FOLDABLE WING AND V TAIL VERSION UNMANNED AERIAL VEHICLE

TECHNICAL AREA

The invention is about an unmanned aerial vehicle which deploys its folded wing and tail after launching from a tube and detonates its exposive warhead upon reaching the target and is used for defensive and/or offensive purposes in regional and/or national areas.

PRIOR ART

Morphing unmanned aerial vehicles have been used in many different fields, especially in the defense industries. Morphing unmanned aerial vehicles can be launced from air, ground and even from shoulder either as single or as multiple units, due to having foldable wing/tail and launching units. These type of unmanned aerial vehicles are often used for suicide attack. Suicide attack missions involve approaching a specific target and detonating the carried ammunition, and destroying itself along with the target.

In the aforementioned unmanned aerial vehicles, the design and deployment of the wing/tail are of great importance. That is to say; the deployment method affects both the wing/tail design and the airframe design. In addition, by minimizing the vehicle volume withwing/tail folded, these related unmanned aerial vehicles can be used more effectively with much smaller launch mechanisms.

In the “Aerodynamic characteristics of a novel catapult launched morphing tandemwing unmanned aerial vehicle" paper by Liag Gao and her associates, a wing deployment mechanism for morphing unamnned aerial vehicles is explained. (1 ).Here, the two wings, which are placed on the two shafts provided on the beam placed longitudinally on the fuselage, are opened with a pivotal movement after launch. In addition, a similar structure is shown in patent applications with publication numbers CN103043214A and EP2475575B1. In another paper by L. Dufour and her associates, titled “A Drone with Insect-Inspired Folding Wings", another foldable wing structure is explained (2). This structure is based on insect wings and, accordingly, the wings are designed as multi-element and overlapping. But this structure is extremely complex and has many attachment and folding axes. This situation causes difficulty in production and decrease in durability.

In a master's thesis by Cory Sudduth titled “Design of A Hybrid Rocket / Inflatable Wing UAV”, an unmanned aerial vehicle with wings inflated during launch was studied (3). Although a compact structure was provided here with a wing mounting body, synchronous deployment of the wings could not be achieved as stated in the study. This will cause imbalance, especially during launch.

The reason for presenting the invention is that studies for target detection and maximizing damage to the target in suicide attack type unmanned areial vehicles are still continuing.

The reason for the invention is that after target detection is achieved, the unmanned aerial vehicle is launched with a launch mechanism and its wings are deployed. However, the desired flight is prevented if the wings do not deploy at the desired amount, or deploy late or wings deform due to post-launch accelerations of the unmanned aerial vehicle depending on position of the wings, The reason for the invention is to reach the target and detonate the explosive with the help of the camera and auto-pilot system in the unmanned aerial vehicle. In case the time to reach the target is longer than desired, most of the tracking of the target is provided by the unmanned aerial vehicle itself. Accordingly, the prolongation of the flight time puts the privacy and detectablitiy principles at risk. With the increase in the time to reach the target, the desired efficiency in the detonation process can not be achieved and sometimes causes the waste of the unmanned aerial vehicle due to the inability to reach the target in sufficient time.

The reason for the invention is that the target guidance of the existing systems is made either by the control operator on the ground according to the on-board camera image or with the help of ground based radar. It is to ensure that the failures caused by the delays and errors that occur here are eliminated. The reason for presenting the invention is that, the time to hold in the air, the time to reach target and stability of the unmanned aerial vehicle, based on the delays in the wing deployment are of utmost importance. However, the wing and tails deployment time in current unmanned aerial vehicles results in acceleration and speed loss of the unmanned aerial vehicle and adversely affects the arrival time to the target.

As a result, all the above-mentioned problems have made it necessary to innovate in the relevant technical field.

OBJECTIVE OF THE INVENTION

The purpose of the invention is to reveal an unmanned aerial vehicle structure that has similar dimensions with the existing products, but with different wing/tail and deployment mechanisms, and can hit the target at a higher rate by easier control in the air

Another purpose of the invention is to reveal the structure of a new target tracking and detonation system that can provide more efficient target detection and target reach.

Another purpose of the invention is to reveal the structure of a system that maximizes the flight efficiency of the unmanned aerial vehicle.

Another target of the invention is to increase the speed of the unmanned aerial vehicle, to ensure that it reaches the target in a shorter time and to provide quick response in emergency situations.

