Improved guided munition system

Abstract

The invention relates to a munition system (10) comprising: - a transport device, referred to as cargo (DC), the cargo device comprising at least one sub-assembly (SE, SE1, SE2) and being configured to eject said sub-assembly once said zone is reached, a sub-assembly comprising: a deceleration device (DR) configured to decelerate the sub-assembly during its descent, once ejected, an analysis device (DA) of an environment of said sub-assembly, a detection and recognition device (DTR) of said target, a guidance device (DGSE) referred to as beacon configured to guide the sub-assembly and stabilize it in the vicinity of said target, once the sub-assembly has been ejected by the cargo device, a signal emission device (DE) of a signal (SB) configured to emit said signal once said sub-assembly has stabilized in the vicinity of said target,-at least one so-called full-charge munition (FCM) comprising a guidance device (GD), referred to as munition configured to guide said munition onto said signal (SB). Figure 3,

Description

Title of the invention: Improved guided munition system FIELD OF INVENTION

[0001] The present invention relates to a munition system enabling precision artillery fire in a harsh environment. STATE OF THE ART

[0002] To ensure fire superiority over the adversary, artillery seeks to increase its range and accuracy. Accuracy is achieved through the use of guided munitions capable of correcting their trajectory.

[0003] In existing solutions, a first guidance method relies on the use of satellite positioning signals (GNSS). Knowing its coordinates and using the satellite positioning signals, the munition guides itself towards the target whose coordinates were previously recorded during the mission preparation phase. An example of this type of munition is the Excalibur artillery shell (155 mm) developed by Raytheon (USA). Another example is the Precision Guidance Kit (PGK) from Northrop Grumman, also for 155 mm.

[0004] A second guidance method is based on laser designation. The target is targeted by a third party with a laser (often carried by an aircraft, a drone, or special forces in contact). The munition is equipped with a laser designator kit that allows it to detect the light spot emitted by the target illuminated by the laser (laser spot) and to adjust its trajectory to reach the laser spot. Such kits incorporate photoreceptors (4Q, mosaics, arrays) that measure the deviation between the munition's axis and the laser spot. A first example is the BAE Systems APKWS kit for a 70 mm rocket, and a second example is the SAL kit for the Leonardo Vulcano munition (155 mm).

[0005] In a high-intensity conflict context, electromagnetic jamming, also known as a "GNSS denied" environment, and the difficulty of flying over or approaching the adversary defeat these guidance methods.

[0006] Ideally, the munition should be equipped with an autonomous scene analysis capability so that it can locate the target designated to it during the mission preparation phase. A munition equipped with an imager and an image processing chain (georeferencing, target detection & recognition) could be capable of analyzing a ground area, locating the target, and guiding itself to it.

[0007] An example of such a fully autonomous munition 11, known as "imaging munition", is illustrated [Fig.1].

[0008] The munition 11 comprises a tail assembly 12, an explosive charge 13 occupying the "rear" part of the munition, the volume of which is sought to be maximized in order to maximize its military effect, but under the constraint of the caliber and volume required for the other elements, a GNSS receiver 14, flight actuators 15 (canard) allowing it to modify its trajectory according to guidance orders, a spread gauge 16 comprising the imager, the image processing chain and a computer, and an ejectable cap 17.

[0009] However, the technical challenges in achieving such a munition are very significant, particularly with regard to the following themes:

[0010] Compactness: a full military payload and flight actuators leave a very limited volume for the terminal guidance kit / deviation gauge: the volume allocated to the "intelligent" part is small.

[0011] The very short time frame between the moment the guidance system is able to acquire an image, once the munition has descended below the cloud layer and to a ground distance corresponding to a photometric budget allowing image acquisition, requires the detection of sufficient photons despite the modest entrance pupil size imposed by the munition's forward geometry. During this highly constrained 2- to 3-second time frame, the image processing chain must analyze the area, recognize the target, and generate the guidance commands. One consequence of this is the need for significant computing power.

