SE2350595A1

SE2350595A1 - Unmanned aerial vehicle, unmanned aerial system, and a kit

Info

Publication number: SE2350595A1
Application number: SE2350595A
Authority: SE
Inventors: Anders Ljung
Original assignee: Acc Innovation Ab
Priority date: 2023-05-16
Filing date: 2023-05-16
Publication date: 2024-11-17
Also published as: WO2024237848A1

Abstract

The present disclosure is related to an unmanned aerial vehicle 1. The vehicle 1, comprises at least three rotors 3, 4, 5, and also a fixed wing 2. The unmanned aerial vehicle may attain two different flying configurations, the first flying configuration A where the wing 2 provides the lift, and a second flying configuration B where the rotors 3, 4, 5 provide the lift.

Description

The present application is related to an un manned aerial vehicle (UAV) according to claim 1, and an unmanned aerial system (UAS) according to claim 20, and a kit according to claim 21.

BACKGROUND There is know from the prior art to use smaller UAV's for delivering munition in a conflict situation.

The prior art is in general related to existing drones which is modified by holders, seats etc. for carrying a munition, such as hand rifles.

For example the document US 2022/0324561 A1 discloses an aerial vehicle that may carry a Claymore mine.

Still there are no prior art that provides for an easy deployment in field operations where the targets are both areal and ground based.

SHORT DESCRIPTION OF THE INVENTION The above problem is solved by the present invention in providing an unmanned aerial vehicle according to claim 1.

The advantage of this vehicle is that it may use its configuration to take off vertically, then change flight configuration to a fixed Wing aerial vehicle and transition much further than any quadcopter drone would be capable of. And by having a separation in height direction of at least one rotor, full vertical take-off capability and manoeuvring may be achieved, no rudders is involved in flying in flying configuration B. ln a further development an UAV according to claim 2 is proposed.

By comprising at least two booms the UAV is provided with a very flexible configuration which allows for easy and light design. lf all or at least some ofthe rotors are attached to an end of a respective boom a very compact and light solution is achieved. ln a further development an UAV according to claim 3 is proposed. BY adding fins a more optional control ofthe UAV is achieved. ln a further development an UAV according to claim 4 is proposed.

By attaching the booms at a predetermined distance from one side ofthe wing there is provided space that helps when using all rotors for flying in particular in the second configuration B. ln particular where any rudder surface is not used for controlling the UAV.

Inkom till Patent- och registreringsverket 2023 -05- 1 6 ln a further development an UAV according to claim 5 is proposed.

By providing a holding device extending in vertical direction, a simple and effective solution to providing the predetermined distance is achieved. ln a further development an UAV according to claim 6 is proposed.

By attaching the longitudinal booms in this way a good balance is achieved which allows for saving energy for control, and also better control in itself is achieved. ln a further development an UAV according to claim 7 is proposed.

The advantage is that a symmetrical configuration is achieved for at least four rotors, which gives a very good configuration to control the UAV when flying in configuration B. ln a further development an UAV according to claim 8 is proposed.

By applying a midsection, a flexibility to the UAV is achieved. The wing can be constituted of two wing halves and electronics and other functional features, may be incorporated in the midsection easily, instead of for example the wing. This also provided for having a power source installed in the UAV at a central portion of the UAV, which helps keeping the vehicle balanced. ln a further development an UAV according to claim 9 is proposed.

By having two halves as the midsection, cargo may easily be employed to the UAV. The two halves may be locked together by means of comprised locks. Thus, making it possible to carry for example a weapon, preferably with an elongated shape. The weapon may be a recoilless weapon. ln particular this type of weapon is suitable for the proposed UAV, as the flight pattern will not change if the weapon is triggered to deliver munition. ln a further development an UAV according to claim 10 is proposed.

With a navigation camera it is possible to as the UAV is Operating send video of the area the UAV is flying over. This simplifies the task or an operator that may be involved in choosing flight path and other tasks that may require permission from the operator. ln a further development an UAV according to claim 11 is proposed.