Another purpose of the invention is to enable the deployment of wing/tail at the desired altitude and speed, immediately after the unmanned aerial vehicle launch, using a mechanism interacting with the wing/tail.

Another target of the invention is to make the best use of the flight time by providing automatic control of the wings, preventing possible delays.

BRIEF DESCRIPTION OF THE INVENTION

The invention includes launch mechanism to provide take-off support, radar and image acquisition element to detect the target and confirm the detected target. It consists of a fuselage, at least one ammunition ready to explode mounted on the fuselage, the propeller to provide sustained flight, and the propeller blades and propeller hub that move together with the mentioned propeller. It consists of at least one tail and wing to maintain balance and flight after takeoff. There is a wing structure in which the spring mechanism will be located and a wing slot in which the wings will be protected while retracted. It is an unmanned aerial vehicle that can be remotely controlled with ailerons and processing unit, in order to increase the load carrying capacity of the mentioned wings and provide control around roll axis during flight.

In an alternative application of the invention, there is a wing deployment element to enable the deployment of the wings which enables flight of the unmanned aerial vehicle.

Another alternative application of the invention includes the wing deployment shaft to undertake the wing deployment element function to to enable the deployment of the wings.

In another alternative application of the invention, there is a shaft connection area to prevent the wing deployment shaft from coming off and breaking during its upward movement.

A preferred embodiment of the invention includes the shaft rotary connection of the wing, which allows the wing deployment shaft to perform the rotational movement to ensure the deployment of the wings, and prevent it from being damaged in case of linear movement.

In another preferred application of the invention, there is a shaft lower fixing point to transfer the torque or acceleration from the shaft rotary connection to the wing deployment shaft.

Another preferred embodiment of the invention includes tail deployment element that enables the tails to be deployed in order to enable the unmanned aerial vehicle balance and control. In another preferred embodiment of the invention, there is a tail deployment hub in order to ensure the deployment of the tail by being in constant contact with the tail and to prevent the tail from closing during the flight.

A possible application of the invention is the wing deployment element, which is provided to deploy the wings which enables the unmanned aerial vehicle to fly.lt includes the wing deployment element upper body, wing deployment element side body and wing deployment element lower body, which protects the mentioned wing deployment element and prevents damage from any contact and wrapping it to protecting from external effects.

In another possible application of the invention, there is a shaft connection screw in order to fix the shaft connection area, which is used to hold the wing deployment shaftin the wing opening element.

In another possible application of the invention, there are shaft fixing feet that enable the wing deployment shaft inside the wing deployment element to be fixed on the ground.

Another possible application of the invention includes the tail deployment assembly element to ensure that the tail deployment element is fixed by placing it on the ground in order to ensure that the tail is deployed and remain deployed continuously.

In another possible application of the invention, there is a tail clamping element to ensure the tighteningof the mentioned tail deployment base element and to increase its stability.

Another possible application of the invention includes the tail crossover space in which the tail deployment hub moves continuouslyback and forth.

BRIEF DESCRIPTION OF THE FIGURES

Figure 1 , shows the fuselage, propeller and wing and tail elements of the unmanned aerial vehicle.

Figure 2, shows the representative schematic view of the system. Figure 3, shows the view of the unmanned aerial vehicle with its wing/tail deployed after launch.

Figure 4, shows the appearance of the unmanned aerial vehicle during launch.

Figure 5, shows the appearance of the fuselage of the unmanned aerial vehicle with wing/tail retracted.

Figure 6, shows the front view of the unmanned aerial vehicle during flight with its wing/tail deployed.

Figure 7 shows the view of the mechanism that enables the wing of the unmanned aerial vehicle to be deployed.

Figure 8 shows the view of the mechanism that enables the tail of the unmanned aerial vehicle to be deployed.

Figure 9, shows the view of the V-tail structure of the unmanned aerial vehicle.

EXPLANATION OF REFERENCE NUMBERS IN THE FIGURES

F. Launch mechanism

H. Target

II. Unmanned aerial vehicle

IA. Image acquisition element

R. Radar

IB. Processing unit

10. Fuselage

11 . Wing nest

20. Wing

201 . Wing assembly 202. Aileron

30. Propeller

301 . Propeller blade

302. Propeller hub

40. Ammunition

60. Tail

601 . Tail control surface

80. Wing deployment element

801 . Wing deployment element upper body

802. Wing deployment element side body

803. Wing deployment element lower body

81 . Shaft connection zone

811. Shaft connecting screw

82. Shaft rotation connection

83. Shaft lower fixing point

84. Wing opening shaft

85. Shaft fixing feet

90. Tail deployment assembly

91. Tail deployment base element

92. Tail clamping element

93. Tail deployment body 94. Taildeployment hub

95. Tail pass gap

DETAILED DESCRIPTION OF THE INVENTION

In this detailed description, the subject of the invention is only explained by examples that will not have any limiting effect, for better understanding of the subject.