[0012] The quality of images acquired in flight, in particular if the munition is in autorotation.

[0013] Military full-charge munition incorporating an optical guidance chain will probably not be available for another ten years.

[0014] Furthermore, there are munitions containing reduced warheads (as opposed to a full warhead) with specific kinematics, an example of which is shown schematically in [Fig. 2] (the 155 mm artillery shell known as Bonus from BAE Systems and Nexter). The munition 20 comprises a so-called "cargo" section 22 configured to transport subassemblies 21 to the target area. These subassemblies are ejected upon arrival at the target area. The munition also includes a trigger fuze 24 that determines the timing of the subassembly ejection by the ejection device 23. Once ejected, these subassemblies 21 undergo a slowed descent (parachute, fins), analyze the area, detect the target, and direct their warhead towards the target (via steerable flight actuators such as rotary wings or steerable fins). Such munitions are limited to targets such as armored vehicles requiring only a small (formed) charge.Another example of this type of munition is the Smart 155 shell manufactured by Rheinmetall and Diehl (Germany).

[0015] In summary: - Existing solutions (GNSS or SAL guidance) are not suitable for high-intensity environments. - The long-term solution (image processing chain integrated into a fully charged munition) will be slow to become available due to its technical complexity. - The small payload solution, in cargo munition, is limited to a restricted target family.

[0016] One object of the present invention is to remedy the aforementioned drawbacks by proposing a munition system comprising two different elements which cooperate, this cooperation making it possible to produce a munition carrying a full explosive charge guided to the target, without it incorporating a complex processing / guidance chain. DESCRIPTION OF THE INVENTION

[0017] The present invention relates to a munition system comprising: - a transport device, referred to as a cargo device, configured to reach and fly over an area comprising at least one target, the cargo device comprising at least one sub-assembly and being configured to eject said sub-assembly once said area has been reached, the sub-assembly comprising: • a deceleration device configured to slow the subassembly during its descent, once ejected, • a device for analyzing the environment of said subset, • a device for detecting and recognizing said target, • a guidance device called a beacon configured to guide the subassembly and to stabilize it in the vicinity of said target, once the subassembly has been ejected by the cargo device, • a signal-emitting device configured to emit said signal once said subassembly has stabilized in the vicinity of said target, - at least one so-called full-charge munition configured to reach and fly over said area independently of the cargo device, and including a guidance device called munition configured to guide said munition on said signal.

[0018] In one embodiment, the cargo device has a shell- or rocket-type structure without an explosive charge. In another embodiment, the cargo device has a missile- or bomb-type structure without an explosive charge. In yet another embodiment, the DC cargo device is a drone.

[0019] According to one embodiment, the subset analysis device is chosen from: a visible or infrared imaging device, a radio frequency imaging device, a lidar.

[0020] According to a first embodiment the emission device is configured to emit an optical signal, and the munition guidance device is configured to use an optical task in a given wavelength range.

[0021] According to a second embodiment the emission device is configured to emit a signal generated by a pyrotechnic composition.

[0022] According to a third embodiment the transmitting device is an antenna configured to emit a radio frequency signal.

[0023] According to one variant, the cargo device and the fully loaded munition have an identical structure in order to be adapted to the same type of launch system for sending to said area.

[0024] According to one embodiment, the cargo device comprises at least a first and a second sub-assembly, the area comprising at least a first and a second target, said first and second sub-assemblies being configured to stabilize in the vicinity of the first and second targets, respectively. Furthermore, a first and a second emitting device associated with the first and second sub-assemblies, respectively, are configured to emit a first and a second signal, respectively. The munition system further comprises at least a first and a second fully charged munition, the first and second munition guidance devices of which are configured to be guided to the first and second signals, respectively.

