An unmanned aerial vehicle with explosives

Abstract

It relates to an unmanned aerial vehicle (1) comprising at least one fuselage (10) and for the take off of said fuselage (10); at least one air flow duct (11) provided in the fuselage (10) and at least one propeller (12) for providing air flow in said air flow duct (11) Accordingly; its novelty is that it is characterized by comprising explosives (13) located in at least one area of the fuselage (10) for detonating at the directed target.

Description

[0001] DESCRIPTION

[0002] AN UNMANNED AERIAL VEHICLE WITH EXPLOSIVES

[0003] TECHNICAL FIELD

[0004] The invention relates to an unmanned aerial vehicle comprising at least one fuselage and for the take off of said fuselage; at least one air flow duct provided in the fuselage and at least one propeller for providing air flow in said air flow duct.

[0005] PRIOR ART

[0006] Unmanned aerial vehicles are vehicles that can generally fly by remote control or following a predetermined path, can be produced in different sizes and can be used in many different fields and purposes such as reconnaissance, surveillance, mapping, cargo transportation, and emergency response.

[0007] Another field where unmanned aerial vehicles are used is the defense industry. Unmanned aerial vehicles with advanced technology play an important role in increasing the effectiveness of military operations, ensuring personnel safety, and obtaining strategic information in fields such as reconnaissance, surveillance, and intelligence gathering. Unmanned aerial vehicles can also be used to transport explosives in the defense industry. Accordingly, unmanned aerial vehicles carry explosives and release the carried explosives on attack targets, these explosives are then detonated upon reaching the target.

[0008] The unmanned aerial vehicle can release the carried explosive by passing directly over or near the target; in order for the explosive to fall on the target and achieve the desired effect, the unmanned aerial vehicle must release the explosive with the correct release angle. However, the unmanned aerial vehicle may not release the explosive at a proper release angle due to weather conditions or the location of the target. In addition, the unmanned aerial vehicle is able to drop the carried explosive from high altitude. In this case, the explosive dropping from the air may deviate from the target due to external factors. All these can cause undesirable situations and the target not to be destroyed. Furthermore, the failure of the explosive to reach the target can reduce the attack power and effectiveness against the actual target. All of this can make it difficult to achieve the objectives of the operation.

[0009] As a result, all the above-mentioned problems have made it imperative to make an innovation in the relevant technical field.

[0010] SUMMARY OF THE INVENTION

[0011] The present invention relates to an unmanned aerial vehicle for eliminating the above- mentioned disadvantages and bringing new advantages to the relevant technical field.

[0012] An object of the invention is to introduce an unmanned aerial vehicle with explosives in its fuselage.

[0013] Another object of the invention is to introduce an easily transportable, small-sized unmanned aerial vehicle comprising explosives.

[0014] Another object of the invention is to introduce an unmanned aerial vehicle capable of both destroying hostile targets and performing reconnaissance flights.

[0015] In order to accomplish all the objects mentioned above and to be derived from the detailed description below, the present invention is an unmanned aerial vehicle comprising at least one fuselage and for the take off of said fuselage; at least one air flow duct provided in the fuselage and at least one propeller for providing air flow in said air flow duct. Accordingly, its novelty is that it comprises explosives located in at least one area of the fuselage for detonating at the directed target.

[0016] Another possible embodiment of the invention is characterized in that the explosive comprises at least some active metal substance. Thus, this ensures that the unmanned aerial vehicle has a longer effect range.

[0017] Another possible embodiment of the invention is characterized in that it comprises at least one camera for remote image capturing. Thus, this ensures observation of the flight area. Another possible embodiment of the invention is characterized in that it includes an additional battery to increase the range. Thus, it is possible for the unmanned aerial vehicle to fly for a longer period of time.

[0018] Another possible embodiment of the invention is characterized in that it comprises at least one solar panel for self-charging. Thus, this ensures that the unmanned aerial vehicle is constantly charged.

