Unmanned aerial vehicles, unmanned aerial systems and kits

Abstract

This disclosure relates to an unmanned aerial vehicle (1). The aircraft (1) also comprises at least three rotors (3, 4, 5) and fixed wings (2). The unmanned aerial vehicle can acquire two different flight configurations: a first flight configuration A in which the wings (2) provide lift, and a second flight configuration B in which the rotors (3, 4, 5) provide lift. A kit (11) for providing the UAV (1) is also provided.

Description

Technical Field

[0001] This application relates to an unmanned aerial vehicle (UAV) according to claim 1, an unmanned aerial system (UAS) according to claim 19, and a kit according to claim 20.

Background Art

[0002] Using small UAVs for ammunition dropping in conflict situations is known from the prior art.

[0003] The prior art generally relates to existing drones modified with holders, pedestals, etc. for dropping ammunition such as small firearms.

[0004] For example, document US2022 / 0324561A1 discloses an aircraft that can carry Claymore mines.

[0005] Another document, US11,643,207, discloses an aircraft that enables lift by thrust and lift by wings.

Summary of the Invention

[0006] Still, there is no prior art that provides easy deployment in field operations where the targets are based on both air and ground.

[0007] The above problem is solved by the present invention in providing an unmanned aerial vehicle according to claim 1.

[0008] The advantage of this aircraft is that, after taking off vertically using its configuration, it can change its flight configuration to that of a fixed-wing aircraft, allowing it to travel farther than a quadcopter drone can. By separating at least one rotor in the vertical direction, full vertical takeoff capability and maneuverability are achieved, and the rudder is not involved in flight in flight configuration B. By having at least two booms, the UAV is given an extremely flexible configuration, allowing for a simple and lightweight design. If all or at least some of the rotors are attached to the ends of each boom, a very compact and lightweight solution is achieved. The weapon could be a recoilless weapon. This type of weapon is particularly suitable for the proposed UAV because its flight pattern does not change even when triggered to drop ammunition.

[0009] Further developments would involve the UAV described in claim 2.

[0010] Adding fins allows for more arbitrary control of the UAV.

[0011] Further developments lead to the proposal of the UAV described in claim 3.

[0012] By attaching a boom at a predetermined distance from one side of the wing, space is provided that is particularly useful when all rotors are used for flight, especially in the second configuration B. This is particularly useful when the rudder surfaces are not used for UAV control.

[0013] Further developments will lead to the proposal of the UAV described in claim 4.

[0014] By providing a vertically extending retaining device, a simple and effective solution that provides a predetermined distance is achieved.

[0015] Further developments will lead to the proposal of the UAV described in claim 5.

[0016] By attaching the vertical boom in this way, a good balance is achieved, not only allowing for energy savings in control but also resulting in better control of the vehicle itself.

[0017] Further developments would involve the UAV described in claim 6.

[0018] The advantage is that a symmetrical configuration is achieved for at least four rotors, resulting in a configuration that is very good for controlling the UAV when flying in configuration B.

[0019] Further developments will lead to the proposal of the UAV described in claim 7.

[0020] The inclusion of a mid-section provides flexibility for the UAV. The wing can be constructed as a hemiwing with two wing elements, and electronics and other functional features can be easily integrated into the mid-section instead of the wing. This also makes it possible to install a power supply in the central part of the UAV, which helps maintain the aircraft's balance.

[0021] Further developments would involve the UAV described in claim 8.

[0022] Having two halves as an intermediate section allows for easy loading of cargo onto the UAV. The two halves can be locked together by an enclosed lock. Therefore, it becomes possible to load, for example, weapons, preferably weapons of an elongated shape.

[0023] Further developments will lead to the proposal of the UAV described in claim 9.

[0024] With a navigation camera, the UAV can transmit video footage of the area it is flying over. This simplifies tasks or operators involved in selecting flight paths or other tasks that require operator authorization.

[0025] Further developments will lead to the proposal of the UAV described in claim 10.

[0026] The aiming camera enables real-time video to be delivered to the operator for aiming the mounted weapon. This significantly improves the effectiveness of the weapon and also helps the operator avoid the risk of wasting ammunition when the proposed target no longer requires an attack.

[0027] In a further development, a UAV according to claim 11 is proposed.

[0028] In a particularly advantageous configuration, the UAV has an intermediate part constituted by the weapon itself. This provides a UAV that is not only lighter but also more cost-effective.

[0029] In a further development, a UAV according to claim 12 is proposed.

[0030] By making it possible to change the direction of the weapon, it can be fired and remain effective in both the first and second configurations.

[0031] In a further development, a UAV according to claim 13 is proposed.

[0032] Adopting the UAV as a kit achieves several advantages. In particular, the transportation of the UAV can be significantly improved and the volume of the UAV can be minimized. Therefore, the UAV can be transported by a normal automobile, greatly enhancing the transportation capacity of the UAV.

[0033] In a further development, a UAV according to claim 14 is proposed.

