Flight controller for an FPV drone

Abstract

The present application relates to a flight control unit (100) for an unmanned aerial vehicle (1), in particular for an FPV drone (1), and to an FPV drone (1) with such a flight control unit (100). The application further relates to an adapter board (1000) for testing electrical contacts and / or for connecting to external means for reading and / or writing data to data processing means of the flight control unit (100). The application further relates to a method (2000) for manufacturing a flight control unit (100).

Description

TECHNICAL AREA

[0001] The present application relates to a flight control unit for an unmanned aerial vehicle, in particular for an FPV drone, and to an FPV drone with such a flight control unit. The application further relates to an adapter board for testing electrical contacts and / or for connecting to external means for reading and / or writing data to data processing means of the flight control unit. The application also relates to a method for manufacturing a flight control unit. BACKGROUND

[0002] Unmanned aerial vehicles (UAVs, or drones) have been used militarily for many decades. In the course of the ongoing Russian war of aggression against Ukraine, which began in 2014, drones have been deployed in unprecedented numbers, particularly since the Russian invasion on February 24, 2022. A major driver of this development is the use or modification of drones originally developed for civilian purposes, from the recreational, enterprise, and consumer sectors, especially fixed-wing or rotary-wing aircraft such as quadcopters and octocopters. Besides reconnaissance, these originally civilian drones are also being used directly to achieve kinetic effects. A distinction must be made here between the delivery of ordnance on the one hand and the use of the drone itself as a guided missile on the other.In the latter case, the drone functions as so-called loitering munition, colloquially also referred to as "kamikaze drones." FPV drones (FPV: "first person view") are preferred for use as loitering munition; these are controlled from the drone's perspective, similar to a pilot's viewpoint, using camera technology. The camera images transmitted by the drone are typically displayed via video goggles.

[0003] The production of FPV drones for military use, particularly as loitering munitions, currently relies predominantly on commercially available hobbyist components, which require time-consuming manual assembly. Therefore, there is a need to streamline the production of FPV drones for use as loitering munitions. SUMMARY

[0004] In light of the aforementioned background, the present application discloses several aspects that enable the rationalization of the manufacturing of unmanned aerial vehicles. Where unmanned aerial vehicles, drones, UAVs, etc., are mentioned herein, preferably drones in the micro UAV range (up to 20 kg takeoff weight) and in the light UAV range (up to 150 kg takeoff weight) are meant. Particularly preferred are FPV drones and / or quadcopters and / or octocopters.

[0005] In a first aspect, a flight control unit for an unmanned aerial vehicle, in particular for an FPV drone, is disclosed. An exemplary embodiment of the first aspect is defined in claim 1.

[0006] In a second aspect, an unmanned aerial vehicle, in particular an FPV drone, with a flight control unit described herein is disclosed. An exemplary embodiment of the first aspect is defined in claim 9.

[0007] A third aspect discloses an adapter board for testing electrical contacts and / or for connecting to external means for reading and / or writing data to data processing means of a flight control unit described herein. An exemplary embodiment of the third aspect is defined in claim 10.

[0008] A fourth aspect discloses a kit consisting of a flight control unit or aircraft described herein, and an adapter board described herein. An exemplary embodiment of the fourth aspect is defined in claim 11.

[0009] A fifth aspect discloses a method for manufacturing a flight control unit described herein. An exemplary embodiment of the fifth aspect is defined in claim 12. BRIEF DESCRIPTION OF THE FIGURES