The aiming camera makes it possible to deliver real time video to the operator for aiming a carried weapon. This highly increases the effectivity ofthe weapon and also helps the operator to avoid risking to waste the munition if a proposed target is no longer needing engagement etc. ln a further development an UAV according to claim 12 is proposed. lnkorn till Patent- och registreringsverket 2023 -05- l 6 ln a particularly advantageous configuration the UAV has a midsection which is constituted by the weapon itself. This provides for a lighter UAV, but also a more cost effective. ln further development an UAV according to claim 13 is proposed.

By being able to alter direction ofthe weapon it may be fired in both the first configuration and the second configuration, and still be effective. ln a further development an UAV according to claim 14 is proposed.

By employing the UAV as a kit several advantages is achieved. ln particular the transport of the UAV, may be significantly improved, and the volume of the UAV is reduced to the minimum. Thus, the UAV may be transported in a normal car, which greatly improves the ability transport the UAV. ln a further development an UAV according to claim 15 is proposed.

By employing ailerons the UAV may be controlled more efficiently in flying configuration A. ln a further development an UAV according to claim 16 is proposed.

By having a landing gear of its own the UAV will not require any auxiliary holders that would be needed to be transported to the launch site of the UAV. ln a further development an UAV according to claim 17 is proposed.

Electric motors is best positioned close to the respective rotor. Thus, the compactness of the UAV is further improved, for avoiding longer shafts etc. ln a further development an UAV according to claim 18 is proposed. By having this ability to control the UAV very precise flying is achieved ln a further development an UAV according to claim 19 is proposed.

By having a trigger device on the UAV, the need that the weapon itself to apply such a feature is dealt with. This makes the UAV more versatile.

The disclosure is also related to an unmanned aerial system UAS, according to claim 20.

The system comprises the UAV and the remote control and thus makes up an effective and small UAS. The disclosure is also related to a kit for providing an UAV according to claim 21.

The kit is very convenient when using the UAV in field operation, for example in a conflict situation. lnkom till Patent- och registreringsverket 2023 -ll5~ 1 6 The disclosure is also related to a kit according to claim 22. By adding a remote control to the kit better and more precise control of the UAV is achieved.

LIST OF DRAWINGS Fig 1 discloses an unmanned aerial vehicle according to the disclosure in flight configuration B. Fig. 2 discloses an unmanned aerial vehicle according to the disclosure in flight configuration A. Fig. 3 discloses an unmanned aerial vehicle according to the disclosure with three rotors.

Fig. 4 discloses an unmanned aerial vehicle kit according to the disclosure.

DETAILED DESCRIPTION The present disclosure is related to an unmanned aerial vehicle, also we use the abbreviation "UAV" below. The name sets the use ofthe vehicle, as it is clearly not piloted by an on-board pilot. instead the UAV is controlled by a comprised control unit, or by a remote operator. The remote control which may made through hardwire or wireless interfaces. The UAV may be part of an Unmanned aerial system, comprising a remote control.

Fig. 1 discloses the UAV 1 according to the disclosure. Three directions of the UAV 1 is hereby defined. Longitudinal direction X, transversal direction Y, and height direction Z, as depicted in Fig. 1 and also referred to in Fig. 3. The UAV 1 also has a defined central axis AA, se Fig. 2.

Fig. 1 discloses the UAV in a first flying configuration A. This, first flying configuration is in general a normal airplane mode, where the UAV is flying as a normal airplane. That is, the UAV flies with speed in the air in longitudinal direction, thus the wing generates lift as a normal flying wing.

Fig. 2 discloses the UAV 1 in a second flying configuration B. This, second flying configuration means that the UAV 1 may hover and fly as a helicopter. This, is also the preferred take off configuration, as the UAV 1 may take off from a very small space. Configuration B may also be used for landing.