[0034] By adopting auxiliary wings, the UAV can be controlled more efficiently in flight configuration A.

[0035] In a further development, a UAV according to claim 15 is proposed.

[0036] By having its own landing gear, the UAV eliminates the need for auxiliary holders that would otherwise need to be transported to the launch site. Furthermore, by employing a vertical boom as the landing gear, a weight-efficient solution is achieved.

[0037] Further developments will lead to the proposal of the UAV described in claim 16.

[0038] The electric motors are optimally positioned near each rotor. Therefore, the compactness of the UAV is further improved, avoiding the need for longer shafts and other modifications.

[0039] Further developments will lead to the proposal of the UAV described in claim 17.

[0040] Having this capability to control UAVs allows for extremely precise flight.

[0041] Further developments will lead to the proposal of the UAV described in claim 18.

[0042] By equipping UAVs with trigger devices, the need to apply such functionality to the weapon itself is addressed. This increases the versatility of the UAV.

[0043] This disclosure also relates to the unmanned aerial system (UAS) described in claim 19.

[0044] This system incorporates a UAV and remote control, thus creating an effective and compact UAS.

[0045] This disclosure also relates to a kit for providing the UAV described in claim 20.

[0046] The kit is extremely useful when using UAVs in field operations, such as in conflict zones. Furthermore, by allowing the wings and longitudinal boom to be assembled and detached, the kit can achieve an initial configuration and then be disassembled when transportation and subsequent deployment of the UAV are required. Repair and replacement of the wings and longitudinal boom are also significantly easier. The holder boom provides safe rotor operation and allows for a wider control area and greater leverage in control between each rotor.

[0047] This disclosure also relates to the kit described in claim 21.

[0048] The intermediate section allows for a more compact kit, and also enables the housing of control and wireless equipment, as well as a power supply, among other things. The intermediate section may have a volume larger than, for example, the wingspan of the wing.

[0049] This disclosure also relates to a kit for providing the UAV described in claim 22.

[0050] By attaching the motor to the vertical boom, assembly becomes easier, and multiple people can work on assembling the UAV simultaneously, thus speeding up the assembly process.

[0051] This disclosure also relates to a kit for providing the UAV described in claim 23.

[0052] By making the holder boom detachable from the vertical boom, a very compact kit can be achieved.

[0053] This disclosure also relates to a kit for providing the UAV described in claim 24.

[0054] By incorporating a foldable rotor into the kit, it is possible to significantly reduce the kit's size. Furthermore, it is possible to apply a larger rotor without affecting the kit's size, allowing for easy adjustment of the motor and drag selection to suit the kit's UAV flight characteristics. Additionally, selecting a larger rotor can actually reduce noise levels.

[0055] This disclosure also relates to a kit for providing the UAV described in claim 25.

[0056] By using a wing consisting of two wing elements, namely a right wing element and a left wing element, the kit becomes smaller, and if any of the wing elements are damaged, it is easier to replace only a part of the entire wing.

[0057] This disclosure also relates to a kit for providing the UAV described in claim 26.

[0058] The holder allows for the carrying of a payload. A recoilless weapon is generally a tube that is left behind, after which a rocket device leaves the tube behind on a UAV, and the UAV then either flies back or remains at the site.

[0059] This disclosure also relates to a kit for providing the UAV described in claim 27.

[0060] The weapon is held in a fixed position around it. Therefore, it is not intended to deploy the entire weapon described in this particular disclosure.

[0061] This disclosure also relates to a kit for providing the UAV described in claim 28.

[0062] Fins can improve stability in the air. If the fins also function as a rudder, the combination of the rudder and fins can significantly improve maneuverability.

[0063] This disclosure also relates to the kit described in claim 29.

[0064] By adding remote control capabilities to the kit, more precise control of the UAV can be achieved.

[0065] This disclosure also relates to a kit for providing the UAV described in claim 30.

[0066] The coupling device makes UAV assembly extremely easy, allowing it to be carried out even in harsh environments.

[0067] This disclosure also relates to a kit for providing the UAV described in claim 31. [Brief explanation of the drawing]

[0068] [Figure 1] We disclose an unmanned aerial vehicle in accordance with this disclosure in Flight Configuration B. [Figure 2] We disclose an unmanned aerial vehicle in accordance with this disclosure in Flight Configuration A. [Figure 3] We disclose an unmanned aerial vehicle having three rotors in accordance with this disclosure. [Figure 4] We hereby disclose an unmanned aerial vehicle kit in accordance with this disclosure. [Modes for carrying out the invention]

[0069] This disclosure also uses the abbreviation "UAV" to refer to unmanned aerial vehicles. This name clearly indicates that the aircraft is not piloted by an onboard pilot. Instead, the UAV is controlled by an included control unit or a remote operator. Remote control may be performed via a wired or wireless interface. The UAV may be part of an unmanned aerial system that includes remote control. The UAV may preferably be provided as a kit.

