WO2021251932A1

WO2021251932A1 - Laser-guided miniature missile system for hybrid threats

Info

Publication number: WO2021251932A1
Application number: PCT/TR2021/050545
Authority: WO
Inventors: Mustafa Özgür Ateşoğlu; Muhammed YÜKSEL; Ali Şimşek TEKEREK; Öznur Cansu SEÇKİN UZEL; Abdullah Alp MUHİDDİNOĞLU
Original assignee: Roketsan Roket Sanayi̇i̇ Ti̇caret A. Ş.
Priority date: 2020-06-08
Filing date: 2021-06-07
Publication date: 2021-12-16
Also published as: TR202008783A1

Abstract

The present invention relates to a laser-guided miniature missile system comprising a launch station (70); and a miniature missile (30) that is provided in said launch station (70), that has an elongated body (32) configured such that it may be launched from a canister (10) or a launch pod (20). The inventive miniature missile system comprises; a remote control station (80) that is connected such that it communicates by means of an RF receiver/transmitter (74) of the launch station (70) accommodated on a mobile vehicle (1) and an opposite RF receiver/transmitter (82); a central controller (72) that triggers a canister (10) or a launch pod (20) such that they launch the miniature missile (30) by means of a pod control member (76) driven by determining a launch command transmitted from the control station (80) to the launch station (70); and a flight controller (38) to the which the central controller (72) is connected such that said central controller (72) ensures signal transmission in a storage mode and that is mounted on the body (32) that activates a flight motor (38) at a predetermined flight motor activation time (t2) by being configured such that it can interrupt the signal communication with the central controller (72) subsequent to a launching moment (t0).

Description

LASER-GUIDED MINIATURE MISSILE SYSTEM FOR HYBRID THREATS

TECHNICAL FIELD OF THE INVENTION The present invention relates to guided missiles, and particularly to guided missiles used in ground target assaults and to their operation methods.

STATE OF THE ART

There are two different munitions systems known in the literature. These are guided munitions and unguided munitions. Unguided munitions may require a useful load as much as the concept of a miniature missile system does. However, the fact that these systems are unguided directly affects the success rate of an operation. Guided munitions, due to their useful load demands, decrease the number of unmanned aerial vehicle classes in which they can be used even though guided munitions may be adequate for the success of an operation. The useful load demand of guided munitions is approximately between 15-20 kg. This useful load demand, however, is way above the useful load-carrying capacity of a miniature unmanned aerial vehicle.

Unguided munitions used in available systems are required to be limited to a target point within 400 m range due to the maximum range of a grenade launcher munition. However, significant delivery and impact errors occur at long ranges due to the fact that the grenade launcher munition is unguided, that it follows a ballistic trajectory, and that it cannot resist potential deformations that may occur at the launching moment/during flight. Moreover, potential scatterings that will occur at the target area based on the fact that the destruction radius of the 40mm grenade launcher munition is 5m significantly reduce the effectiveness at the target.

The publication numbered US20160216075A1 discloses a gun-launched ballistically stable spinning laser-guided munition that is backward compatible with existing guns having rifled barrels as deployed for unguided munitions with the same caliber and follows the same ballistic trajectory. Thus, laser-guided munitions may be used with the existing base of weapons systems and logistics.

The munition disclosed in said publication comprises a plurality of explosive divert elements arranged around the bullet in order to produce a force vector along the center of mass of the bullet.

BRIEF DESCRIPTION OF THE INVENTION

The object of the present invention is to provide a safe, laser-guided miniature missile system that may be used in mobile vehicles such as miniature unmanned aerial vehicles (UAV) and pedestal-mounted missile systems.