The UAV 1 may switch independently between flying configuration A and flying configuration B. A normal scenario is that the UAV 1 takes off in Flying configuration B, i.e. vertically, then switches to flying configuration A, for transport flying a longer distance, and then alters to flying configuration B, in order to hover or fly slowly at a designated area, then the UAV 1 may return back to initial position in flying configuration A and land in flying configuration B.

Referring to Fig. 1 and Fig.2 the UAV 1 is provided with a fixed wing 2. The fixed wing 2 is in general a normal wing without any swept configuration, such that the wing gives good lift and may operate at lower speeds. That is the wing 2 is extending mainly in transversal direction Y. l.e. the wing is inkom till Patenr- ocn registreringsverket 2023 -05- l ﬁ preferred to be 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, 2b, assembles together to provide the wing 2. The wing elements may be attached directly to each other for providing the wing 2. lt is also thinkable that the wing 2 is a unit, and thus no need for assembling a right and left wing element to each other. The wing 2 is preferably provided with ailerons 12a, 12b. The ailerons 12a, 12b are individually controllable by means of servos, not shown. The ailerons provide control in the roll plane.

The UAV further is provided with rotors, 3, 4, 5. That is at least a three rotor configuration, is possible for the UAV 1, Fig. 3. This provide for a vertical control capability when flying in the second configuration B. In this three rotor configuration, it is preferred that the third rotor 5 is more centrally positioned, such that a more equilateral triangle configuration is achieved when viewing the rotors in longitudinal direction X, as shown in Fig. 3. That is, also the first and second rotor 3 and 4, is positioned essentially in a longitudinal plane positioned on a first side of the wing 2. And the third rotor 5 is positioned on the other side ofthe wing at a position that in transversal direction Y would be between the first and second rotor, see Fig. 3. A four rotor configuration gives more easy control of the UAV, that is by adding a fourth rotor 6. With four rotors, Fig. 1 and Fig, 2, there are a squared configuration in longitudinal direction, which allows for excellent and balanced control ofthe UAV. lt also allows for attachment of all the rotors to the wing 2, which in turn simplifies the UAV and keep the midsection 7 clean from rotor installation.

The rotors 3, 4, 5, 6, are preferably powered by a respective electric motor 3c, 4c, 5c, 6c, preferably brushless motor. The electric motors are powered by a suitable power source, such as batteries. The batteries may be of any suitable form, such as Lithium batteries. The batteries are preferred to be incorporated in the wing elements 2a, 2b close to the midsection 7. The batteries may also be incorporated into the midsection 7.

The rotor axes 3g, 4g, and 5g, and 6g, if applicable are essentially parallel, that is the rotors are spinning in parallel planes. This provides for an easy to control UAV 1. It is also preferred that the rotors 3, 4, 5, and 6 are spinning in different directions. For example rotor 3 and 5 may spin in clockwise direction and rotor 4 and 5 may spin in counter clockwise direction, such that the torque of the motors/rotors is cancelled out.

The first flying configuration A is when the UAV 1 is flying forward by means of the one or more rotors 3, 4, 5, 6, and uses the wing 2 for lift. ln this configuration, the energy consumption for the UAV 1 may be considerably reduced. It should also be mentioned that the UAV is only intended to be powered in this configuration A, with the same rotors 3, 4, 5, and 6, as used in configuration B. Thus, inkom till Patent- och registreringsverket 2023 -05- 1 6 there is no need for further rotors for switching between configuration A and configuration B. Also, the speed ofthe UAV 1 may be improved compared to an UAV 1 only using rotors for flying, and not having other lift/control surfaces. The control of the UAV 1 is made with acting on the ailerons 12a, 12b and also provided rudders 3e, 4e, 5e, etc.

The second flying configuration B is when the UAV 1 is flying by means of the rotors only. The wing 2 is not used for providing lift. In this configuration the rotors provide the lift. This means precision flying on the spot is possible. The UAV 1 may hover in position, or move away from the spot but and stop in the air. Control of the UAV 1 is made by adjusting the rotation speed ofthe respective rotor individually.