The invention described in detail below is relevant to a new type unmanned aerial vehicle (I) to be used in the offensive or defensive roles, designed to enable the user to reach her target (H) without being harmed.

The invention is set forth by including the following elements:

• There is a launch mechanism (F) to enable the unmanned aerial vehicle (I) to be launched.

• Radar (R) for identifying the target (H) to enable the unmanned aerial vehicle (I) to do its mission.

• There is an image acquisition element (IA) to distinguish whether the object identified by the mentioned radar (R) is the correct target (H).

• There is a processing unit (IB), which allows the unmanned aerial vehicle (I) to be controlled manually, and also to process the information it receives from the launch mechanism (F), image acquisition element (IA) and radar (R).

• A fuselage that constitutes the Unmanned Aerial Vehicle (I), having a longtudinal structure, housing the ammunitioned) which enables the mission of the Unmanned Aerial Vehicle (I), where the wings (20) are protected in the retracted position, housing the launch mechanism (F) to enable the launching to take place and the aft body (10) in which the propeller (30) is located to sustain the flight ofunction.

• There is a wing (20) to fly the unmanned aerial vehicle (I) and increase the endurance in the air.

• In order to enable the unmanned aerial vehicle (I) to be launced, there is a wing nest (11 ) that allows the mentioned wings (20) to be kept in the retracted position. • There is an aileron(202) to be used in case of need for higher lift at low speeds during the launch and landing and provide balance and control around the roll axes of the unmanned aerial vehicle (I).

• There is a propeller (30) to enable the unmanned aerial vehicle (I) to accelerate after launch.

• It includes a propeller blade (301 ) with a rotating structure to enable the said propeller (30) to operate.

• It contains the propeller hub (302) that provides the connection with the motor in order to ensure the operation of the mentioned propeller (30).

• There is an explosive and flammable ammunition(40) that the unmanned aerial vehicle (I) will release to the target (H) to cause an explosion in case of offense and/or defense.

• It includes a tail (60) that allows the unmanned aerial vehicle (I) to maintain its balance during flight

• There is a tail control surface (601 ) in order provide pitch and yaw control of the Unmanned Aerial Vehicle (I) during flight.

• There is a wing deployment element (80) to enable the wings (20) of the unmanned aerial vehicle (I) to be opened by spring force.

• There are wing deployment element upper body (801 ), wing deployment element side body (802) and wing deployment element lower body (803) to form the mentioned wing deployment element (80) and to protect it from external effects.

• In order to ensure that the mentioned wing deployment element (80) function properly, there is a shaft connection zone (81 ) and a shaft connection screw (811 ) to prevent thementioned shaft connection zone (81 ) from coming off and breaking.

• It includes the shaft rotation connection (82), which enables the wing opening shaft (84) to be connected to the shaft connection zone (81), which is necessary for the operation of the wing deployment element (80) and which prevents it from being damaged during the desired rotational movement and enabling the desired rotational movement. . • There is a shaft lower fixing point (83) which is located between the shaft rotary connection (82) and the wing deployment shaft (84) to keep the shaft movement under control.

• In order to enable the mentioned wing opening element (80) to function properly, it includes a shaft fixing foot (85) to ensure that the rotating and sliding shafts stay stationary while moving.

• It includes tail deployment assembly (90) to enable the tail (60) of the unmanned aerial vehicle (I) to be deployed.

• There is a tail opening base element (91 ) to ensure the positioning of the mentioned tail deployment assembly (90).

• There is a tail clamping element (92) in order to connect the tail deployment base element (91 ) and the tail deployment body (93).

• There is a tail deployment hub (94) to enable the tail (60) to be deployed.

• It includes the tail pass gap (95) in which the mentioned tail deployment hub (94) is located.

The elements that make up the invention and their functions to ensure the proper operation of the invention are given above. The structures and detailed working principle of these elements are given below.