[0070] Figure 1 discloses a UAV1 in accordance with this disclosure. Three directions are defined for the UAV1 as shown herein: the longitudinal direction X, the transverse direction Y, and the height direction Z, as shown in Figure 1 and also referenced in Figure 3. The UAV1 also has a defined central axis AA, as shown in Figure 2.

[0071] Figure 1 shows a UAV in the first flight configuration A. This first flight configuration is generally the normal airplane mode, where the UAV flies like a normal airplane. That is, the UAV flies through the air while maintaining longitudinal speed, and its wings generate lift like normal aircraft wings.

[0072] Figure 2 discloses UAV1 in a second flight configuration B. This second flight configuration means that UAV1 can hover and fly like a helicopter. This is also a preferred takeoff configuration because it allows UAV1 to take off from very narrow spaces. Configuration B can also be used for landing.

[0073] UAV1 can independently switch between flight configuration A and flight configuration B. In a typical scenario, UAV1 may take off in flight configuration B, i.e., vertical takeoff, then switch to flight configuration A for long-range transport flights, then change back to flight configuration B for hovering or low-speed flight in a designated area, and then return to its initial position in flight configuration A and land in flight configuration B.

[0074] Referring to Figures 1 and 2, the UAV 1 is provided with a fixed wing 2. The fixed wing 2 is generally a conventional wing without a sweep configuration, and the wing can generate good lift and operate at low speeds. That is, the wing 2 extends mainly in the lateral direction Y, i.e., the wing is preferably a straight wing 2. The wing 2 may be divided into two sections: a right wing element 2a and a left wing element 2b. The wing elements 2a and 2b are assembled together to provide the wing 2. The wing elements can be directly attached to each other to provide the wing 2. Alternatively, the wing 2 may be a single unit, eliminating the need to assemble the right and left wing elements together. The wing 2 is preferably provided with ailerons 12a and 12b. The ailerons 12a and 12b are individually controllable by servos (not shown). The ailerons provide control in the roll plane.

[0075] The UAV is further provided with rotors 3, 4, and 5. That is, UAV1 in Figure 3 can have at least three rotor configurations. A rotor generally refers to a propeller with a fixed pitch. However, a propeller with a variable pitch can also be considered a rotor. The rotors provide vertical control capability when flying in the second configuration B. In this three-rotor configuration, it is preferable to position the third rotor 5 more centrally, thereby achieving a configuration that is closer to an equilateral triangle when the rotors are viewed from the longitudinal direction X, as shown in Figure 3. That is, the first rotor 3 and the second rotor 4 are also positioned on a longitudinal plane located on one side of the wing 2. The third rotor 5 is positioned on the other side of the wing, in the transverse direction Y, between the first rotor and the second rotor. See Figure 3. A four-rotor configuration, i.e., by adding a fourth rotor 6, makes the control of the UAV easier. As shown in Figures 1 and 2, the four-rotor configuration results in a square arrangement in the longitudinal direction, enabling excellent balanced control of the UAV. Furthermore, all rotors can be attached to the wing 2, which simplifies the UAV and eliminates the need to install rotors in the intermediate section 7.

[0076] Rotors 3, 4, 5, and 6 are preferably driven by electric motors 3c, 4c, 5c, and 6c, respectively, preferably brushless motors. The electric motors are driven by a suitable power source such as a battery. The battery can be any suitable form, such as a lithium battery. The battery is preferably incorporated into the blade elements 2a and 2b near the intermediate section 7. The battery may also be incorporated into the intermediate section 7.

[0077] Rotor shafts 3g, 4g, 5g, and 6g are essentially parallel where applicable, meaning the rotors rotate in parallel planes. This makes the UAV1 easier to control. It is also preferable that rotors 3, 4, 5, and 6 rotate in different directions. For example, the motor / rotor torques can be canceled out by having rotors 3 and 5 rotate clockwise and rotors 4 and 5 rotate counterclockwise.

[0078] The first flight configuration A is when UAV1 flies forward using one or more rotors 3, 4, 5, and 6, and utilizes the wings 2 for lift. In this configuration, the energy consumption of UAV1 can be significantly reduced. It should also be noted that in configuration A only, the UAV is intended to be driven by the same rotors 3, 4, 5, and 6 used in configuration B. Therefore, no additional rotors are required to switch between configuration A and configuration B. Furthermore, the speed of UAV1 can be improved compared to UAV1 that uses only rotors for flight and does not have other lift / control surfaces. Control of UAV1 is performed by operating ailerons 12a and 12b, as well as rudders 3e, 4e, and 5e.

[0079] The second flight configuration B is when UAV1 is flying using only its rotors. Wings 2 are not used to provide lift. In this configuration, the rotors provide lift. This means that precise flight in place is possible. UAV1 can hover in place or leave its position and stop in the air. Control of UAV1 is achieved by individually adjusting the rotation speed of each rotor.