[0019] Another possible embodiment of the invention is characterized in that said solar panel is located on opposite sides of the fuselage. Thus, the unmanned aerial vehicle is able to charge faster.

[0020] Another possible embodiment of the invention is characterized in that the air flow duct is located in the direction of the extension of a central axis.

[0021] Another possible embodiment of the invention is characterized in that the air flow duct comprises at least one propeller located on the central axis.

[0022] Another possible embodiment of the invention is characterized in that the air flow duct comprises at least one curved form at the inlet of the fuselage, at least one straight form around said propeller, and an inclined form provided at a predetermined angle at the air outlet of the fuselage.

[0023] Another possible embodiment of the invention is characterized in that it comprises at least one steering element provided around the said inclined form to change the direction of movement of the fuselage.

[0024] Another possible embodiment of the invention is characterized in that said steering element for steering the fuselage can be configured to be at least partially movable with respect to the central axis.

[0025] Another possible embodiment of the invention is characterized in that it comprises at least one handle to facilitate transportation of the fuselage. Thus, ease of transportation is ensured. Another possible embodiment of the invention is characterized in that said handle is at least partially curved structure. Thus, this facilitates the attachment of the unmanned aerial vehicle to any location.

[0026] Another possible embodiment of the invention is characterized in that said handle has at least a partially clamped structure.

[0027] Another possible embodiment of the invention is characterized in that it comprises a control unit for remote control.

[0028] Another possible embodiment of the invention is characterized in that said control unit comprises a processor unit.

[0029] Another possible embodiment of the invention is characterized in that the control unit comprises a communication unit associated with said processor unit.

[0030] Another possible embodiment of the invention is characterized in that the control unit comprises a memory unit associated with the processor unit.

[0031] Another possible embodiment of the invention is characterized in that it comprises a user terminal associated with the unmanned aerial vehicle for managing the unmanned aerial vehicle and viewing the images obtained by the unmanned aerial vehicle.

[0032] BRIEF DESCRIPTION OF THE DRAWING

[0033] Fig. 1 shows a representative view of the unmanned aerial vehicle.

[0034] Fig. 2 shows a representative view of the internal structure of the unmanned aerial vehicle.

[0035] Fig. 3 shows a representative view of the solar panel of the unmanned aerial vehicle.

[0036] Fig. 4 shows a representative view of the air flow duct of the unmanned aerial vehicle. Fig. 5 shows a representative view of the partial freedom of rotation of the propellers of the unmanned aerial vehicle relative to the central axis.

[0037] Fig. 6 shows a representative view of the handle structure of the unmanned aerial vehicle.

[0038] Fig. 7 shows a representative view of the operation scenario of the unmanned aerial vehicle.

[0039] Fig. 8 shows a representative view of the steering element structure of the unmanned aerial vehicle.

[0040] Fig. 9 shows another representative view of the steering element structure of the unmanned aerial vehicle.

[0041] Fig. 10 shows a representative view of the air flow duct structure of the unmanned aerial vehicle.

[0042] DETAILED DESCRIPTION OF THE INVENTION

[0043] In this detailed description, the subject of the invention is explained by way of example only for a better understanding of the subject, which shall not create any limiting effect.

[0044] In Fig. 1 , the unmanned aerial vehicle (1 ) of the invention comprises at least one fuselage

[0045] (10). Said fuselage (10) is the main structure on which various components are located. There is at least one air flow duct (11 ) located on the fuselage (10). Said air flow duct

[0046] (11 ) can be configured to allow air to pass through for the take off of the fuselage (10). There is at least one propeller (12) located on the air flow duct (11 ).

[0047] In a possible embodiment of the invention, the air flow duct (11 ) can be configured to comprise at least one propeller (12) located on the central axis (I).

[0048] In a possible embodiment of the invention, there is at least one stator guide vanes on said propeller. By the rotation of the stator guide vane on said propeller (12) about itself, air propulsion in the air flow duct (11 ), and consequently flight, is achieved. Furthermore, since there are inclined stator guide vanes to provide rotational moment under the propeller (12) in the air flow direction and in the opposite direction to the rotation direction of the propeller (1 ) in the air flow direction, the uncontrolled rotation of the unmanned aerial vehicle (1) around itself due to the rotational moment of the single propeller (12) is prevented.