[0010] Further aspects, embodiments, and examples of the disclosed technology are described below in conjunction with the accompanying drawings. The terms "left," "right," "below," and "above" refer to an orientation of the drawings that facilitates the normal reading of the reference numerals, but do not necessarily define a position or orientation of the features or components with respect to manufacture or intended use, unless expressly stated or evident from the technical context. The experienced reader will immediately recognize that the accompanying drawings (unless otherwise indicated) are derived from CAD models and are to scale.The combinations of absolute and relative dimensions shown in the accompanying drawings are representative of the special aspects, embodiments and examples shown, but are not to be understood as limiting or essential to the disclosed technology. Fig. Figure 1 shows an embodiment of an unmanned aerial vehicle 1, which is designed as an FPV drone and is equipped as an agent or for the delivery of agents; Fig. 2: is a perspective view of a flight control unit 100 for a drone, in particular for a drone 1 as in Fig. 1 shown; Fig. Figure 3: is a schematic representation of a particular embodiment of a drone 1 which has the flight control arrangement 30; Fig. 4: is a rear view of the Flight Control Unit 100 from Fig. 2; Fig. 5: shows the electronic flight control unit 200 in standalone isometric view; Fig. 6: shows the electronic engine control unit 300 in standalone isometric view; Fig. Figure 7 shows an example adapter board 1000; Fig. Figure 8 shows an arrangement consisting of the flight control unit 100 and the adapter board 1000 in a state in which the pin connector interface 1100 contacts the interface 260 in a side view; Fig. 9: shows the arrangement from Fig. 8 in a rear view; Fig. Figure 10 shows a schematic flowchart of an exemplary procedure 2000 for the manufacture of a flight control unit, in particular a flight control unit 100 from the preceding figures. DETAILED DESCRIPTION OF THE FIGURES

[0011] The following sections describe further aspects, embodiments, and examples of the disclosed technology in conjunction with the attached drawings. The following sections are headed to improve readability. These headings are not intended to be restrictive of the disclosed technology. The technical content of the following description indicates that the aspects, embodiments, and examples described in the various sections can readily be combined, even if such a combination is not explicitly mentioned. Even if some elements are shown in combination in the attached drawings, these elements can, in principle, also exist independently of one another in other embodiments (particularly those not shown).Insofar as the following description and / or the drawings suggest a relationship between different elements shown in combination in the accompanying drawings, no inseparable functional or structural connection is to be seen therein unless there is a compelling technical necessity for such a combination. FPV drone

[0012] Fig. Figure 1 shows a preferred embodiment of an unmanned aerial vehicle 1, which is configured as an FPV drone and is set up as an agent or for delivering agents. An aircraft according to the technology disclosed herein can comprise a supporting basic structure 10, at least one electric drive unit 20, a flight control arrangement 30, a battery or accumulator 40, and an agent arrangement 50.

[0013] In preferred embodiments, as well as in Fig. As shown in Figure 1, the drone 1 is designed as a rotary-wing aircraft. Alternatively, the drone 1 can also be designed as a fixed-wing aircraft or a fixed-wing aircraft. In further embodiments, the drone 1 is a combination of a rotary-wing aircraft and a fixed-wing aircraft (so-called transition aircraft), and is particularly preferably equipped with tiltrotors.

[0014] In the illustrated rotary-wing configuration, the basic structure 10 has a plurality of rotor carriers 12, preferably four (quadcopter) or eight rotor carriers 12 (octocopter), each with a free end for receiving an electric drive unit 20, which is preferably provided in the form of a drive unit 20 consisting of a lift rotor 22 and an associated electric motor 24. The rotor carriers 12 extend in different directions from a central section, which is designed to receive further components of the drone, in particular the flight control system 30, and / or the battery or accumulator 40, and / or the control element assembly 50. In particular embodiments, the basic structure 10 is preferably made partially, predominantly, or entirely of wood, especially preferably of plywood.Alternatively or additionally preferably, the flight control arrangement 30 and / or the battery or accumulator 40 are arranged on a top side of the basic structure 10, and the active agent arrangement 50 is arranged on a bottom side of the basic structure 10.

[0015] In the illustrated embodiment, the weapon arrangement 50 comprises a payload carrier 52 and at least one weapon 54, which is attached to the base structure 10 by means of the payload carrier 52. The weapon 54 preferably comprises an explosive charge and a detonator, and can in particular be in the form of a conventional warhead of portable weapons, such as a mortar shell, a shaped charge warhead, a fragmentation warhead, a hand grenade, or a grenade from an automatic grenade launcher. In alternative embodiments, the weapon 54 can also be in the form of a firearm or cannon, such as a rifle.