[0080] UAV1 may be equipped with at least two longitudinal booms 3a, 4a, 5a, and / or 6a. A preferred configuration is to have one longitudinal boom for each rotor provided on UAV1. The longitudinal booms are intended to extend primarily in the longitudinal direction X. The longitudinal booms may be made of resin or a light metal material such as aluminum. The longitudinal booms 3a, 4a, 5a may be detachably attached to UAV1. The longitudinal booms 3a, 4a, 5a, 6a hold rotors 3, 4, 5, and 6. The rotors are preferably attached to the ends of the longitudinal booms. The extensions of the longitudinal booms may be used as landing gear 3f, 4f, 5f, 6f; that is, the ends opposite to the ends that hold the respective rotors. The landing gear preferably allows UAV1 to stand on its own on the ground, which is essentially the same as when UAV1 is flying in the second flight configuration B. There may be three, four, or more longitudinal booms. In a preferred configuration, there are four longitudinal booms 3a, 4a, 5a, and 6a, as seen in Figures 1 and 2. Further longitudinal booms 5a and 6a should be configured as the first and second longitudinal booms 3a and 4a.

[0081] At least two longitudinal booms 3a, 4a can be attached to the UAV1 at a predetermined distance from the same side of the wing 2. This is preferably achieved using retaining devices that extend in the height direction. If additional longitudinal booms are added, further retaining devices are added for each longitudinal boom 5a, 6a. It is optimal to have holder booms 3b, 4b, 5b, 6b, as can be shown in Figures 1 to 4. By adding retaining devices to the UAV1, it is easily achieved to separate the rotor from the wing and the UAV1 as a whole.

[0082] The holding device, such as the holding boom, can also be mounted entirely to the midsection rather than the blade. Therefore, the configuration shown in Figure 3 and the configuration of Group 5 are described herein. This means that the rotor 5, which faces downward in Figure 3, has a corresponding rotor mounted on the opposite side of the midsection 7, but is mounted at an angle to each other to avoid interference. Thus, for example, the holder devices 3b and 4b extend and are fixed to the midsection 7, so the angle between them is 120 degrees. In configurations with more modes, such as four motors, the angle between each holder boom is 90 degrees.

[0083] UAVs also have holders for tubular cargo. These holders may be structural components of the UAV or they may be detachable holders themselves. If a holder is a structural component of the UAV, it is defined as being integrated into the UAV.

[0084] Therefore, an unmanned aerial vehicle (UAV) 1 is disclosed having a longitudinal extension X, a lateral extension Y perpendicular to the longitudinal extension, and a vertical extension Z perpendicular to both the longitudinal X and lateral Y directions, and the UAV 1 is, A fixed wing 2, comprising a wing 2 that mainly extends in the lateral direction, It is equipped with two power rotors 3 and 4 for providing longitudinal thrust, The unmanned aerial vehicle 1 further comprises at least one additional power rotor 5 to also provide thrust in the longitudinal direction X, The power rotors 3, 4, and 5 are mounted on the UAV1 in such a configuration that, when viewed from the longitudinal direction X, at least one rotor 5 is separated from the other rotors 3 and 4 in the height direction Z, and at least two rotors 3 and 4 are separated in the lateral direction. The rotor axes 3g, 4g, and 5g of all three rotors 3, 4, and 5 are essentially parallel. The unmanned aerial vehicle 1 can achieve a first flight configuration A for conventional flight in which lift is mainly generated by the wings 2, and a second flight configuration B in which lift is mainly achieved by the rotors 3, 4, and 5. The same rotors 3, 4, and 5 are used for both the first flight configuration A and the second flight configuration B.

[0085] Therefore, this disclosure can be combined with any features of the disclosed UAV and / or kit for providing the UAV.

[0086] The UAV1 preferably comprises one or more fins 3d, 4d, 5d, and 6d. The fins are used to provide flight stability in a first configuration A of flight. The fins 3d, 4d, 5d, and 6d preferably have controllable rudders 3e, 4e, 5e, and 6e, which control the yaw and pitch angles when flying in the first configuration. The fins 3d, 4d, 5d, and 6d preferably have angles with respect to the lateral Y and vertical Z directions. This also allows for input in both the vertical and roll directions as needed. This also makes it possible not to add ailerons to the UAV1.

[0087] The UAV1 may have an intermediate section 7 as shown in Figures 1 to 4. The intermediate section 7 may be configured so that the wings 2 can be detachably attached to the intermediate section 7. The wings 2 are attached to the intermediate section 7 together with the right wing element 2a and the left wing element 2b. The intermediate section 7 preferably has a longitudinal extension so that it can support the wings 2 over the entire chord length. Furthermore, by extending outward along the chord length of the wings, the weight can be adjusted by changing the position of the intermediate section in the longitudinal direction X, thus improving the overall balance of the UAV1. The intermediate section 7 preferably includes couplers 22 for attaching the wings 2, more precisely the wing elements 2a and 2b. The couplers 22 are of a type such that each wing element 2a and 2b can be attached to both couplers 22 on either side of the intermediate section 7. However, it is clear that the intermediate section may have couplers for attaching the complete wing 2 instead of the two wing elements.

