, that identify their position (bolted or unbolted). In this embodiment, each fitting structure 30 has a magnet that activates the sensor when it is moved sideways. As an alternative to the magnetic sensor, any other type of sensor or mechanism that can identify the movement of a part may also be used. Non-exhaustive examples of alternatives to the magnetic sensor are an optical sensor, an end switch, and a capacitive sensor.

[0045] In the embodiment fitted with sensors, the smart electronics can identify whenever the bolts 41 are not secured correctly, notifying the user in real time of the bolt status.

[0046] FIG. 9 presents a flowchart with the main firing and operating control status of the launcher 10 performed by software embedded in the smart electronics of the preferred embodiment of the present invention.

[0047] Software constantly monitors the status of the bolts 41 on the ammunition trays 20, and notifies the user should it find any tray 20 loose. The purpose of this feature is to prevent the launcher 10 being used if any tray is not fully bolted onto its supporting launcher 10 and coming loose during its operations. If the trays 20 are coupled and bolted correctly, the software monitors the receipt of firing commands. If a command is received, it analyzes the amount of munitions that the user wishes to fire, selects the positions of the munitions to be fired (with priority for balancing the payload), and generates the firing signal for each of them.

[0048] The described coupling between the chassis 11 and the tray 20 is exemplified through the latch pins 22 on the tray 20 and fitting openings 32 on the fitting structure 30. However, the same removable coupling principle used for the tray 20 on the chassis 11 may be attained through several different configurations that perform the same function. For example, any part that prevents removal of the tray when slid sideways may be used instead of the illustrated latch pins 22, provided that the corresponding coupling with the fitting structure 30 takes place. Furthermore, the coupling mechanism is not limited to the illustrated fitting structure 30, which may be replaced by alternative configurations, such as levers, cables, knobs or any other type of part that allows a sideways movement through which a variation in the opening diameter comes into contact with the latch pins 22 on the tray 20.