[0049] In another possible embodiment of the invention, the air flow duct (11 ) can be configured to comprise two propellers (12) located on the central axis (I). In a possible embodiment of the invention, the propellers (12) are coaxial counter-rotating propellers. The propellers (12) can rotate in the opposite directions to each other. In addition, the rotation of the propellers (12) in the opposite direction relative to each other prevents the unmanned aerial vehicle (1) from rotating around itself, without the need for stator guide vanes. In addition, any one of the propellers (12) can be configured to rotate slower and the other faster. Thus, the rotation of the unmanned aerial vehicle (1 ) in the desired direction can be adjusted by creating controlled differences between the rotation speeds. In this way, there is no additional part required for the rotation of the unmanned aerial vehicle (1 ) around itself. This allows the weight of the unmanned aerial vehicle (1 ) to be reduced.

[0050] The air flow duct (11) has at least one curved form (II) at the inlet of the fuselage (10), at least one straight form (III) around at least one of the propellers, and an inclined form (IV) provided at a predetermined angle at the air outlet of the fuselage (10). In this way, air entry into and exit out of the air flow duct (11 ) is carried out in a more balanced way. As shown in Fig. 2, it is assumed that the air flow duct (11 ) is located in the direction of the extension of a central axis (I).

[0051] With reference to fig. 10, the air flow duct (11 ) is formed according to the predetermined values of at least one curved form (II), at least one straight form (III), and inclined form (IV). The parameters of the forms of the air flow duct (11 ) are described below.

[0052] The parameters of the air flow duct (11 ) are named as follows. According to the mentioned parameters, the gap diameter parameter is denoted by R; the gap parameter between the propeller tip and the duct wall by L1 ; the air inlet lip radius parameter by r1 ; the air outlet length parameter by L2; and the air outlet angle by A. The characteristic cross-sectional surface form of the air flow duct (11 ) can be 360 degrees of a full circle or smaller angles at the air inlet, as shown in fig. 10. It can also be 45 degrees, which is 1 / 8 of a circle, and its diameter is denoted by r1 . The parameter values of the air flow duct (11 ) can be within the optimal ranges specified below.

[0053] Between propeller tip and duct wall (L1), 0.1 %R < L1< 1 ,6%R

[0054] Air inlet lip radius parameter (r1 ), 6%R < r1 < 13%R

[0055] Air outlet length parameter (L2), 31 %R < L2 < 72%R

[0056] Air outlet angle (A), 0° < A < 20°

[0057] With the air flow duct determined according to these ranges, the propulsion efficiency and energy efficiency of the propellers (12) are increased. Thus, with the same air entry power (with the air flow duct gap), more thrust or thrust can be produced for a longer period of time compared to an open propeller (12) of the same diameter.

[0058] In order to change the direction of movement of the fuselage (10), at least one steering element (18) is provided in the vicinity of the said inclined form (IV). The said steering element (18) can be configured to be at least partially movable with respect to the central axis (I) for steering the fuselage (10). Thus, by moving at a certain angle with respect to the central axis (I), it ensures that the air is directed. The unmanned aerial vehicle (1) is able to move in the determined direction by the directed air.

[0059] In another possible embodiment of the invention with reference to Fig. 8, the steering element (18) is a control surface. Said control surface is able to perform the opening and closing movement by means of an electromagnet. In a possible embodiment of the invention, the control surface is able to perform the opening and closing movement by means of a servo motor. In a possible embodiment of the invention with reference to Fig. 9, the steering element (18) is avionics control blades.

[0060] In a possible embodiment of the invention, the steering element (18) can be configured such that there are at least two located opposite each other. Every two steering elements (18) located together form a pair of steering elements (18). In another possible embodiment of the invention, there is at least one drive element for controlling the movement of the steering element (18). In a possible embodiment of the invention, the drive element is a servo motor.