[0088] The intermediate section 7 can be configured to accommodate a load 13. The load 13 may be a pipe-shaped load 13. However, the UAV 1 can carry any other load, such as cameras, rescue equipment, food packages, or medical supplies. The pipe-shaped load could be a weapon. The most preferred weapon is a recoilless weapon 13. A recoilless weapon does not affect the flight of the UAV 1 when ammunition is dropped. The UAV 1 does not require any modifications to deal with any recoil. Of course, the weapon 7 could be an automatic pistol or a rifle. Also, since the coupling 23 of the intermediate section is of the same type on both sides of the UAV 1, the pipe-shaped load can be oriented in both directions in the longitudinal direction X. Therefore, if the first wing element 2a is attached to the first coupling 22 (not shown) in Figure 4, it can also be attached to the second coupling 22 on the opposite side, thereby allowing the pipe-shaped load to be oriented in the opposite direction.

[0089] The intermediate section 7 is preferably molded on the inside to match the shape of the cargo to be loaded. Therefore, the intermediate section 7 may have an interior molded to fit the aforementioned recoilless weapon 13, achieving a very good fit.

[0090] The intermediate section 7 may consist of two halves that are fixed together. In particular, this configuration allows for easy attachment of tubular cargo, such as a recoilless rifle 13, for example, a Carl Gustaf recoilless rifle, to the UAV 1. For this purpose, the intermediate section 7 may be provided with assembly means 20, such as snap fasteners or eccentric locks.

[0091] While the two-part configuration of the intermediate section 7 is a preferred modification, it should also be understood that a band may be present to form the lower part of the intermediate section. In this case, the band is used to secure the cargo.

[0092] A navigation camera 18 is optionally provided in the intermediate section 7. The navigation camera 18 is generally mounted in the intermediate section of the gimbal and can rotate 360° in a horizontal plane, i.e., a plane including the vertical X and horizontal Y directions, and can rotate at least 180° in a plane parallel to the height Z direction.

[0093] An optional aiming camera 19 is provided in the mid-section 7. The aiming camera 19 views the direction of the weapon 13 mounted by the mid-section 7 at a narrow angle. The aiming camera 19 is calibrated with a sight 17 on the weapon 13 so that the camera can be used for remote aiming. The aiming camera 19 is positioned and configured to always aim in the direction of ammunition drop. If the UAV 1 is configured to drop ammunition forward or backward, the aiming camera may be positioned and configured to transmit images in the intended direction of ammunition drop. This can be positioned and configured in several different ways; for example, the aiming camera can be moved on the mid-section 7 to view the rear direction as needed, rather than the forward direction disclosed in Figure 1. A more preferred method is to rotate the entire mid-section 7 180 degrees so that the aiming camera 19 follows the rotation and obtains a rear view instead of a forward view.

[0094] Alternatively, the intermediate section 7 itself can serve as a weapon. The wing 2, equipped with a longitudinal boom, can be directly attached to the weapon housing 13a. A preferred configuration is one in which all rotors are attached to the wing, so that the only attachment points to the weapon are the attachment points to the wing. If the wing 2 is composed of two separate wing elements 2a and 2b, simple attachment to the weapon can be achieved, for example, by a strap.

[0095] The weapon can be mounted longitudinally on both sides of the UAV1, allowing it to drop ammunition while hovering when flying in configuration B, which is essentially a downward vertical launch. When flying in configuration A, the UAV1 can drop ammunition within its flight line, thereby attacking other targets such as aerial targets. Variations of these two attack patterns can be achieved by changing the orientation of the mid-section 7 on the UAV1. Therefore, the wing 2 should be attachable to either side of the mid-section 7, thereby changing the ammunition drop direction by 180 degrees.

[0096] The UAV1 preferably includes a trigger device 16 that allows the onboard weapon 13 to be fired remotely. The trigger device 16 may be software acting on a local control unit within the weapon. The trigger device 16 may also be a servo that mechanically acts on the weapon's original trigger.

[0097] A preferred attack pattern would involve UAV1 being equipped with a recoilless weapon and firing the ammunition towards the rear as shown in Figure 2. This would allow UAV1 to start vertically in flight configuration B and then fly towards the target in flight configuration A. For example, against a target such as a tank, UAV1 would switch to flight configuration B, hover above the tank, and fire the recoilless weapon vertically downwards towards the tank.

[0098] If the above attack patterns are not used, a recoilless weapon can be mounted as shown in Figure 2. In this configuration, after UAV1 takes off in flight configuration B, it can continue flying in flight configuration A at a much higher speed than is possible in flight configuration B. Therefore, it becomes possible to attack, for example, a helicopter, by firing a recoilless weapon in the direction ahead of UAV1's flight path.