In Figure 1 , the view of the propeller (30), tail (60) and wing (20) playing an active role in the operation of the invention is given. As can be seen from Figure 1 , there are propeller blades (301 ) that are symmetrically connected to each other. Mentioned propeller blades (301 ) are connected to the propeller hub (302) which is used to move the propeller (30) and hence the unmanned aerial vehicle (I), by starting to rotate after motor start.

In an alternative application of the invention, the propeller blade (301 ) mentioned is in one piece.

In another alternative application of the invention, mentioned propeller wings (301 ) are used in quantities of two or more to accelerate the unmanned aerial vehicle (I). Again, as can be seen from Figure 1 ,two tail (60) structures which are in the upper part of the propeller (30) are placed symmetrically with each other to maintain the stability of the unmanned aerial vehicle (I) during its flight.

Again as shown in Figure 1 , mentioned unmanned aerial vehicle (I) has at least one ammunition(40) in a ready-to-detonate state, which is attached to its fuselage (10) during flight. Wing (20) and tail (60) which enables flight and maintain stability of the unmanned aerial vehicle (I) are also shown.

In another alternative embodiment of the invention, the mentioned tail (60) mentioned is produced in one piece.

In another alternative embodiment of the invention, the mentioned tail (60) is placed on the unmanned aerial vehicle (I) in two or more parts. It is designed to stabilize the unmanned air vehicle (I) at all flight speeds.

In an alternative application of the invention, the mentioned wings (20) are produced in one piece.

In another alternative embodiment of the invention, the mentioned wing (20) mentioned is produced in two or more pieces.

The spring mechanism which is used to keep the wings (20) at the correct angle and position is given in Figure 1 and 3. The mentioned spring mechanism is positioned to to constantly push the wings (20) away from the fuselage (forward) (10). The spring mechanism is connected to the inside of the wing assembly (201 ) in order to maintain the task attributed to it and to keep it in constant interaction with the wings (20).

After the launch mechanism (F) activates the unmanned aerial vehicle (I), it provides the flight of the mentioned unmanned aerial vehicle (I). The wings (20) in the closed position are deployed by the spring mechanism to ensure that the wings (20) used in order to increase the flight time and to ensure reaching the target (H). Mentioned spring mechanism is in constant contact with the wings (20) and continuously push the wings forward. The spring mechanism continuously applies forward force to the wings (20) in order to prevent the drag force from retracting the wings (20), depending on the speed of the unmanned aerial vehicle (I). The unmanned aerial vehicle (I) is triggered by the launch mechanism (F) and comes to the position where it will fly. Figure 3 shows the unmanned aerial vehicle (I) in the air, after it opens its wings (20) via a spring mechanism, focuses on the target (H) and ready to drop its ammunition(40).

Again, as indicatedin figure 3, aileron (202) structures are attached to the wings (20) to be used in case of a need for higher lift force at low speeds during landing and take-off and provide balance and control around roll axes.

In figure 4, the appearance of the unmanned aerial vehicle (I) during take-off, before its wings (20) are fully deployed, is given. Unmanned aerial vehicle (I) overcomes the drag force of the air and climbs until the desired altitude, using the initial power it receives from the launch mechanism (F) and thrust force created by the propeller (30) which is rotated by a motor. Mentioned unmanned aerial vehicle (I) will continue to climb and gain altitude overcoming the drag force of the air by reducing the surface area before it deploying its wings (20) fully.

Again, as can be seen from figure 4, the wing nest (11 ), which is connected to the fuselage (10) of the mentioned unmanned aerial vehicle (I), keeps the wings (20) inside until the drag force is balanced. Thus, the wing (20) of the unmanned aerial vehicle (I) which is accelerated by the launch mechanism (F) and the propeller (30) is prevented from breaking by avoiding the drag force of air until it takes the ideal flight position. The ammunition(40) of the unmanned aerial vehicle (I) is carried on board the fuselage (10) for defensive and/or offensive purposes and is detonated upon reaching the target (H).

In figure 5, the unmanned aerial vehicle (I) is shown with the wings (20) retracted in the wing nest on the fuselage (10) and the propeller (30) is still. The wings (20) in the mentioned unmanned aerial vehicle (I) are kept inside the wing nest (11 ) in order to be protected from external effects and to prevent them from being damaged. Mentioned wing nests (11 ) are positioned on the fuselage (10) and are supported by the wing assembly (201 ).