The UAV 1 may comprise at least two longitudinal booms 3a, 4a, Sa, and/or 6a. The preferred configuration is one longitudinal boom for each rotor provided to the UAV 1. The longitudinal booms are intended to extend mainly in the longitudinal direction X. The longitudinal booms may be manufactured in resin or in a light metal material, such as aluminium. The longitudinal booms 3a, 4a, Sa, may be detachably attached to the UAV 1. The longitudinal booms 3a, 4a, 5a, 6a, hosts the rotors 3, 4, 5, and 6. The rotors, is preferred to be attached to the end section of the longitudinal booms. The extension ofthe longitudinal booms may be used as a landing gear 3f, 4f, 5f, 6f. That is, the opposite end to the end holding the respective rotor. The landing gear preferably allows for the UAV 1 to stand on ground, that is essentially in the same manner as when the UAV 1 is flying in the second flying configuration B. The longitudinal booms may be three or four, or more. In a preferred configuration there are four longitudinal booms 3a, 4a, 5a, 6a, as seen in Fig. 1 and 2. The further longitudinal booms 5a, 6a, should be configured as the first and second longitudinal booms 3a, 4a.

At least two of the longitudinal booms 3a, 4a are attached to the UAV 1 at a predetermined distance from the same side of the wing 2. This is preferably achieved with holding device extending in height direction. lf more longitudinal booms are added further holding devices for each longitudinal boom 5a, 6a, added. The best mode is to have a holder boom 3b, 4b, Sb, 6b, as can be seen in Figs. 1 - 4. By adding the holding device to the UAV 1 the separation of the rotors from the wing and the UAV 1 in general is easily achieved.

The UAV 1, preferably comprises one or plural fins 3d, 4d, Sd, 6d. The fins are used to give stability of flight in the first configuration A of flying. The fins 3d, 4d, 5d, and 6d comprises preferably a rudder that is controllable 3e, 4e, 5,e, 6e, and thereby control yaw and pitch when flying in the first configuration. The fins 3d, 4d, 5d, 6d, are preferred to have an angle to the transversal Y and the height direction Z. Thus, giving input also in both height and roll direction if needed. This also gives a possibility to not add ailerons to the UAV 1.

Inkom till Patent- och registreringsverket 2023 -05- l 6 The UAV 1 may comprise a midsection 7 as seen in Figs. 1-4. The midsection 7, may be configured such that the wing 2 is attached to the midsection 7, in a detachable way. The wing 2, may be attached with the right wing element 2a and the left wing element 2b to the midsection 7. The midsection 7 is preferred to have an extension in longitudinal direction, such that it may support the wing 2 over the full chord. And also by extending outside the chord ofthe wing, the balance ofthe whole UAV 1 may be improved as the weight may be adjusted by changing the position of the midsection in longitudinal direction X. The midsection 7 comprises couplings 22 for attaching the wing 2, or more precisely the wing elements 2a, 2b. The couplings 22 are of such type such that the respective wing element 2a, 2b may be attached to both couplings 22 on both sides of the midsection 7.

The midsection 7, may be arranged such that it can carry a load 13. The load 13 may be a pipe shaped load 13. But other loads as cameras, rescue equipment, food packages, medicine or anything may be carried by the UAV 1. The pipe shaped load may be a weapon. The most preferred weapon is a recoilless 13 weapon. A recoilless weapon will not affect the flying ofthe UAV 1, when the munition is delivered. The UAV 1 needs no adaptation for handling any recoil. Obviously the weapon 7 could be an automatic gun or rifle or the like. And as the couplings 23 of the midsection is ofthe same type on both sides ofthe UAV 1, the pipe shaped load may be pointed in both directions, of the longitudinal direction X. Thus, ifthe first wing element 2a is attached to a first coupling 22 (not shown) in Fig. 4, it may also be attached to the second coupling 22 on the other side, thus pointing the pipe shaped load in the reverse direction.

The midsection 7 is preferred to be moulded on the inside to the shape of the cargo it is to carry. Thus, the midsection may have an interior that is moulded after the discussed recoilless weapon 13, thus achieving a very good fit.