[0061] In a possible embodiment of the invention, the steering element pair can be configured to be controlled by at least a single servo motor. The steering element pairs are configured to move at a predetermined angle.

[0062] In another possible embodiment of the invention, the fuselage (10) can be configured to comprise four separate steering elements. In a possible embodiment of the invention, the steering element pairs are configured to be steered by two drive elements.

[0063] In a possible embodiment of the invention, said fuselage (10) can be configured to be slightly flattened at the top and bottom and bulging at the sides. In a possible embodiment of the invention, this form is provided in a sphere-like form. The fuselage (10) being provided in this form provides aerodynamic stability, allowing the unmanned aerial vehicle (1 ) to remain in the air more efficiently and stably. Thus, the unmanned aerial vehicle (1 ) is able to perform various flight movements with better maneuverability during flying. Owing to the light weight and small size of the fuselage (10), it is easy to transport the unmanned aerial vehicle (1). Thus, the unmanned aerial vehicle (1) will not be easily hit by hostile missiles, and it will be possible to conduct high or low altitude reconnaissance flights. Furthermore, the fuselage (10) can be easily transported like a grenade and can be sent away when necessary for detonation at a distance. In addition, it is ensured that the unmanned aerial vehicle (1) is prevented from entangling with enemies and obstacles around, or, consequently, the unmanned aerial vehicle (1) from breaking apart.

[0064] With reference to Fig. 2, a possible embodiment of the invention comprises at least one explosive (13) located on the fuselage (10). The explosive (13) provided in the fuselage (10) detonates when the unmanned aerial vehicle (1 ) reaches the hostile target, ensuring the destruction of the target.

[0065] In a possible embodiment of the invention, it is preferred to use TNT-RDX explosive as the mentioned explosive (13). The explosive (13) mentioned in a possible embodiment of the invention is located on at least one side of the fuselage (10).

[0066] In a possible embodiment of the invention, explosives (13) are located around the perimeter of the fuselage (10). In another alternative embodiment of the invention, the explosives (13) are located on at least two sides of the fuselage (10). Thus, it is ensured that the detonation power of explosives (13) is increased. Therefore, when the unmanned aerial vehicle (1 ) reaches the enemy target and detonates, the destruction process is completed with greater impact on the target.

[0067] In another possible embodiment of the invention, the explosive (13) is located around the perimeter, on both sides, or at least on one side of the fuselage (10).

[0068] In a possible embodiment of the invention, the explosive (13) can be evenly distributed in the fuselage (10) so that the unmanned aerial vehicle (1) flies with a balanced load during the flight, further increasing the impact power. The unmanned aerial vehicle (1) is able to accurately reach the target during the flight owing to the balanced load.

[0069] In a possible embodiment of the invention, some active metal substance (131) may be present in the explosive (13). Here, with the active metal substances (131) placed in explosives (13), a longer range and a larger area of impact is provided.

[0070] In a possible embodiment of the invention, the unmanned aerial vehicle (1) comprises at least one camera (14) for capturing images from the environment during flight. With the camera (14), the unmanned aerial vehicle (1) can make observation flights and the images of the areas where it flies over can be obtained. This allows users to defend themselves by detecting their enemies remotely and in advance, since information about the environment can be obtained. In addition, with the users being able to see the surroundings during the flight, the unmanned aerial vehicle (1 ) is prevented from crashing into anything and the accurate steering capability is increased.

[0071] The camera (14) used in a possible embodiment of the invention can be configured to be an infrared camera. With the use of an infrared camera, it can perform effective imaging in dark or low light conditions. Furthermore, it is prevented from being affected by weather conditions such as fog or rain. In a possible embodiment of the invention, the unmanned aerial vehicle (1) can be configured to include one of the camera varieties well-known in the art and the infrared camera. Thus, while the camera (14) provides images under normal conditions during the day, the infrared camera can be used to capture images properly in dark or adverse weather conditions.