[0099] The UAV1 is preferably a kit 11 with separate elements, as shown in Figure 4. The kit 11 may include a right wing element 2a and a left wing element 2b, but may also include a whole wing 2 as an alternative. The longitudinal booms 3a, 4a, 5a, and 6a, including the motors for the rotors, are separated from the wing 2 or wing elements. The rotors 3, 4, 5, and 6 are also separable from the motors, which makes the kit 11 very compact. The holding device may also be separable from the longitudinal booms. If an intermediate section 7 is included, the intermediate section may be separable from the other elements. However, the wing elements may be changed to a complete monowing.

[0100] Kit 11 is configured to be assembled without tools, and it is desirable that all control surfaces and electric motor electrical contacts be waterproof so that UAV1 can operate in rainy conditions and harsh environments. This applies to all considered variations of the UAV above, meaning that UAV1 has the necessary gaskets and materials to cope with any wet environment and may have protection ratings of, for example, IP64, IP65, 66, 67, IP68, or in extreme cases, IP69K. Kit 11 will be described further below.

[0101] A preferred kit 11 for providing an unmanned aerial vehicle 1 is disclosed in Figure 4, as previously mentioned. Kit 11 includes the components already described above. Specifically, the kit includes an intermediate section 7, longitudinal booms 3a, 4a, 5a, 6a, and foldable rotors 3, 4, 5, 6. Motors 3c, 4c, 5c, 6c are also included. As shown in Figure 4, the rotors and motors are mounted on holder booms 3b, 4b, 5b, 6b. The rotors are preferably foldable, which allows the kit to be stored in a small volume. Couplers 21, 22, 23, 24 are also included. The couplers are designed to be used without tools. For example, there may be a cone surrounded by a threaded ring. The threaded ring acts as a thread to surround the cone, reducing its diameter when the ring is tightened. This allows for a very strong attachment, for example, by inserting the connection 25 of the holder boom 6b into the connection 23 of the wing element 2b and tightening the ring. However, this type of connection is not unique; for example, a spring-operated click-in attachment could be considered for the ultra-fast deployment of the UAV1. This click-in attachment could function in a similar manner to buckle-type side-release buckles.

[0102] Figure 4 discloses four motors, four rotors, four longitudinal booms, and four holder booms, but it should be understood that different numbers of these components are also possible. The UAV disclosed in Figure 3 can also be considered as Kit 11. In addition to mounting the motors and rotors via holder devices on the wings, they can also be directly mounted to the intermediate section, such as rotor 5, longitudinal boom 5a, motor 5c, and holder boom 5b, as shown in Figure 3. In this case, the holder booms may not be parallel to the Z direction in Figure 3.

[0103] The UAV1 preferably includes a control unit 15. The control unit 15 is primarily intended to control the rotor and flight plane so that the UAV can be easily flown by the operator. However, if the operator provides control data to control the UAV1 via remote control 14, the control unit 15 only needs to have communication capabilities. The control unit 15 is preferably installed in an optional intermediate unit 7. This provides simple maintenance and operation and can also be used as the central position of the UAV or as part of a kit providing the UAV.

[0104] The vertical boom and holder boom are preferably made from lightweight materials such as carbon fiber.

Claims

1. An unmanned aerial vehicle (UAV) (1) having a vertical extension (X), a horizontal extension (Y) perpendicular to the vertical extension, and a vertical extension (Z) perpendicular to both the vertical (X) and horizontal (Y) directions, A fixed wing (2), comprising a wing (2) that mainly extends in the lateral direction, Two power rotors (3, 4) for providing the aforementioned thrust in the longitudinal direction, The system comprises at least one further power rotor (5) for providing thrust in the longitudinal direction (X), The power rotors (3, 4, 5) are mounted on the UAV (1) in such a configuration that, when viewed from the vertical direction (X), at least one rotor (5) is separated from the other rotors (3, 4) in the height direction (Z), and at least two rotors (3, 4) are separated in the lateral direction. The rotor axes (3g, 4g, 5g) of all three rotors (3, 4, 5) are essentially parallel. The unmanned aerial vehicle (1) can achieve a first flight configuration (A) for conventional flight in which lift is mainly generated by the wings (2), and a second flight configuration (B) in which lift is mainly achieved by the rotors (3, 4, 5). The same rotors (3, 4, 5) are used for both the first flight configuration (A) and the second flight configuration (B). The unmanned aerial vehicle (1) further comprises at least two longitudinal booms (3a, 4a, 5a) that extend mainly in the longitudinal direction (X), The at least two vertical booms (3a, 4a, 5a) are detachably attached to the unmanned aerial vehicle. At least two of the power rotors (3, 4, 5) are attached to the ends of the respective longitudinal booms (3a, 4a, 5a), preferably the two longitudinal booms are attached to the blade (2), At least two of the power rotors (3, 4, 5) are attached to the ends of each of the vertical booms (3a, 4a, 5a), The UAV is equipped with a holder for pipe-shaped cargo, preferably the pipe-shaped cargo is equipped with a weapon, preferably the pipe-shaped cargo is equipped with a recoilless weapon. An unmanned aerial vehicle (1) characterized by the following:

2. Each vertical boom (3a, 4a, 5a) is equipped with one or more fins (3d, 4d, 5d), Preferably, the configuration of one or more fins (3d, 4d, 5d) is angled such that the fins (3d, 4d, 5d) extend in both the lateral and height directions. The unmanned aircraft (1) according to claim 1, optionally comprising one or more fins that are rudders (3e, 4e, 5e) for controlling the unmanned aircraft (1) in yaw angle and / or pitch and / or roll when flying in the first configuration (A).