The midsection 7, may be made in two halves that are fixed together. ln this way in particular a pipe shaped cargo as a recoilless rifle 13, for example the Carl Gustaf recoilless rifle, may be easily attached to the UAV 1. The midsection 7 is for this purpose provided with assembly means 20, for example in the shape of snap fittings, eccentric lock, or the like.

The midsection 7 is optionally provided with a navigation camera 18. The navigation camera 18 is in general mounted to the midsection in a gimbal so that the camera may rotate 360" in a horizontal plane, i.e. the plane comprising the longitudinal and transversal directions X and Y, and at least 180 grader in a plane parallel with the height direction Z.

The midsection 7 is optionally provided with an aiming camera 19. The aiming camera 19 is viewing narrowly in the direction of a weapon 13 carried by the midsection 7. The aiming camera 19 is inkom tiii Patent ocn registreringsverket 2023 -05- 1 6 calibrated with an aim 17 on the weapon 13, such that the camera may be used for aiming remotely. The aiming camera 19 is arranged such that it may always aim in the direction of munition delivery. lt the UAV 1 is arranged to send munition forward or backward, the aiming camera may be arranged to send video of the intended direction of sending munition. This may be arranged in several different ways, for example the aiming camera may be moved on the midsection 7 to view in backward direction ifthis is desired, instead of a forward direction as disciosed in Fig. 1. in a more preferred way the whole midsection 7 may be turned 180 degrees thus the aiming camera 19 follows in the turn and gets a view backwards instead of forward.

As an alternative the midsection 7 may be a weapon itself. The wing 2 comprising the longitudinal booms, may be directly attached to the weapon housing 13a. The preferred configuration that all rotors are attached to the wing, thus making the attachment points to the weapon only being the wing attachment. If the wing 2 is made up of two respective wing elements 2a, 2b, a simple attachment to the weapon may be achieved, for example by straps or the like.

The weapon may be attached in both longitudinal directions, to the UAV 1, thus it may be possible to deliver munition when hovering when flying in configuration B, that is firing downwards in essentially vertical direction. When, flying in configuration A, the UAV 1 may deliver munition in the line of flying of the UAV 1, and thus other targets maybe attached, such as for example flying targets. The variation of these two attack patterns, may be achieved by changing the direction ofthe midsection 7 on the UAV 1. Thus, the wings 2 should be possible to be attached to either side of the midsection 7, such that the direction of delivering munition is altered 180 degrees.

The UAV 1, preferably comprises a trigger device 16, such that a carried weapon 13 may be fired remotely. The trigger device 16 may be a software that acts on a local control unit in the weapon.

The trigger device 16 may also be a servo that mechanically acts on an original trigger ofthe weapon.

A preferred attack pattern may be that the UAV 1 starts with a recoilless weapon with the munition direction being to the back of Fig. 2. The UAV 1 thus starts in flying configuration B, vertically, then flies to a target in flying configuration A. At the target, for example a tank, the UAV 1 alters to flying configuration B, hovers above the tank, and fires the recoilless weapon vertically downwards on the tank. lfthe above attack pattern is not used, the recoilless weapon may be attached as in Fig. 2. In this configuration the UAV 1 may take off in flying configuration B, then continue in flying configuration A, at a much higher speed than possible l flying configuration B. An attack is thus made possible on for example a helicopter or the like by firing the recoilless weapon forward in the flight path ofthe UAV 1. inkom till Patent- och registreringsverket 2023 -05- l 5 The UAV 1 is preferred to be a kit 11 with separate elements, as seen in Fig. 4. The kit 11, may comprise a right wing element 2a and a left wing element 2b. From the wing 2 or wing elements the longitudinal booms 3a, 4a, 5a, 6a, are separated including the motors for the rotors. Also the rotors 3, 4, 5, 6, may be separated from the motors, thus making it possible to make the kit 11 very compact. Also the holding devices, may be separated from the longitudinal booms. lf a midsection 7 is included, the midsection may be separated from the other elements.