[0025] According to another aspect, the invention relates to a method for destroying a target with a munition system comprising the steps of: A. Sending a transport device, called the cargo, overflying an area comprising at least one target, the cargo device comprising at least one sub-assembly; B. Sending at least one munition, called the full-load munition, overflying said area independently of the cargo device; C. Dropping or ejecting said sub-assembly once said area is reached and slowing said sub-assembly during its descent; D. Analyzing an environment of said ejected sub-assembly, detecting and recognizing said target in the environment with an analysis device specific to said sub-assembly; E. Guiding the sub-assembly towards the target and stabilizing it in the vicinity of said target with a guidance device, called the beacon, specific to said sub-assembly; F. Emitting a signal once said sub-assembly has stabilized in the vicinity of said target.with a specific emission device for said sub-assembly, G guides said fully charged munition onto said signal with a guidance device for said munition specific to said fully charged munition.

[0026] According to one embodiment, steps A and B are implemented so that the fully charged munition reaches the area once the signal is emitted in step F.

[0027] According to one embodiment the cargo device is an uncharged shell, the fully charged munition is a shell, and steps A and B are implemented by one or two guns adapted to launch said shells.

[0028] The following description presents several embodiments of the device of the invention: these examples are not limiting to the scope of the invention. These embodiments present both the essential features of the invention and additional features related to the embodiments considered.

[0029] The invention will be better understood and other features, objectives and advantages thereof will become apparent from the following detailed description and with reference to the accompanying drawings given by way of non-limiting examples and in which:

[0030] The [Fig. 1] already cited illustrates a future imaging munition.

[0031] The [Fig.2] already cited illustrates a low-charge guided munition.

[0032] Fig. 3 illustrates the ammunition system according to the invention.

[0033] Figure 4 illustrates one embodiment of the invention in an operational context. with two subsets, two targets and two types of ammunition.

[0034] Fig. 5 illustrates steps A (left diagram) and B (right diagram) of the process according to the invention.

[0035] Figure 6 illustrates on the left diagram steps C and D and on the right diagram steps E and F of the process according to the invention.

[0036] Figure 7 illustrates step G of the process according to the invention. DETAILED DESCRIPTION OF THE INVENTION

[0037] The idea behind the munition system 10 according to the invention is to divide the problem into two parts, resulting in a tandem of two complementary elements, each optimized for a specific function. A first element without an explosive charge performs area analysis and target recognition, and a second element is a munition carrying a full warhead, the guidance of which is facilitated by a "beacon" deployed by the first element. At the operational level, a coordinated firing of the first element, the "munition" without an explosive charge, is carried out, followed by the fully loaded munition, which reaches the target thanks to the guidance provided by the beacon.

[0038] The munition system 10 according to the invention, a two-element "kit," is illustrated [Fig. 3]. It comprises a transport device called the DC cargo system configured to reach and fly over an area ZN containing at least one target TA. The cargo system comprises at least one SE subassembly and is configured to eject the subassembly once the area ZN has been reached. The DC cargo system does not carry any warhead.

[0039] According to one embodiment, the DC cargo device has a shell- or rocket-type structure, as in the Bonus-type munition. In the case of a shell the trajectory to the zone is ballistic in type, in the case of a rocket the ballistic trajectory is improved by steerable flight actuators.

[0040] According to another embodiment the DC cargo device has a missile-type structure (self-propelled) or a bomb-type structure (without explosive charge).

[0041] According to yet another embodiment, the DC cargo device is a drone.

[0042] The mission of the cargo device is to drop the SE subassembly onto the area.

[0043] The SE subassembly includes a deceleration device DR configured to slow it during its descent after ejection, an environmental analysis device DA for the subassembly, typically located at its front, and a target detection and recognition device DTR. It also includes a guidance device DGSE, referred to as a beacon guidance device, configured to guide and stabilize the SE subassembly in the vicinity of the target after the SE subassembly has been ejected by the cargo device DC and the target has been located by the DTR. Positioning on the target can be performed via air and optionally on the ground. Finally, the SE subassembly includes a signal transmitter DE configured to emit the SB signal once the subassembly has stabilized near the target. The SB signal is activated once the SE is positioned close to the target.