[0072] In a possible embodiment of the invention, the unmanned aerial vehicle (1) can be configured to include one of the varieties of cameras (14) well-known in the art, an infrared camera, or any one of the two.

[0073] The unmanned aerial vehicle (1) comprises a battery for flight. In a possible embodiment of the invention, the unmanned aerial vehicle (1) can be configured to comprise at least one additional battery (15) to increase the flight range. With the additional battery (15), it is possible to fly for a longer time. Thus, sudden flight terminations due to battery depletion are prevented in long-term flights.

[0074] In a possible embodiment of the invention, with reference to Fig. 3, the unmanned aerial vehicle (1 ) can be configured to comprise at least one solar panel (16) for self-charging. With the solar panel (16), the unmanned aerial vehicle (1 ) is able to fly in a continuously charged state. In this way, the unmanned aerial vehicle (1 ) is always ready in case of a sudden observation flight or a sudden operation. In a possible embodiment of the invention, solar panels (16) are configured in an openable and closeable (folding) structure depending on the usage situation. Accordingly, when the solar panel (16) is to be used, the solar panels (16) open outwards from both opposite sides of the fuselage (10), similar to a wing structure.

[0075] In a possible embodiment of the invention, the solar panels (16) are located on both opposite sides of the fuselage (10). Owing to this, the unmanned aerial vehicle (1) can charge faster. Furthermore, the solar panels (16) provide load balance for the unmanned aerial vehicle (1 ), ensuring that the flight takes place in a balanced manner.

[0076] With reference to Fig. 4, the present invention can be configured such that the air flow duct (11 ) is located in the extension direction of a central axis (I). In a possible embodiment of the invention, at least one of the propellers (12) can be configured to have partial freedom of rotation with respect to the central axis (I) for steering the fuselage (10). In this way, the unmanned aerial vehicle (1 ) can be moved in the desired direction and orbit. During the flight, if a tree or a foreign object is detected in front of the unmanned aerial vehicle (1 ), the flight can be continued without a collision.

[0077] In another possible embodiment of the invention, all propellers (12) are configured to have partial freedom of rotation with respect to the central axis (I) for steering the fuselage (10). In this way, the turning capability of the unmanned aerial vehicle (1 ) is improved.

[0078] The present invention can be configured to comprise at least one handle (17) to facilitate the transportation of the fuselage (10). Said handle (17) can be configured such that it is embedded in the fuselage (10). In this way, the handle (17) is located inside the fuselage (10) when not in use, while the handle (17) is removed to the outside of the fuselage (10) when the handle (17) is to be used. The unmanned aerial vehicle (1) can be easily transported in this way. It can be transported by being hung on a kit bag or any structure, thus enabling transportation both easily and without expending unmanned aerial vehicle (1 ) power.

[0079] In a possible embodiment of the invention, the said handle (17) can be configured to be at least partially curved structure. A handle (17) with a curved structure facilitates attachment to a kit bag or any structure. The said curved structure is in the form of a hanger / hasp / carabin, allowing the unmanned aerial vehicle (1 ) to easily attach to the structures. The hanger can have a structure that usually has a shape resembling a ring or hook. The open side of the hanger surrounds the structure on which the unmanned aerial vehicle (1) will be hung, thus providing a tight grip. Thus, the unmanned aerial vehicle (1 ) can be transported safely and stably. At the same time, it prevents the unmanned aerial vehicle (1) from slipping or falling during transportation.

[0080] In a possible embodiment of the invention, the handle (17) can be configured to have at least a partially clamped structure. Another alternative embodiment of the invention is that the handle (17) has a curved structure, clamped structure, or at least one of the two. In a possible embodiment of the invention, the unmanned aerial vehicle (1) can be configured to comprise a control unit (20). The control unit (20) comprises a processor unit (21 ) for steering and operating the unmanned aerial vehicle (1 ). The processor unit (21 ) can be configured to receive the directions given by the user and to generate signals that will enable the transmission of the images collected by the unmanned aerial vehicle (1).