3. The at least two of the vertical booms (3a, 4a) are attached to the unmanned aerial vehicle (1) at a predetermined distance from one side of the wing (2). One of the horizontal booms (5a) is attached to the unmanned aircraft at a predetermined distance from the other side of the wing (2). The predetermined distance is the distance over which each of the rotors (3, 4, 5) can rotate freely, according to claim 1 or 2 (unmanned aerial vehicle (1)).

4. The attachment of the at least two of the vertical booms (3a, 4a) is achieved by the respective holding devices (3b, 4b, 5b, 6b) that extend in the height direction or both the height direction and the lateral direction. Preferably, the holding device is in the form of holder booms (3b, 4b, 5b, 6b) that extend in the height direction to which at least two of the vertical booms (3a, 4a, 5a, 6a) are attached, the unmanned aerial vehicle (1) according to any one of claims 1 to 3.

5. The unmanned aerial vehicle (1) according to claim 3 or 4, wherein the at least two longitudinal booms (3b, 4b) attached at a predetermined distance from the same side of the wing (2) are attached to both sides of the line of symmetry (AA) of the wing (2).

6. The aforementioned unmanned aerial vehicle (1) is equipped with third and fourth vertical booms (5a, 6a), The third rotor (5) is attached to one of these vertical booms (5a), The fourth rotor (6) is attached to the fourth vertical boom (6a), All rotors (3, 4, 5, 6) are attached near one end of each of the aforementioned vertical booms (5a, 6a). All provided vertical booms (3a, 4a, 5a, 6a) are positioned at a predetermined distance from the wings (2) and attached to holding devices (3b, 4b, 5b, 6b), preferably taking the form of a holding boom (5b) that extends in the height direction (Z) and / or both the height direction (Z) and the lateral direction (Y). The preferred configuration of the horizontal booms (3a, 4a, 5a, 6a) is such that two vertical booms (3a, 4a) are attached to one side of the wing (2) in the height direction (Z), and two of the vertical booms (5a, 6a) are attached to the opposite side of the wing (2). An unmanned aerial vehicle (1) according to any one of claims 1 to 5, wherein each rotor (3, 4, 5, 6) is separated from another rotor (3, 4, 5, 6) in either the height direction (Z) or the lateral direction.

7. The fixed wings (2a, 2b) further include an intermediate section (7) to which they are detachably attached. Preferably, the wing 2 is separable into a left wing element (2a) and a right wing element (2b), Preferably, the intermediate portion (7) extends longer in the longitudinal direction than in the lateral and / or vertical direction, according to any one of claims 1 to 6, the unmanned aerial vehicle (1).

8. The intermediate section (7) is equipped with the holder and is therefore configured to carry the pipe-shaped cargo (13). Preferably, the intermediate portion (7) can be opened into two halves (7a, 7b), The pipe-shaped cargo (13) is surrounded when the two halves (14a, 14b) are attached to each other after the pipe-shaped cargo (13) is positioned within the intermediate portion (7), as described in claim 7.

9. The aforementioned unmanned aerial vehicle (1) is equipped with a navigation camera (18) and / or a targeting camera (19), Preferably, both the navigation camera (18) and the aiming camera (19) are provided in the intermediate portion (7) of the unmanned aerial vehicle (1) according to any one of claims 1 to 8.

10. The unmanned aerial vehicle (1) according to claim 9, wherein the targeting camera (19) is positioned to look in the same direction as the mounted weapon (13) drops ammunition.

11. The intermediate portion (7) is composed of a weapon (13), and therefore the weapon constitutes both the intermediate portion (7) and the holder of the weapon, preferably a recoilless weapon. The unmanned aerial vehicle (1) according to any one of claims 7 to 10, wherein the unmanned aerial vehicle (1) is assembled to the weapon (13) by attaching the wings (2) to the weapon (13).

12. The attached or incorporated weapon (13) may drop ammunition in a first predetermined direction parallel to the longitudinal direction (X), The aforementioned recoilless weapon (13) may be alternatively mounted in a second predetermined opposite direction parallel to the longitudinal direction (X), The first predetermined direction is defined as the forward direction when flying in the first configuration (A), The unmanned aircraft (1) according to any one of claims 7 to 11, wherein the second predetermined direction is defined as the rear direction when flying in the first configuration (A).

13. The aforementioned unmanned aerial vehicle (1) is arranged and configured so that it can be transported in a disassembled state as a kit (11). Preferably, the disassembled state includes a wing (2), preferably a right wing element (2a) and a left wing element (2b), at least three longitudinal booms (3, 4, 5, 6) to which each rotor (3, 4, 5, 6) is optionally separated, and an intermediate section (7) to which the wing (2) is optionally also attached, according to any one of claims 1 to 12.