In figure 6, the front view of the unmanned aerial vehicle (I) with the deployed wings (20) during flight is given. As can be seen from the figure mentioned, the tails (60) are located symmetrically with each other, helping the unmanned aerial vehicle (I) to stay in balance and in control. The wings (20), on the other hand, are parallel with each other with respect to the fuselage (10) and ensures that the unmanned aerial vehicle (I) executes a straight and smoothflight by providing equivalent lift forces.

The ammunition(40) which is attached to the fuselage (10) for defense and/or offense, .is located at the front in order to ensure that the unmanned aerial vehicle (I) creates maximum damage when exploded.

In figure 8, the view of the mechanism that allows the tails (60) to be deployed when the unmanned aerial vehicle (I) attains the desired altitude and speed is given. The mentioned mechanism, is developed to enable the tails (60) to open after the unmanned aerial vehicle (I) obtains the desired acceleration and leaves the launch mechanism (F) and is connected to the unmanned aerial vehicle (I).

Mentioned wing opening element (80) consists of at least one wing opening element upper body (801 ), at least one wing opening element lateral body (802) and at least 1 wing opening element lower body (803).

Mentioned wing opening element body parts are there to protect the wing opening element (80) from external effects and prevent it from being damaged in any contact. The wing opening element lower body (803) is produced and connected from two symmetrical parts having the same dimensions. There is a mechanism on each part that will trigger each of the wings (20) and the mentioned mechanisms work simultaneously to ensure that the wings (20) are deployed and retracted together. While unmanned aerial vehicle (I) performs its flight, mentioned wing opening element (80) prevents the wings (20) from being closed by the drag force or lose is angle by being in constant contact with the wings (20).

There is a shaft connection zone (81 ) in order to enable thementioned wing opening element (80) to function. Mentioned shaft connection zone (81 ) allows the wing opening element (80) to be fixed from above by means of shaft connection screws (811), and allows rotational and pressing motion. Mentioned shaft connection screws (811) are connected over the shaft connection zone (81) to obtain maximum strength and maximum durability. With the shaft connection zones (81 ), the on-going instantaneous pressing and pushing movements are limited and the wings (20) are prevented from damage by being in contact with the wing opening element (80). . Wing deployment element (80) contains a shaft rotation connection (82) that connects wing deployment shaft (84) with shaft connection zone (81 ), which enables pressing and rotating motions and also prevent damage while doing these motions. Mentioned wing opening shaft (84) prevent the wings (20) from losing its angle and/or being retracted by creating a reaction force against the drag force exerted on the wings (20) by continuously up and down motion.

There is the shaft lower fixing point (83) between the shaft rotary connection (82) and the wings opening shaft (84), which controls the shaft movement . The wings (20) of the unmanned aerial vehicle (I) are deployed ater leaving launch mechanism (F) upon reaching desired position, by movement of the shafts with the force that is created by the triggering of the springs that lie along within the shaft lower fixing point (83) and triggering of the wings (20) by the shafts pressing the springs axially, back and forth

The wing openin element (80) contains shaft fixing feet (85) that keeps the rotating and sliding shafts fixed while in action, in order to perform its function. The wing opening shaft (84), which performs its function between the shaft fixing foot (85) and the shaft connection zone (81 ), makes the pressure necessary for the wings (20) to deploy and not to retract in the deployed position by making pressing and pulling movements.

In Figure 8, the view of the spring mechanism that enables the tails (60) of the unmanned aerial vehicle (I) to be deployed is given. Mentioned tail deployment element (90) is connected to the fuselage (10). It enables the deployment of tails (60) after unmanned aerial vehicle (I) leaves the launch mechanism (F) and upon reaching desired position, by triggering itself with compression-extension motion and transferring the spring force to the tails (60). Mentioned tail deployment assembly (90) is fixed on the fuselage (10) with the tail deployment base element (91), to prevent its damage during the separation of the unmanned aerial vehicle (I) from the launch mechanism (F). Tail clamping element (92) strengthens the connection of the mentioben tail deployment base element (91 ) on the fuselage (10) .and prevents it from breaking, and/or disengaging, under the acceleration and speeds attained by the unmanned aerial vehicle (I). The springs which deploy the tails (60) with the compression force are located inside the tail deployment body (93) within the tail deployment assembly (90). Mentioned tail deployment body (93) is connected to the tail deployment base element (91 ) with the tail clamping element (92). Thus, the tail deployment base element is prevented from disengaging or breaking with any reaction force when the spring gets compressed and move back and forth. There is a tail pass gap (95) inside the mentioned tail deployment assembly (90) to which the tail deployment hub (94) is connected. Mentioned tail deployment hub (94) will enable the connection of the tail deployment assemby (90) to the tails (60). During this connection, it will be ensured that the tail deployment assembly (90) is intertwined with the tails (60) through the tail pass gap(95).