[0081] In a possible embodiment of the invention, the control unit (20) comprises a sensor unit

[0082] (23) to collect data belonging to the unmanned aerial vehicle (1). In a possible embodiment of the invention, said sensor unit (23) comprises an optical flux sensor and a distance / proximity sensor to measure the ground clearance of the unmanned aerial vehicle (1 ).

[0083] In a possible embodiment of the invention, the control unit (20) comprises a locating unit

[0084] (24) to determine the location of the unmanned aerial vehicle (1 ). Said locating unit (24) can be configured to include a GPS module. In a possible embodiment of the invention, the control unit (20) comprises a memory unit. The memory unit enables the recording of data from the sensor unit (23) and the locating unit (24).

[0085] In a possible embodiment of the invention, a user terminal (30) associated with the unmanned aerial vehicle (1) is provided in which users can input commands to manage the unmanned aerial vehicle (1) and view the images collected by the unmanned aerial vehicle (1 ). The user terminal (30) can be configured with a user interface to allow command input for users to steer the unmanned aerial vehicle (1 ). Furthermore, the images collected by the unmanned aerial vehicle (1 ) can be visually presented to users by a user interface in the user terminal (30). Accordingly, the unmanned aerial vehicle (1 ) can move in a direction determined by the soldier, and the unmanned aerial vehicle (1 ) can self-detonate according to the command of a soldier.

[0086] In a possible embodiment of the invention, the user terminal (30) can be configured to be a smart watch, portable tablet, or a computer that users can wear on their arms.

[0087] In a possible embodiment of the invention, the control unit (20) comprises a communication unit (22) for communication of the unmanned aerial vehicle (1 ) with the user terminal (30). Data exchange between the communication unit (22) and the user terminal (30) and the unmanned aerial vehicle (1 ) can be one of the well-known wireless communication methods in technology such as Bluetooth, WIFI, and mobile networks.

[0088] An example usage scenario of the invention is as follows;

[0089] Observing and destroying targets with unmanned aerial vehicles is of great importance in the defense industry. For this, the unmanned aerial vehicle (1 ) provided in the spherical form described in the invention is launched into the air by a soldier during an operation or for reconnaissance flights. The unmanned aerial vehicle (1 ), which is launched into the air, is equipped with a camera (14) on its fuselage (10), allowing the soldier to view the images of the environment in which it flies through a smart watch worn on the soldier's arm or a handheld tablet. With the reconnaissance flight, it is possible to acquire information about the environmental conditions and enable accurate military planning. Furthermore, the location of the unmanned aerial vehicle (1 ) can be tracked with the GPS module, therefore the location information of the images obtained can also be accessed.

[0090] In a possible embodiment of the invention, the soldier is able to see an enemy target based on the image information transmitted by the unmanned aerial vehicle (1 ). Accordingly, the soldier can send a command for the unmanned aerial vehicle (1 ) to destroy the enemy target in the image. It is ensured that the commanded unmanned aerial vehicle (1 ) reaches the enemy target and is detonated with one of the well-known grenade detonation methods in the art. Effective destruction of the target is ensured by the explosive (13) substance provided in the fuselage (10) of the unmanned aerial vehicle (1 ) and the active metal substances (131 ) therein.

[0091] In a possible embodiment of the invention, the soldier can put the unmanned aerial vehicle (1 ) in tracking mode with a smart watch worn on their arm or a handheld tablet. The unmanned aerial vehicle (1 ), which is put into tracking mode, monitors the soldier using the unmanned aerial vehicle (1) within a specified area and ensures the safety of the military and other military personnel in the area against any danger.

[0092] In a possible embodiment of the invention, the unmanned aerial vehicle (1) is able to operate with the automatic enemy detection and destruction mode. Accordingly, if any enemy vehicle is detected entering the tracking area by the unmanned aerial vehicle (1 ), the unmanned aerial vehicle (1 ) automatically approaches the enemy vehicle and selfdetonates, ensuring the destruction of the enemy.