[0044] The munition system 10 also includes at least one MPC full-charge munition configured to reach and overfly the ZN zone independently of the cargo device. The MPC full-charge munition obviously includes a CM warhead and also includes a DGM guidance device, referred to as the munition guidance device, configured to guide the full-charge munition on the SB signal. The MPC's DGM munition guidance device is adapted to the emitted SB signal.

[0045] Thus the SE sub-assembly, once positioned close to the target, acts as an impact "beacon", having the function of guiding the fully charged munition onto the target.

[0046] Thus, the ammunition system according to the invention comprises two cooperating elements: one specialized in target acquisition and the other a simple warhead. The ammunition system according to the invention enables high-precision, full-charge artillery strikes compatible with mature and currently available technologies.

[0047] Operationally, it is appropriate that the cargo device arrives first on site, with the fully loaded munition arriving afterwards, once the sub-assembly has been ejected and placed near the target.

[0048] According to one embodiment, the fully charged MPC munition is of the shell or rocket type. According to another embodiment, the fully charged munition is of the bomb type, and according to yet another embodiment, the fully charged munition is of the type missile. These munitions are equipped with a guidance system adapted to their nature and to the beacon (SB signal) used. They can be conventional (see below).

[0049] A fully charged munition is associated, via its guidance device, with a given subset, i.e. a given emission signal.

[0050] In one embodiment, several MPC munitions are associated with a given subset, to maximize the probability of destroying the target.

[0051] In a preferred variant the DC cargo device comprises N subsets, typically two, i.e. at least a first subset SE1 and a second subset SE2, as illustrated [Fig.4] in an operational context.

[0052] A multiplicity of subsets implies a multiplicity of MPC munition, each munition being configured to be guided on one of the subsets, typically by a specific coding of the SB signal.

[0053] In a first embodiment, the ZN zone comprises only one target and the various sub-assemblies are guided to this single target, the multiplicity of sub-assemblies and associated munitions maximizing the probability of destruction of the target.

[0054] In a second embodiment, the zone ZN comprises several targets, namely at least a first target TA1 and a second target TA, and the subassemblies SE1 and SE2 are configured to stabilize themselves in the vicinity of the first and second targets, respectively. Thus, each subassembly is associated with a target. For the associated munitions, discrimination between targets is achieved by encoding the emitted signal. Thus, the subassembly SE1 comprises a first emitting device DE1 configured to emit a first signal SI, and the subassembly SE2 comprises a second emitting device DE2 configured to emit a second signal S2. This is typically a signal of the same nature (see below) with specific encoding.

[0055] The munition system also includes at least one first full-charge munition MPC1 comprising a first munition guidance device DGM1 and a second full-charge munition MPC2 comprising a second munition guidance device DGM2. The first munition guidance device DGM1 is configured to be guided on the first signal SI and the second munition guidance device DGM2 is configured to be guided on the second signal S2 as illustrated [Fig.4].

[0056] Once subassembly SE1 is located near TA1, it emits the signal SI to guide MPC1 to TA1 via DGM1. Similarly, once subassembly SE2 is located near TA2, it emits the signal S2 to guide MPC2 to TA2 via DGM2.

[0057] A combination of the two aforementioned modes is also possible with several munitions associated with a given subset, and several subsets, a subset being associated with a target (therefore several targets).

[0058] According to one embodiment, the cargo device and the fully loaded munition have an identical structure so that they can be adapted to the same type of launch system for delivery to the target area. For example, these could be artillery shells adapted for firing from a 155mm gun or similar. The cargo device then has the structure of a shell without a warhead, and the munition that of a conventional guided shell. They can be fired sequentially, first the cargo device then the munition, or simultaneously. In the latter case, the arrival of the cargo device in the target area before the arrival of the munition is achieved by differentiating their trajectories.