The kit 11 is arranged to be fitted together without tools and, the electric contacts for control surfaces and electric motors are al water proof, such that the UAV 1, may be operated in rain or harsh environments. This is true for all the discussed variants of UAV above, i.e. that the UAV 1 has the necessary gaskets and materials for allowing it to handle any water situation, the UAV may for example have an lP64 rating, or |P65, 66, 67 or |P68 rating, or even for extreme cases an |P69K rating.

The kit 11 is further discussed below.

A preferred kit 11, for providing an unmanned aerial vehicle 1 is disclosed, see Fig. 4. The kit 11 comprises the components already described above. ln particular the kit comprises a midsection 7, longitudinal booms 3a, 4a, 5a, 6a, foldable rotors 3, 4, 5, 6. A respective motor 3c, 4c, 5c, 6c is also comprised. As can be seen in Fig. 4 the rotors and motors are attached to the holder booms 3b, 4b, 5b, 6b. The rotors are preferred to be foldable, such that the kit may be packed in a small volume. There is also comprised couplings 21, 22, 23, 24. The couplings are designed to be used without any tool. For example there may be a cone that is surrounded by a threaded ring. And the threaded ring is acting on a thread such that the cone diameter is reduced if the ring is tightened, in an enclosing way. The connection 25 of for example a holder boom 6b is thus inserted in the connection 23 of a wing element 2b, and the ring is tightened and thus a very strong attachment is used. But this type of connection is not unique, one might consider for example a spring actuated click-in attachment for really fast build of the UAV 1. The click in attachment may function in the same way as a buckled side release buckle, or the like.

The UAV 1 preferably comprises a control unit 15. The control unit 15 is mainly aimed at controlling the rotors and flight surfaces such that the UAV may fly effortlessly for an operator. However the control unit 15 may only have a communicative function, ifthe operator provide control data with a remote control 14, to control the UAV 1.

The longitudinal booms and holder booms are preferred to be made in a light material as carbon fiber, or the like.

Claims

1. Unmanned aerial vehicle (1) having a longitudinal extension (X) and a transversal extension (Y) perpendicular to the longitudinal extension, and a vertical extension (Z) perpendicular to both the longitudinal (X) and transversal direction (Y), the unmanned aerial vehicle (1) comprising: -a fixed wing (2), wherein the wing (2) extend mainly in the transversal direction, -two powered rotors (3, 4) to provide thrust in the longitudinal direction, characterized in that the unmanned aerial vehicle (1) further comprises: - at least one further powered rotor (5), also to provide thrust in the longitudinal direction (X), - wherein the powered rotors (3, 4, 5) are attached to the UAV (1) in a configuration such that when viewed in longitudinal direction (X), at least one of the rotors (5) are separated in height direction (Z) from the other rotors (3, 4), and wherein at least two of the rotors (3, 4) is separated in transversal direction, -wherein the rotor axes (3g, 4g, 5g) of all three rotors (3, 4, 5) are essentially parallel, -wherein the unmanned aerial vehicle (1), may achieve a first flying configuration (A), where lift force is mainly generated by the wing (2) for conventional flying and a second flying configuration (B) where lift force is mainly achieved by the rotors (3, 4, 5), -wherein the same rotors (3, 4, 5) are used for both the first flying configuration (A) and the second flying configuration (B).

2. Unmanned aerial vehicle (1) according to claim 1, further comprising, -at least two longitudinal booms (3a, 4a, 5a), extending mainly in the in the longitudinal direction (X), optionally the at least two longitudinal booms (3a, 4a, 5a) are detachably attached to the unmanned aerial vehicle, preferably attached to the wing (2), wherein at least two of the powered rotors (3, 4, 5) are attached to an end section of the respective longitudinal boom (3a, 4a, 5a).