[0016] In certain embodiments, the payload carrier 52 is configured for the selective release of one or more warheads 54. In particular, if the payload carrier 52 is configured to accommodate several warheads 54, the drone 1 can thus be used to engage multiple targets. The release of warheads also advantageously allows the drone 1 to be landed or recovered after the deployment of one or more warheads 54, in order to be used again.

[0017] In other embodiments, particularly those not designed for the selective release of weapons, the drone 1 is configured as a "kamikaze drone" or loitering munition. That is, the drone 1, with the weapon 54 attached to it, is flown to the target in order to trigger the weapon 54, in particular to detonate it.

[0018] The flight control arrangement 30, as explained in more detail below, is preferably configured to control the one or more electric drive units 20 in order to control the flight status of the drone 1. In preferred embodiments, the desired flight status is specified by a human operator who sends flight control signals to the drone 1 via a remote control. In other embodiments, the drone 1 is configured for autonomous operation and does not require remote control. In particularly preferred embodiments, the drone 1 is configured to be operated either remotely or autonomously. In particular embodiments, the flight control signal is transmitted via radio. In other embodiments, the flight control signal is transmitted to the ground via a cable connection, in particular via an optical fiber, as is known, for example, from wire-guided anti-tank weapons.Such a drone 1, which has a cable connection to the ground during flight, is also called a "tethered drone".

[0019] Additionally or alternatively, the flight control arrangement 30 may be configured, as explained in more detail below, to send digital or analog electrical signals to and / or receive digital or analog electrical signals from the countermeasure arrangement 50.

[0020] In the illustrated embodiment, the drone 1 is preferably configured as an FPV drone, which is why the flight control arrangement 30 has at least one camera 32 pointing in the direction of flight. As explained in more detail below, in such embodiments the flight control arrangement is configured to transmit a video signal to an operator on the ground. In particular embodiments, the video signal is transmitted wirelessly. In other embodiments, the video signal is transmitted to the ground via a cable connection, in particular via a fiber optic cable, as is known, for example, from wire-guided anti-tank weapons. Flight control unit

[0021] Fig. Figure 2 shows a flight control unit 100 for a drone, in particular for a drone 1 as described above. In certain embodiments, the flight control unit 100 constitutes the flight control assembly 30 of the drone 1 or is encompassed by the flight control assembly 30 of the drone 1. The flight control unit 100 comprises an electronic flight control unit 200 and an electronic motor control unit 300. In the field of FPV drones, electronic flight control units are also referred to as flight controllers (FC), and electronic motor control units as electronic speed controllers (ESC). Fig. Figure 3 is a schematic representation of a particular embodiment of a drone 1, which includes the flight control arrangement 30. The electronic flight control unit 200 is shown in a standalone isometric view in Figure 3. Fig. Figure 5 shows the electronic engine control unit 300 in standalone position, shown in isometric view. Fig. 6 shown.

[0022] The electronic flight control unit 200 can comprise at least an electronic data processing means 210, an interface 220 for establishing a connection for exchanging analog or digital electrical signals with the electronic motor control unit 300, and means 230 for acquiring actual flight parameters and / or receiving target flight parameters. Preferably, the electronic data processing means 210 comprise a central processing unit and at least one data storage device. Alternatively or additionally preferably, the electronic data processing means 210 are designed as an integrated circuit. Alternatively or additionally preferably, the data storage device contains at least one data processing program for execution by the central processing unit.The data processing program is configured at least to control the flight status of the drone 1, in particular to compare actual flight parameters with target flight parameters, and to control the electronic motor control unit 300 so that the target flight parameters are achieved. In special embodiments designed for remote control by a human operator, the data processing program is specifically configured to calculate the target flight parameters based on the flight control signals transmitted by the remote control.