After the mentioned connections, the springs within thetail deployment assembly (90) will continuously exert force on the tails (60) and enable the deployment of tails (60) upon the unmanned aerial vehicle (I) reaching the desired position and altitude.

In Figure 9, the position of the tail deployment assembly (90) between the tails (60) is shown. After the unmanned aerial vehicle (I) is launched, springs located in the tail deployment assembly (90) creates a push force on the tails (60) and the enables the deployment of the tails (60). The tail deployment assembly (90) applies the mentioned push force continuously and does not allow the tails (60) to be retracted back.

Again, in Figure 9, the tail (60) structure with a different design and which is used in an alternative application of the invention is given. There is a tail control surface (601) located on the aforementioned tail (60) structure maintain the pitch and yaw balance and control of the unmanned aerial vehicle (I) during flight.

The representative schematic view of the system is given in Figure 2. As can be seen from the figure in question, the system includes a a launch mechanism (F) that will launch the unmanned aerial vehicle (I), a radar (R) that will provide presence detection in the airspace where the system will be used, an image acquisition element (IA) that will verify the target upon radar (R) target (H) detection and a processing unit (IB) that can communicate with and process data it receives from the mentioned unmanned aerial vehicle (I), launch mechanism (F), image acquisition element (IA), and radar (R).

The working principle of the invention, whose connections and functions are explained in detail above, is as follows:

• In order to enable the unmanned aerial vehicle (I) to take action and perform its mission, the desired target (H) to be reached is detected by radar (R).

• The target (H) detected by the radar (R) is confirmed by the imaging element (IA), and the desired location to be reached by the unmanned aerial vehicle (I) is confirmed.

• To start the flight, the unmanned aerial vehicle (I) is launched by the launch mechanism (F).

• The unmanned aerial vehicle (I) continues its launching path with wings (20) retracted until it reaches the desired altitude, so that the wings (20) are protected from breaking under its acceleration combined with the drag force of the air.

• When the unmanned aerial vehicle (I) reaches the desired altitude, it first opens the tails (60) via the tail deployment assembly (90).

• There are springs in the mentioned tail deployment assembly (90) that prevent the tails (60) from retracting by triggering them continuously and deploy the tails (60) after launch. Mentioned springs are in compressed state right after launch and it is waited until the unmanned aerial vehicle (I) reaches the desired position. When the unmanned aerial vehicle (I) reaches the desired position and altitude, the springs are released, creating deployment force on the tails (60) and the tails (60) deploy simultaneously.

• There is a possibility of slight retraction of tails due to external forces which might result in unmanned aerial vehicle (I) loss of control To prevent this to happen, tails (60) are continuously pushed backwards by the tail deployment assembly (90).

• Following the launchof the unmanned aerial vehicle (I), the wings (20) are deployed simultaneously by means of the wing deployment element (80). Mentioned wings (20) create lift force on the unmanned aerial vehicle (I) to balance its weight and help to perform its flight safely. • Mentioned wing deployment element (80) uses compression force of the spring to create a continuous push effect on the wings (20)to prevent the wings (20) from retracting and to keep the wings (20) open throughout the flight by being in constant contact.

• The spring force that is required to deploy the wings (20) and keep them in deployed state is obtained by the compression created by wing deployment shaft (84) moving between the shaft connection zone (81 ) and shaft fixing feet (85) and transferring this compression force to the springs which in turn continuously pushes the wings (20).

• After the unmanned aerial vehicle (I) is launched, it deploys its tails (60) and wings (20) at the desired position and altitude, continues on its flight path and reaches the predetermined target (H).

• The unmanned aerial vehicle (I) completes its task by detonating the ammunition (40) in its fuselage (10) upon reaching the target (H).

The scope of protection of the invention is specified in the attached claims and cannot be limited to what is described in this detailed description for exemplary purposes. Because it is clear that a person skilled in the art can present similar embodiments in the light of what has been described above without departing from the main theme of the invention.