3. Unmanned aerial vehicle (1) according to claim 2, wherein each longitudinal boom (3a, 4a, 5a) comprises one or more fins (3d, 4d, 5d), preferably the configuration ofthe one or more fins (3d, 4d, 5d) is/are at an angle such that the fins (3d, 4d, 5d) extend both in the transversal and height direction, optionally the one or more fins comprises a rudder (3e, 4e, Se) for controlling the unmanned aerial vehicle (1) in yaw and/or pitch and/or roll, when flying in the first configuration (A).

4. Unmanned aerial vehicle (1) according to claim 2 or 3, Inkom till Patent- och registreringsverket 2023 -Û5- 1-wherein the at least two ofthe longitudinal booms (3a, 4a) are attached to the unmanned aerial vehicle (1) at a predetermined distance from one side ofthe wing (2) and one of the horizontal booms (5a) to the unmanned aerial vehicle at a predetermined distance from the other side of the wing (2), wherein the predetermined distance is such that the respective rotor (3, 4, 5) may rotate freely.

5. Unmanned aerial vehicle (1) according to any of the claims 2 to 4, wherein the attachment of the at least two of the longitudinal booms (3a, 4a) are being achieved by a respective holding device extending (3b, 4b, 5b, 6b) in height direction or both in height direction and transversal direction, preferably the holding device is in the form of a respective holder boom (3b, 4b, 5b, 6b) extending in the height direction, to which at least two of the longitudinal boom (3a, 4a, 5a, 6a) are attached.

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

7. Unmanned aerial vehicle (1) according to any of the claims above, wherein the unmanned aerial vehicle (1) comprises a third and fourth longitudinal boom (5a, 6a), with the third rotor (5) attached to one of these longitudinal booms (5a) and a fourth rotor (6) attached to the forth longitudinal boom (6a), all rotors (3, 4, 5, 6) being attached near one end section ofthe respective longitudinal boom (5a, 6a), all comprised longitudinal booms (3a, 4a, 5a, 6a) are arranged at a at a predetermined distance from the wing (2) and attached to a holding device (3b, 4b, 5b, 6b), preferably in the form of a holder boom (5b) extending in height direction (Z) and or both height direction (Z) and transversal (Y) direction, the preferred configuration of the horizontal booms (3a, 4a, 5a, 6a) being that two longitudinal booms (3a, 4a) are attached in height direction (Z) on one side ofthe wing (2) and two of the longitudinal booms (5a, 6a) are attached on the opposite side ofthe wing (2), such that each rotor (3, 4, 5, 6) is separated from another rotor (3, 4, 5, 6) either in height direction (Z) of transversal direction.

8. Unmanned aerial vehicle (1) according to any of the claims above, further comprising a midsection (7) to which the fixed wing (Za, 2b) is detachably attached, preferably such that the wing 2 may be separated into a left wing element (Za) and a right wing element (2b), preferably the mid-section (7) extends longer in the direction in the longitudinal direction than the transversal direction and/or the vertical direction.

9. Unmanned aerial vehicle (1) according to claim 8, wherein the midsection (7) is arranged to carry a pipe shaped cargo (13), preferably the midsection (7) may be opened into to two halves (7a, 7b), such that a pipe shaped cargo (13) may be enclosed when the two halves (14a, 14b) are attached inkom till Pateni- OCH registreringsverket 2023 -05- ltogether after positioning the pipe shaped cargo (13) into the midsection (7), preferably the pipe shaped cargo is a weapon (13), more preferred a recoilless weapon (13).

10. Unmanned aerial vehicle (1) according to any of the claims above, wherein the unmanned aerial vehicle (1) comprises an navigation camera (18), and/or an aiming camera (19), preferably the navigation camera (18) and/the aiming camera (19) are both comprised in the midsection (7) of the unmanned aerial vehicle (1).

11. Unmanned aerial vehicle (1) according to claim 10, wherein the aiming camera (19) is arranged to view in the same direction, as a comprised weapon (13) delivers munition.