[0023] The electronic motor control unit 300 has one or more interfaces 310, 320, 330, and power electronics 340. The first interface 310 is configured to establish a connection for the exchange of analog or digital electrical signals with the flight control unit 200. The second interface 320 is configured to establish a current-carrying connection with the battery or accumulator 40. The third interface 330 is configured to establish a current-carrying connection with the at least one electric drive unit 20. The power electronics 340 is configured to supply the one or more electric motors 24 with electrical power from the battery or accumulator 40 via the third interface 330, based on the signals received from the flight control unit 200, and in particular to control their speed and / or torque.

[0024] In special embodiments, the one or more electric motors 24 are designed as brushless DC motors (also: brushless DC or BLDC motor), and the power electronics 340 are designed according to the type of a known motor control for such a BLDC motor.

[0025] In the particular embodiment shown, the electronic flight control unit 200 and the electronic motor control unit 300 are designed as separate circuit boards, with associated circuit board base plates 202 and 302, respectively. Preferably, the flight control unit 100 is provided as a so-called flight stack, meaning that the units 200 and 300 are arranged one above the other and mechanically connected to each other. For this purpose, preferably one or more, in particular four, spacer elements 350 of height H are provided, so that the units 200 and 300 are arranged in planes spaced apart from each other by height H, in particular parallel planes (see figure). Fig. 4) In particular embodiments, the spacer elements 350 are designed as threaded bushings with internal threads, so that the units 200 and 300 can advantageously be screwed together. For example, the spacer elements 350 are attached to a top surface of the motor control unit 300, in particular soldered to it, and the flight control unit 200 has corresponding through-holes 204 so that the two units can be detachably connected to each other by screws (not shown). In other embodiments, the detachable connection is implemented, for example, by a plug connection.

[0026] In a particular aspect of the disclosed technology, the flight control unit 200 and the motor control unit 300 are configured such that establishing the mechanical connection between the flight control unit 200 and the motor control unit 300 simultaneously connects the interfaces 220 and 310. It is particularly preferred that the connection between the interfaces 220 and 310 be mechanical, thus eliminating the need for soldering. Methods for implementing this aspect are explained below by way of example. This aspect advantageously simplifies the assembly of the flight control unit 100.

[0027] It is particularly preferred that the flight control unit 200 and the motor control unit 300 are configured to be mechanically connected to one another such that the interfaces 220 and 310 are arranged directly above one another. For example, interface 220 is located on a lower side of the flight control unit 200 and interface 310 is located on a top side of the motor control unit 300. In particular, interfaces 220 and 310 are designed as matching connectors. In the embodiment shown, interface 220 is designed as a male connector or pin plug, and interface 310 as a female connector or socket. In other embodiments, the configuration is reversed, i.e., the male and female connectors can also be arranged on the other unit 220, 310.The length of the male connector 220 is adapted to the height H of the spacer elements 350 in such a way that the needle plug 220 engages in the socket 310 when the flight control unit 200 is as shown. Fig. 4 shown on the motor control unit 300. In the particular embodiment shown, the connectors of interfaces 220, 310 are designed with fourteen pins, in particular in the form of two rows with seven pins or pin sockets each.

[0028] In a further alternative or additional aspect of the disclosed technology, the second interface 320 and / or the third interface 330 of the motor control unit 300 are also configured as mechanical connectors. In preferred embodiments, all interfaces 310, 320, 330 of the motor control unit 300 are configured as mechanical connectors. This advantageously eliminates the need for soldered connections. In other words, it is preferred that the first interface 310 and / or the second interface 320 and / or the third interface 330 are not configured as soldered connections.

[0029] In particular embodiments, the second interface 320 is configured as a two-pole female connector or socket designed to receive a two-pole male connector 42, which can be connected to or is connected to the battery or accumulator 40 via a two-phase cable 44. In other embodiments, the configuration is reversed, i.e., the male and female connectors can be assigned to each other. For example, the male and female connectors conform to one of the XT30, XT60, or XT90 standards.