14. The unmanned aerial vehicle (1) according to any one of claims 1 to 13, wherein the wing (2) is provided with auxiliary wings (12a, 12b) for controlling the roll axis direction when flying in the first configuration.

15. The aforementioned unmanned aerial vehicle (1) is configured to be equipped with fixed landing gear (3f, 4f, 5f, 6f), Preferably, the landing gear is arranged so that the longitudinal direction of the unmanned aerial vehicle (1) is oriented vertically. Preferably, the landing device is formed by one end of the provided vertical boom, the unmanned aerial vehicle (1) according to any one of claims 1 to 14.

16. Each rotor (3, 4, 5, 6) is driven by a dedicated electric motor (3c, 4c, 5c, 6c), Preferably, the motor is positioned near the rotor end of each of the vertical booms (3a, 4a, 5a, 6a), according to any one of claims 1 to 15 (1).

17. The unmanned aerial vehicle (1) is further provided with a control unit (15) configured to individually control the rotors (3, 4, 5, 6) of the unmanned aerial vehicle (1), The unmanned aircraft (1) according to any one of claims 1 to 16, wherein the control unit (15) is configured to receive instructions regarding the flight pattern by uploading instructions for the flight pattern to the memory of the control unit (15), and / or by receiving instructions from a remote control device (14) configured to communicate with the unmanned aircraft (1) located away from the unmanned aircraft (1).

18. The unmanned aerial vehicle (1) according to any one of claims 1 to 17, further comprising a trigger device (16) which can trigger the control unit (15) and / or a weapon (13) equipped with remote control (14).

19. An unmanned aerial vehicle system comprising an unmanned aerial vehicle (1) according to any one of claims 1 to 18, The unmanned aerial vehicle (1) is an unmanned aerial vehicle system further comprising remote control (14) for controlling the unmanned aerial vehicle (1).

20. A kit (11) for providing an unmanned aerial vehicle (1), comprising a wing (2), at least three longitudinal booms (3a, 4a, 5a), at least three rotors (3, 4, 5), motors (3c, 4c, 5c) for each rotor (3, 4, 5, 6), and holder booms (3b, 4b, 5b) for each longitudinal boom (3b, 4b, 5b), The wings (2) and the holder booms (3b, 4b, 5b) are attached to each other directly or indirectly, preferably indirectly via the intermediate portion (7). The holder booms (3b, 4b, 5b) are detachably attached to the vertical booms (3a, 4a, 5a), in a kit (11).

21. The kit (11) according to claim 20, further comprising an intermediate section (7) to which the wing (2) is attached.

22. The kit (11) according to claim 20 or 21, wherein at least one motor, preferably all of the motors (3c, 4c, 5c, 6c), is attached to one end of the corresponding vertical boom (3a, 4a, 5a, 6a).

23. The holder booms (3b, 4b, 5b) are detachably attached to either the wing (2) or the intermediate section (7). The kit (11) according to claim 20, 21, or 22, wherein, during assembly, each vertical boom is separated in either the horizontal direction (Y), the height direction (Z), or both directions (Y, Z).

24. The kit (11) according to any one of claims 20 to 23, wherein the rotor is a foldable rotor.

25. The kit (11) according to any one of claims 20 to 24, wherein the wing (2) is composed of two wing elements (2a, 2b) that are detachably attached to each other directly or via an intermediate portion (7).

26. The UAV (1) is equipped with a holder for pipe-shaped cargo, preferably for a recoilless weapon, Preferably, the holder is integrated into the intermediate portion (7) or configured as a holder under the wing (2), and / or the holder is configured as a structural component of the UAV (1), according to any one of claims 20 to 25, kit (11).

27. The holder is positioned to surround the recoilless weapon in a configuration in which it is fixedly attached. The kit (11) according to claim 26, wherein the recoilless weapon is detachable only when the UAV is not in flight.

28. A kit (11) according to any one of claims 20 to 27, further comprising at least one fin (3d, 4d, 5d, 6d, 7d), preferably attached to one end of at least one longitudinal boom.

29. The kit (11) according to any one of claims 20 to 28, further comprising a remote control (14) configured to control the UAV assembled from the kit (11).

30. The kit comprises a coupler (21) on the wing and a coupler in the intermediate section, and couplers (23) on the upper and lower surfaces of the wing (2) for attaching at least a group of holder booms to a coupler (25) at the first end of the holder boom. Preferably, the kit (11) according to any one of claims 20 to 29, comprising a coupler (24) on the vertical boom (3a, 4a, 5a, 6a) for attachment to a coupler (26) at the second end of the holder boom (3b, 4b, 5b, 6b).

31. A kit (11) according to any one of claims 20 to 30, wherein the UAV provided is the UAV according to any one of claims 1 to 18.

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