12. Unmanned aerial vehicle (1) according to the claim 8, wherein the midsection (7) is constituted of a weapon (13), preferably a recoilless weapon, such that the unmanned aerial vehicle (1) is assembled to the recoilless weapon (13), by attaching the wing (2) to the weapon (13).

13. Unmanned aerial vehicle (1) according to any of the claims 8 to 12, wherein the weapon (13) as attached or as incorporated, may deliver munition in a first predetermined direction parallel with the longitudinal direction (X), and wherein the recoilless weapon (13) alternatively may be attached in a second predetermined reversed direction, also parallel with the longitudinal direction (X), wherein the first predetermined direction is defined as the forward direction when flying in the first configuration (A) and the second predetermined direction is defined as backwards when flying in the first configuration (A).

14. Unmanned aerial vehicle (1) according to any of the claims above, wherein the unmanned aerial vehicle (1) is arranged to be transported in a disassembled state as kit (11), preferably the disassembled state comprises a right wing element (2a), a left wing element (2b), at least three longitudinal booms (3, 4, 5, 6) from which respective rotor (3, 4, 5, 6) optionally has been separated, and optionally also a midsection (7) to which the wing (2) is attached.

15. Unmanned aerial vehicle (1) according to any of the claims above, wherein the wing (2) comprises ailerons (12a, 12b) for control in roll axis, when flying in the first configuration.

16. Unmanned aerial vehicle (1) according to any ofthe claims above, wherein the unmanned aerial vehicle (1) is arranged with a fixed landing gear (3f, 4f, 5f, 6f) preferably such that the landing gear makes the unmanned aerial vehicle (1) point with its longitudinal direction in vertical direction.

17. Unmanned aerial vehicle (1) according to any ofthe claims above, wherein each rotor (3, 4, 5, 6) is powered by a dedicated electric motor (3c, 4c, 5c, 6c), preferably the motor is positioned near the rotor end ofthe respective longitudinal boom (3a, 4a, 5a, 6a). lnkom till Pateni- OCH registreringsvêfkeï 2023 -05- l

18. Unmanned aerial vehicle (1) according to any of the claims above, wherein it further comprises a control unit (15) arranged to control the rotors (3, 4, 5, 6) individually of the unmanned aerial vehicle (1), wherein the control unit (15) is arranged to be given instructions for a flight pattern either by uploading flight pattern instructions to a memory ofthe control unit (15), and/or the control unit may be given instructions by a remote control device (14) arranged to communicate with the unmanned aerial vehicle (1) at distance from the unmanned aerial vehicle (1).

19. Unmanned aerial vehicle (1) according to any ofthe claims 1-18, wherein there is further comprised a trigger device (16), such that the control unit (15) and/ or a remote control (14), may trigger a carried weapon (13).

20. Unmanned aerial system, comprising an unmanned aerial vehicle (1) according to any ofthe claims 1-19, wherein the system further comprises a remote control (14) for controlling the unmanned aerial vehicle (1).

21. Kit (11) for providing an unmanned aerial vehicle (1) according to any of the claims 1-19, wherein the kit (11) comprises a midsection (7), four longitudinal booms (3a, 4a, 5a, 6), fourfoldable rotors (3, 4, 5, 6) with a respective motor (3c, 4c, 5c, 6c) and a respective holder boom (3b, 4b, 5b, 6b), two wing elements (2a, 2b), wherein the kit (11) is assembled without using tools, by means of couplings (21) at the wing elements (2), and couplings (22) at the midsection (7) for attaching the wing elements (2a, 2b) and further couplings (23) on the lower and upper surface of the wing elements (2a, 2b) for attaching the holder booms (3b, 4b, 5b, 6b) to the wing with couplings (25) at a first end of the holder booms (3b, 4b, 5b, 6b) and couplings (24) on the longitudinal booms (3a, 4a, 5a, 6a) for attaching to couplings (26) at a second end of the holder booms (3b, 4b, 5b, 6b).

22. Kit (11) according to claim 21, wherein further comprised is a remote control (14) for controlling the unmanned aerial vehicle (1) as built from the kit (11).