[0030] In embodiments in which the second interface 320 is configured as a two-pole connector, it is further preferred that the motor control unit 300 has one or more, in particular two, decoupling capacitors 342, 344 arranged on the circuit board base plate 302 for stabilizing the supply voltage provided by the battery or accumulator 40. The decoupling capacitors 342, 344 are, for example, designed as electrolytic capacitors with a capacitance between 20 µF and 1000 µF, between 100 µF and 700 µF, between 400 µF and 600 µF, and in particular preferably with a capacitance between 500 µF and 600 µF.

[0031] In the illustrated embodiment, the third interface 330 is configured as two connectors 332, each designed to receive two connectors 26 of a respective electric drive unit 20. In other words, each of the two connectors 332 is designed to connect to two electric drive units 20, in particular their motors 22. This advantageously saves installation space, since only one connector 332 needs to be mounted on the circuit board 302 for each pair of motors. In embodiments with more than four motors 22, it is also preferred to provide only two connectors 332, each then designed to receive a correspondingly larger number of connectors 26. In particular, the drone 1 can be configured as an octocopter, i.e., have eight motors 22, with each connector 332 designed to receive four connectors 26.In embodiments in which the motors 22 are designed as BLDC motors, the connectors 26 are preferably three-pole, so that in the embodiment shown with four motors 22 each of the two connectors 332 is six-pole.

[0032] In other embodiments, the third interface 330 is configured with one connector 332 for each electric drive unit 20. In other words, in such embodiments, each of the connectors 332 is configured to receive a single connector 26 of a respective electric drive unit 20. For example, the third interface 330 can have four connectors 332 if the drone 1 is configured as a quadcopter, or eight connectors 332 if the drone 1 is configured as an octocopter. In such embodiments as well, the connectors 26 are preferably three-pin, particularly if the motor(s) 22 are configured as BLDC motors. In such embodiments, each of the connectors 332 is also three-pin.

[0033] As previously mentioned, the electronic flight control unit 200 includes means 230 for acquiring actual flight parameters and / or receiving target flight parameters. Means 230 can, for example, include a module 232 for signal exchange with a remote control. In certain embodiments, this is a radio module. In other embodiments, it is a cable connection, in particular via an optical fiber, as is known, for example, from wire-guided anti-tank weapons. Alternatively or additionally, means 230 can include an inertial measurement unit 234 (also referred to as an IMU) with acceleration and / or yaw rate sensors. Alternatively or additionally, means 230 can include pressure sensors (not shown), for example, for determining static pressure and / or dynamic pressure.

[0034] Devices 230 can be integrated on the circuit board 202 or connected to the electronic flight control unit 200 via interfaces 240. In the illustrated embodiment, the flight control unit 200 has four interfaces in the form of connectors 240, the number of which can be greater or less than four as required. Radio module 232 is shown as an example external device 230, which is connected to the flight control unit 200 via connectors 240.

[0035] Particularly in embodiments of the drone 1 configured as an FPV drone, it is preferred to provide a camera 32, which is optionally connected to the flight control unit 200 via connectors 240. To transmit a video signal to the operator, means for transmitting a video signal, in particular a radio module 250, can be provided, which is optionally connected to the flight control unit 200 via connectors 240. In other embodiments, a single radio module is configured to transmit the video signal and to communicate with a remote control. Alternatively, one or both functions are performed by a single wire connection, in particular an optical fiber.

[0036] Particularly in embodiments of the drone 1 configured as a delivery device or for the delivery of delivery devices, it is preferred that the delivery device arrangement 50 is connected to the flight control unit 200 via a signal connection, in particular by means of a connector 240. In such embodiments, the flight control unit 200 can be configured to send signals to the delivery device arrangement 50 that cause the ignition and / or release of one or more delivery devices 54. In particular, the drone 1 can thus be advantageously configured so that the ignition and / or release of the delivery devices 54 can be effected via the remote control for flight control.