The present invention, for the purpose of achieving the aforementioned object, comprises a laser-guided miniature missile system comprising a launch station and a miniature missile that is provided in said launch station, that has an elongated body that is configured such that it may be launched from a canister or a launch pod in an operation mode. The miniature missile system further comprises a remote control station that is connected such that it is capable of communicating by means of an RF (Radio Frequency) receiver/transmitter of a launch station accommodated on a mobile vehicle and an opposite RF receiver/transmitter; a central controller that triggers a canister or launch pod such that they launch the miniature missile by means of a pod control member by determining a launch command transmitted from the control station to the launch station; and a flight controller to which the central controller is connected such that said central controller ensures signal transmission in a storage mode, and that is mounted on a body that activates a flight motor at a predetermined flight motor activation time by being configured such that it can interrupt the signal communication with the central controller subsequent to a launching moment.

In a preferred embodiment of the present invention, the mobile vehicle comprises a miniature armed unmanned aerial vehicle or a mobile vehicle. In a preferred embodiment of the present invention, the flight controller is configured to deploy a folding tail located at the rear end subsequent to a launching moment. Said folding tail is accommodated inside the body and has a structure that radially extends outwards once triggered. The folding tail may comprise two, four, or more fins. Launch from the barrel occurs only through the impact created by the capsule under pressure. Subsequent to the launch impact, the miniature missile is stabilized on a straight course by means of the tail.

In a preferred embodiment of the present invention, the flight controller is configured to wait for a predetermined tail deployment time duration in order to deploy the tail subsequent to a launching moment. The missile does not require using a launch motor since the launch from the barrel occurs by means of the capsule. However, a certain tail deployment time is defined subsequent to exiting the barrel in order to prevent the tails from sustaining damage. This time, for example, may be 0.5 seconds at the most as of the launching moment.

In a preferred embodiment of the present invention, the flight controller is configured to outwardly deploy the folding control wings on the body after the flight motor is started. Thus, the thrust of the flight motor may be provided by means of the control actuation system comprising control wings without performing a thrust vector control inside the body.

In a preferred embodiment of the present invention, the flight controller is connected to a laser seeker head located on the front portion of the body such that there is a signal transmission therebetween, and the flight controller is configured to set a course based on the location data conveyed by a laser designator to the laser seeker head and to rotate the control wings in compliance with the course. Thus, the miniature missile possesses laser guidance.

In a preferred embodiment of the present invention, the canister of the launch pod comprises a groove that is adjusted such that it rotates the body in the extension axis at the launching moment. Said groove allows the miniature missile to spin as it exits the barrel. Thus, the spin of the body on the extension axis thereof ensures stable progress throughout the time that elapses from the launching moment to the deployment of the tail until the flight altitude is gained.

To achieve the aforementioned object, a preferred embodiment of the present invention comprises the process steps of; inserting the miniature missile into a canister or a launch pod located on the launch station; positioning the launch station at a location away from the control station; transmitting a firing signal from the control station to the launch station by means of the opposite receiver/transmitter; firing the body such that it launches from a frontal opening of the canister or the launch pod; deploying the folding tail at a rear end of the body outwardly towards the outer portion of the body by means of the flight controller on the launched body once a tail deployment time is reached based on the time measurement as of the launching moment; activating the flight motor by means of the flight controller; deploying the folding control wings on the body outwardly by means of the flight controller; and heading towards a designated target. In a preferred embodiment of the present invention, the launching of the miniature missile is performed by means of a launch motor located at the rear portion of the miniature missile. In different embodiments, the launching may be performed by means of a cartridge/capsule to be adapted to the canister or the launch pod.

A preferred embodiment of the present invention comprises the process step of designating a laser signal that reflects from a target marked by a laser designator by means of a laser seeker head adapted to the body from the front portion, setting a course towards a designated target and driving the control wings in accordance with said course by means of the flight controller. In a preferred embodiment, said laser designator is in the form of a separate mobile unit. In a possible embodiment, said laser designator may be adapted to a miniature armed unmanned aerial vehicle or a mobile vehicle.

A preferred embodiment of the present invention comprises the process step of interrupting all RF communication with the outer environment as of a launching moment by means of the flight controller. BRIEF DESCRIPTION OF THE FIGURES

FIGURE 1 illustrates a schematic view of the operation method showing a representational embodiment of a miniature guided missile system mounted on a miniature UAV or a pedestal.