[0093] In a possible embodiment of the invention, a large number of unmanned aerial vehicles (1 ) at the time of operation offer the possibility of surveillance of the area and surroundings of military personnel using the hive algorithm, which is an algorithm used to ensure that unmanned aerial vehicles (1 ) very well known in the art automatically follow a circular path around a target or a specific area. The scope of protection of the invention is specified in the appended claims and cannot be limited to what is described for illustrative purposes in this detailed description. It is clear that a person skilled in the art can produce similar embodiments in the light of what is explained above, without deviating from the main theme of the invention.

[0094] REFERENCE NUMERALS GIVEN IN DRAWING

[0095] I Unmanned aerial vehicle

[0096] 10 Fuselage

[0097] I I Air flow duct

[0098] 12 Propeller

[0099] 13 Explosive

[0100] 131 Active metal substance

[0101] 14 Camera

[0102] 15 Additional battery

[0103] 16 Solar panel

[0104] 17 Handle

[0105] 18 Steering element

[0106] 20 Control unit

[0107] 21 Processor unit

[0108] 22 Communication unit

[0109] 23 Sensor unit

[0110] 24 Locating unit

[0111] 30 User terminal

[0112] (I) Central axis

[0113] (II) Curved form

[0114] (III) Straight form

[0115] (IV) Inclined form

[0116] R Air flow duct gap diameter parameter

[0117] L1 Gap parameter between propeller tip and duct wall r1 Air inlet lip radius parameter

[0118] L2 Air outlet length parameter

[0119] A Air outlet angle

Claims

CLAIMS1 . An unmanned aerial vehicle (1) comprising at least one fuselage (10) and for the take off of said fuselage (10); at least one air flow duct (11 ) provided in the fuselage (10) and at least one propeller (12) for providing air flow in said air flow duct (11), characterized in that it comprises an explosive (13) containing at least some active metal substance (131 ) located in at least one area of the fuselage (10) for detonation at the directed target, and at least one steering element (18) provided around the inclined form (IV) for changing the direction of movement of said fuselage (10).

2. An unmanned aerial vehicle (1 ) according to claim 1 , characterized in that it comprises at least one camera (14) for capturing images remotely.

3. An unmanned aerial vehicle (1 ) according to claim 1 , characterized in that it comprises an additional battery (15) to increase the range.

4. An unmanned aerial vehicle (1 ) according to claim 1 , characterized in that it comprises at least one solar panel (16) for self-charging.

5. An unmanned aerial vehicle (1) according to claim 1 , characterized in that said solar panel (16) is located on opposite sides of the fuselage (10).

6. An unmanned aerial vehicle (1) according to claim 1 , characterized in that t e air flow duct (11) is located in the direction of extension of a central axis (I).

7. An unmanned aerial vehicle (1) according to claim 1 , characterized in that the air flow duct (11 ) comprises at least one propeller (12) located on the central axis (I).

8. An unmanned aerial vehicle (1) according to claim 1 , characterized in that the air flow duct (1 1 ) comprises at least one curved form (II) at the inlet of the fuselage (10), at least one straight form (III) around said propeller (12), and an inclined form (IV) provided at a predetermined angle at the air outlet of the fuselage (10).

9. An unmanned aerial vehicle (1) according to claim 1 , characterized in that said steering element (18) for steering the fuselage (10) can be configured to be at least partially movable with respect to the central axis (I).

10. An unmanned aerial vehicle (1 ) according to claim 1 , characterized in that it comprises at least one handle (17) which has at least a partially curved structure and is at least partially clamped to facilitate the transport of the fuselage (10).1 1. An unmanned aerial vehicle (1 ) according to claim 1 , characterized in that it comprises a control unit (20) comprising a processor unit (21 ) for remote control, a communication unit (22) associated with said processor unit (21 ) of said control unit (20), a memory unit associated with said processor unit (21) of said control unit (20), and at least one user terminal (30) associated with the processor unit (21 ) for remote control by at least one user.

Images