[0037] Alternatively or additionally, an electrical detonator of one or more active devices 54 can be supplied with voltage via the signal connection between the active device arrangement 50 and the flight control unit 200. In particular, the flight control unit 200 can serve as an additional safety mechanism in this way. It is preferred that the flight control unit 200 is configured to selectively de-energize or energize the electrical detonators of one or more active devices 54.

[0038] Alternatively or additionally, one or more of the active means 54 are other than kinetic active means. For example, drone 1 can be equipped for firefighting. In such embodiments, active means 54 can be in the form of firefighting agents containing, for example, water and / or other extinguishing agents. Active means arrangement 50 can, for example, be in the form of an extinguishing agent container that can be selectively opened to release an extinguishing agent. In other embodiments, active means 54 can be in the form of a jettisonable extinguishing agent container that is configured to release extinguishing agents after being jettisoned.

[0039] Alternatively or additionally, the weapon system 50 is configured to transmit energy to a target in a manner other than kinetic. For example, the weapon system 54 can be configured to transmit electromagnetic energy to a target. For example, the weapon system 54 can be configured as a laser and / or as a microwave transmitter. The energy emitted by the weapon system 54 can be used to directly engage a target, for example, by converting the transmitted electromagnetic energy into heat within the target. Alternatively or additionally, the energy emitted by the weapon system 54 can be used for electronic warfare. Alternatively or additionally, the energy emitted by the weapon system 54 can be used for indirect engagement of a target, in particular for target illumination for laser- and / or radar-guided weapons.

[0040] The flight control unit 200 can therefore generally be configured to send analog or digital electrical signals to the control device assembly 50, in particular to control one or more electrical, mechanical, electromechanical and / or electronic control elements (not shown) of the control device assembly 50. Such control elements can, for example, include actuators, in particular servo motors.

[0041] Such an actuator can be configured, in particular, to cause the release of an active agent 54, for example, by releasing a releasable connection between the active agent receptacle 52 and the active agent 54 (for example, opening a bomb lock), or by opening an extinguishing agent container to release extinguishing agent. Alternatively or additionally, the control elements can comprise one or more relays and / or transistors. For example, by controlling a transistor, a means of emitting electromechanical energy (laser, radar, microwave transmitter, etc.) can be activated and / or deactivated. Adapter board

[0042] As in Fig. As shown in Figure 3, the flight control unit 200 can have an optional additional interface 260, which is configured to receive digital or analog electrical signals. In particular, the interface 260 can be configured as a multi-pole contact area, preferably ten-pole, with planar individual contacts 262, which are configured to be contacted by the pins of a pin connector. Fig. Figure 7 shows an exemplary adapter board 1000 with interface 1100 (e.g. needle plug) which is set up to make electrical contact with interface 260, in particular by each of the needles 1110 contacting a single contact 262. Fig. Figure 8 shows an arrangement consisting of the flight control unit 100 and the adapter board 1000 in a state in which the pin connector interface 1100 contacts the interface 260 in a side view. Fig. Figure 9 shows the same arrangement in a rear view.

[0043] Adapter board 1000 is designed for testing the electrical contacts of the flight control unit 100 and / or for connecting to external devices for reading and / or writing data to the data processing devices, in particular for reading and / or saving data to the data memory of the flight control unit 200. For this purpose, adapter board 1000 has an interface 1400 for connecting to external devices, in particular a serial interface, such as a USB interface. Alternatively or additionally, adapter board 1000 has an interface 1500 for an external storage medium.

[0044] When the drone 1 is used as loitering ammunition, it is possible that a warhead 54 may fail to detonate (so-called dud), or that when warhead 54 detonates, the flight control unit 100 may not be destroyed, or not destroyed in a way that prevents the data storage from being read. In such cases, there is a possibility that enemy forces could obtain militarily relevant information by reading the data storage. In certain embodiments, the data storage of the flight control unit 200 is therefore encrypted using known methods for encrypting digital data. This is intended to advantageously prevent unauthorized access to data on the data storage, in particular the data processing program for flight control.