FIGURE 2 illustrates the schematic view of the architecture of a representational Platform-Pod-Missile of the inventive miniature guided missile.

DETAILED DESCRIPTION OF THE INVENTION

In the detailed description provided herein, the inventive innovation is described only to provide a better understanding of the subject matter by examples and references and without constituting any limiting effect.

Figure 1 illustrates a representational embodiment of a miniature guided missile used on a canister (10) and launch pod (20) suited for a 40-mm munition in a state mounted on a land vehicle and a miniature armed unmanned aerial vehicle respectively. The canister (10) and the launch pod (20) are in the form of a tube and comprise an opening for launching at the front portion.

A miniature missile (30) for each is configured to be able to reach a range of 1000+ meters and inserted into the canister (10) and the launch pod (20) from the launching opening. A cylindrical body (32) of the miniature missile (30) is in compliance with the inner diameter of the canister (10) and the launch pod (20). A laser seeker head (36) is located at the front end of the body (32) while a flight motor (34) is positioned at a rear end (35) in an opposite direction thereto. A flight controller (38) comprising a processor is adapted to the body (32) such that it ensures signal transmission with the laser seeker head (36) and the flight motor (34). The inner diameter of the canister (10) and the launch pod (20) is 40 mm and the inner walls thereof have a groove (not shown) that extends from one end to the other.

When a firing command is received, a flight motor (37) of the miniature missile (30) is activated, thereby pushing the missile out of the canister (10) and the launch pod (20). The body (32) leaves the barrel (10) from the launching opening by spinning around itself by means of the groove. The miniature missile (30) begins gaining altitude by spinning around its axis from a launching moment (to) once the missile has left the barrel. Rear wings (40) that are positioned in a folded manner at the rear end (35) of the body (32) are deployed once a tail deployment time (t-i) has elapsed. Subsequently, the miniature missile (30) continues gaining altitude stably through the thrust of the launch motor (37), and the flight motor (34) is activated once the missile has gained a flight altitude (h) that makes operational activity possible. The flight altitude (h) is calculated by means of the flight controller (38) that measures the flight motor starting time (t2) and the flight motor (34) is activated subsequently. Then, the flight controller (38) measures the control wing deployment time (t3) and subsequently, deploys the control wings (50), which are in a folded state at that time, located at the front portion of the body (32). Laser seeker head (36) recognizes a laser signal that reflects from a target (A) designated by a laser designator (60) located at the front of the miniature missile (30) and determines the direction and orientation of the target so as to define the flight course (y). The flight controller (38) drives the control wings (50) towards the target (A) and ensures that the flight motor (34) delivers the miniature missile (30) to the target (A).

Figure 2 illustrates a schematic of the architecture of the missile system. A launch station (70) in the form of a miniature armed unmanned aerial vehicle and mobile vehicle respectively carries the launch pod (20) and canister (10) on a movable platform (75) thereof. An electronic central controller (72) comprising a processor is integrated into the platform (75) so as to transmit electrical signals. An RF receiver/transmitter (74) adapted to a launch station (70) establishes a connection so as to ensure data transmission over an opposite RF receiver/transmitter (82) to a control station (80) at a command center through an encrypted radio signal. There is a console (84) at the control station (80). An operator may drive the platform (75) over the console (84). The operator inputs the fire command by using the console (84) when a target (A) is marked by the laser designator (60). An operation method is activated by decrypting and transmitting the encrypted fire command to the launch station (70) over the RF receiver/transmitter by means of the central controller (72). In this case, the central controller (72) drives the pod control member (76) connected to the platform (75) and triggers the miniature missile (30) by means of a switch (77). Subsequently, the central controller (72) interrupts its connection with the flight controller (38). To that end, RF receiver/transmitter (74) is completely turned off by means of the central controller (72) from the launching moment (to) until the tail deployment time (t-i). REFERENCE NUMERALS

1 Mobile Vehicle 75 Platform 10 Canister 76 Pod Control Member 20 Launch Pod 77 Switch 30 Miniature Missile 80 Control Station 32 Body 82 Opposite RF Receiver/Transmitter