[0059] Both types of shells (cargo and munition) can be fired by the same gun, or by two guns of the same firing battery.

[0060] According to one embodiment, the DA analysis device of the SE subset is chosen from: a visible or infrared imaging device, a radio frequency imaging device, a lidar.

[0061] The beacons, i.e. the DE emission devices of the SE subassemblies, can be active or passive. They must constitute an easily detectable marker (and suitable for spread measurement) for the DGM ammunition guidance device of the associated ammunition.

[0062] According to one embodiment, the emitted signal is an optical signal (light beacon), visible or infrared. Typically, the emitting device DE is chosen from an LED, a laser diode, or a laser.

[0063] Preferably the DGM munition guidance device is configured to use an optical task in a given wavelength range, including the case of a single wavelength.

[0064] This could be, for example, a four-quadrant homing device on an optical spot. An example is a four-quadrant device detecting the near-IR (typically 1.06 pm), such as a semi-active laser or SAL kit known from the prior art.

[0065] Another example is the use of a low-resolution imager (typically sensitive in the visible or 1TR range) to guide the munition. This imager is not efficient enough to precisely locate the target like the one used by the SE subassembly, but has sufficient resolution to guide the munition onto a task. The choice of wavelength results from a search for the optimal balance between cost (beacon + guidance kit) and performance (locking range, etc.).

[0066] According to one embodiment, the emitted signal is generated by a pyrotechnic composition. This is a "thermal" signal (generation of a hot spot). exhibiting a very broad spectral emission band. The associated DGM munition guidance system is, for example, a four-quadrant thermal seeker (detection in the 8-12 pm band) or a low-resolution imager. Low resolution is defined as a pixel count typically below 100,000 pixels. The image processing also features a simplified algorithm compared to that which would be required for a fully loaded military munition incorporating a complex optical guidance system (future munition).

[0067] According to another embodiment, the emitted signal is a radio frequency signal typically emitted by an antenna. An associated guidance device is typically a device for identifying the direction of emission (direction measurement, wavefront analysis, etc.).

[0068] An example of a passive beacon is a retroreflective beacon in the visible, infrared, or radar ranges. The "emitting" device DE is here a reflector, and the "emitted" signal is a signal present in the environment of the beacon and reflected by it within an angular range covering the area in which the fully charged munition is located during the approach.

[0069] According to another aspect, the invention relates to a method for destroying a target with a munition system. The different stages of the method according to the invention are illustrated in Figures 5, 6 and 7 for the case of two sets, two fully charged munitions and two targets.

[0070] The method comprises a first step A consisting of sending a DC cargo transport device to fly over an area ZN comprising at least one target, the cargo device comprising at least one subset as described above. Then, in a second step B, at least one full-charge MPC munition is sent to fly over the area ZN independently of the cargo device. As explained above, the two steps A and B can be carried out sequentially or simultaneously. Steps A and B are illustrated [Fig. 5].

[0071] During step C, the cargo device ejects the SE subassembly once the ZN zone is reached, and the ejected subassembly is slowed down during its descent. In step D, the environment of the ejected subassembly is analyzed, and the target is detected and recognized in the environment using the subassembly's own analysis device DA. Steps C and D are illustrated in [Fig. 6] on the left.

[0072] In step E, the subassembly is guided towards the target and stabilized in its vicinity using a DGSE beacon guidance device specific to the subassembly. In step F, a transmission device specific to the subassembly emits an SB signal once the subassembly has stabilized in its vicinity of the target. Steps E and F are illustrated in [Fig. 6] on the right.

[0073] In an illustrated step G [Fig.7] the fully loaded munition is guided on the signal with a guidance device called munition specific to the fully loaded munition.

[0074] Preferably steps A and B are implemented so that the fully charged munition reaches the area once the signal is emitted in step F.

[0075] According to one embodiment the cargo device is an uncharged shell, the fully charged munition is a shell, and steps A and B are implemented by one or two guns adapted to launch said shells.

Claims

Demands

1. Munition system (10) comprising: - a transport device, referred to as cargo (CD), configured to reach and fly over an area (ZN) comprising at least one target (TA, TA1, TA2), the cargo device comprising at least one sub-assembly (SE, SE1, SE2) and being configured to eject said sub-assembly once said area is reached, the sub-assembly comprising: • a deceleration device (DR) configured to decelerate the sub-assembly during its descent, once ejected, • an analysis device (DA) of an environment of said sub-assembly, • a detection and recognition device (DTR) of said target, • a guidance device (DGSE) referred to as beacon configured to guide the sub-assembly and stabilize it in the vicinity of said target, once the sub-assembly has been ejected by the cargo device,• a signal emission device (SED) for a signal (SB) configured to emit said signal once said subassembly has stabilized in the vicinity of said target, -at least one full-charge munition (FCM) configured to reach and fly over said zone (ZN) independently of the cargo device, and comprising a guidance device (GDD) said munition configured to guide said munition onto said signal (SB).

2. Munition system according to the preceding claim in which the cargo device (CD) has a shell- or rocket-type structure without an explosive charge.

3. Munition system according to claim 1 in which the cargo device (CD) has a missile- or bomb-type structure without an explosive charge.

4. Munition system according to claim 1 wherein the cargo device (CD) is a drone.

5. Munition system according to any one of the preceding claims wherein the analysis device of said subassembly is selected from: a visible or infrared imaging device, a radio frequency imaging device, a lidar.

6. Munition system according to any one of the preceding claims, wherein the emitting device is configured to emit a signal optical, and in which the munition guidance device (DGM) is configured to use an optical task in a given wavelength range.

7. Munition system according to any one of claims 1 to 6 wherein the emitting device is configured to emit a signal generated by a pyrotechnic composition.

8. Munition system according to any one of claims 1 to 6 wherein the emitting device is an antenna configured to emit a radio frequency signal.

9. Munition system according to any one of the preceding claims wherein the cargo device and the fully loaded munition have an identical structure in order to be adapted to the same type of launching system for being sent to said area.

10. Munition system according to any one of the preceding claims wherein the cargo device comprises at least a first (SE1) and a second (SE2) subset, the area comprising at least a first (TA1) and a second (TA2) target, said first and second subsets being configured to stabilize in the vicinity of the first and second target respectively, wherein a first (DE1) and a second (DE2) emitting device associated respectively with the first and second subsets are configured to emit a first (SI) and a second signal (S2) respectively, the munition system further comprising at least a first (MPC1) and a second (MPC2) fully loaded munition of which the first (DGM1) and second (DGM2) munition guidance devices respectively are configured to be guided on the first and second signal respectively.

11. Method (100) of destroying a target with a munition system comprising the steps of: A sending a transport device, referred to as cargo (CD), to fly over an area (ZN) comprising at least one target (TA, TA1, TA2), the cargo device comprising at least one sub-assembly (SE, SE1, SE2), B sending at least one munition, referred to as full-charge munition (FCM), to fly over said area (ZN) independently of the cargo device, C releasing or ejecting said sub-assembly once said area is reached and slowing said sub-assembly during its descent, D analyze an environment of said ejected sub-assembly, detect and recognize said target in the environment with an analysis device proper to said sub-assembly E guide the sub-assembly towards the target and stabilize it in the vicinity of said target with a guidance device, called a beacon, proper to said sub-assembly, F emit a signal once said sub-assembly is stabilized in the vicinity of said target, with an emission device proper to said sub-assembly, G guide said full-charge munition on said signal with a guidance device called munition proper to said full-charge munition.

12. A method according to the preceding claim wherein steps A and B are implemented so that the fully charged munition reaches the area once the signal is emitted in step F.

13. A method according to any one of claims 11 or 12 wherein the cargo device is an uncharged shell, the fully charged munition is a shell, and steps A and B are carried out by one or two guns adapted for launching said shells.

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