34 Flight Motor 84 Console

35 Rear End A Target

36 Laser Seeker Head to Launching Moment 38 Flight Controller ti Tail Deployment Time 40 Tail t2 Flight Motor Starting Time

50 Control Wing t3 Control Wing Deployment Time 60 Laser Designator h Flight Altitude 70 Launch Station y Flight Course 72 Central Controller

74 RF Receiver/Transmitter

Claims

1 A laser-guided miniature missile system comprising a launch station (70); and a miniature missile (30) that is provided in said launch station (70) and that has an elongated body (32) configured to be launched from a canister (10) or a launch pod (20) in an operation mode, characterized in that, it comprises; a remote control station (80) that is connected such that it communicates by means of an RF receiver/transmitter (74) of the launch station (70) accommodated on a mobile vehicle (1) and an opposite RF receiver/transmitter (82); a central controller (72) that triggers a canister (10) or a launch pod (20) such that they launch the miniature missile (30) by means of a pod control member (76) driven by determining a launch command transmitted from the control station (80) to the launch station (70); and a flight controller (38) to the which the central controller (72) is connected such that said central controller (72) ensures signal transmission in a storage mode and that is mounted on the body (32) that activates a flight motor (38) at a predetermined flight motor activation time (t2) by being configured such that it can interrupt the signal communication with the central controller (72) subsequent to a launching moment (to).

2 A missile system according to Claim 1 , characterized in that, said mobile vehicle (1) comprises a miniature armed unmanned aerial vehicle or a mobile vehicle.

3 A missile system according to any one of the preceding claims, characterized in that, said flight controller (38) is configured to deploy a folding tail (40) located at a rear end (35) subsequent to a launching moment (to).

4 A missile system according to Claim 3, characterized in that, said flight controller (38) is configured to wait for a predetermined tail deployment time (t-i) to deploy the tail (40) subsequent to a launching moment (to). 5- A missile system according to any one of the preceding claims, characterized in that, said flight controller (38) is configured to outwardly deploy control wings (50) on the body (32) after the flight motor (34) is activated.

6- A missile system according to Claim 5, characterized in that, said flight controller (38) is configured to be connected to a laser seeker head (36) located on the front portion of the body (32) such that there is a signal transmission therebetween, and said flight controller (38) is further configured to set a course based on the location data conveyed by a laser designator (60) to the laser seeker head (36) and to rotate the control wings (50) in accordance with the course.

7- A missile system according to any one of the preceding claims, characterized in that, said canister (10) and launch pod (20) comprise a groove that is adjusted such that it spins the body (32) in the extension axis at the launching moment (to).

8- An operation method for a missile system according to any one of the preceding claims, characterized in that, it comprises the process steps of; inserting the miniature missile (30) into a canister (10) or a launch pod (20) located on the launch station (70); positioning the launch station (70) at a location away from the control station (80); transmitting a firing signal from the control station (80) to the launch station (70) by means of the opposite receiver/transmitter (82); firing the body (32) such that it launches from a frontal opening of the canister (10) or the launch pod (20); deploying the folding tail (40) at a rear end (35) of the body (32) outwardly towards the outer portion of the body (32) by means of the flight controller (38) on the launched body (32) once a tail deployment time (t-i) is reached based on the time measurement as of the launching moment (to); activating the flight motor (34) by means of the flight controller (38); deploying the folding control wings (50) on the body (32) outwardly by means of the flight controller (38); and heading towards a designated target (A). An operation method according to Claim 10, characterized in that, it comprises the process steps of; determining a laser signal that reflects from a target (A) which is marked with a laser designator (60), by means of a laser seeker head (36) that is adapted to the body (32) from a front portion thereof, setting a course towards a target (A) and driving the control wings (50) in accordance with said course by means of the flight controller (38). An operation method for a missile system according to Claims 8-9, characterized in that, it comprises the process step of interrupting all RF communication with the outer environment as of a launching moment (to) by means of the flight controller (38).