[0045] However, encrypting the data storage prevents or hinders unauthorized access to or modification of data on the data storage device. Nevertheless, it is desirable for the operator of drone 1 to have the ability to access or modify this data. Therefore, in certain embodiments, the adapter board 1000 includes means for decrypting the data storage. Specifically, a decryption key can be stored on a data storage device on the adapter board 1000. In alternative embodiments, a data storage device with a key can be provided on an external storage medium, which can be connected to the adapter board 1000 via interface 1500.

[0046] In other embodiments, unauthorized reading of the data memory of the flight control unit 200 is at least made more difficult by the fact that interfaces 260 and 1100 are not designed as standardized serial interfaces. In particular, interfaces 260 and 1100 are not USB interfaces.

[0047] Alternatively or additionally, adapter board 1000 can advantageously be used in the manufacturing process of the flight control unit 100. In particular embodiments of the adapter board 1000, it has one or more (for example, two) spacer elements 1200 which are configured to make mechanical contact with the flight control unit 200, so that an electrical contact is simultaneously established between the interfaces 260 and 1100. For this purpose, for example, the length L of one or more contact elements 1200 can be matched to the length of the interface 1100, in particular to the length L of the pins 1110 in the contacted state with interface 260.

[0048] Alternatively or additionally, spacers 1200 can also be configured to align the adapter board 1000 relative to the flight control unit 100, in particular by means of mechanical contact between one or more spacers 1200 and one or more reference elements of the flight control unit 100. In particular, the spacers 1200 and the reference elements can be adapted to each other such that establishing mechanical contact between the spacers 1200 and the reference elements causes the interfaces 260 and 1100 to align with each other in a direction perpendicular to the boards 1000 and 302. For example, as shown in the Fig. 8 and Fig. Figure 9 shows that the longitudinal axes A of the through holes 204 and the spacer elements 350 of the flight control unit 100 serve as reference elements. In the illustrated embodiment, the interface 1100 is located on the underside of the adapter board 1000, centrally positioned between two adapter elements 1200, and the interface 260 is located on the top side of the flight control unit 200, centrally positioned between the through holes 204. This alignment of the spacer elements 1200 with the longitudinal axes A of the through holes 204 and the spacer elements 350 results in the interfaces 260 and 1100 aligning with each other in a direction perpendicular to the boards 1000 and 302. In particular embodiments, the spacer elements 1200 can have optional engagement elements (not shown) designed to engage with the through holes 204. Method for manufacturing a flight control unit

[0049] Fig. Figure 10 shows a schematic flowchart of an exemplary procedure 2000 for the manufacture of a flight control unit, in particular a flight control unit 100 as described above.

[0050] In step 2100, an electronic motor control unit, in particular a motor control unit 300 as described above, is provided. In step 2200, a flight control unit, in particular a flight control unit 200 as described above, is mechanically and preferably detachably connected to the motor control unit. In particular embodiments, in step 2200, an interface of the flight control unit, in particular an interface 220 as described above, is simultaneously electrically connected to an interface of the motor control unit, in particular an interface 310 as described above. In preferred embodiments, the interfaces are connected via a mechanical plug connection. It is particularly preferred that the step of connecting the interfaces does not include soldering.

[0051] Step 2200 can, in certain embodiments, consist of several sub-steps. In a first sub-step 2210, the flight control unit is positioned at a distance from the engine control unit in one direction (e.g., vertically). In a subsequent second sub-step 2220, the flight control unit is aligned with the engine control unit in a plane perpendicular to this direction (e.g., horizontally), so that the interfaces to be connected between the flight control unit and the engine control unit are aligned in the first (e.g., vertical) direction. In particular, through-holes 204 and spacer elements 350 can be aligned with each other as described above, so that interface 220 is arranged in the first (e.g., vertical) direction above interface 310 and is aligned with it. In a subsequent third sub-step 2230, the flight control unit is positioned along the first (e.g., vertical) direction.in a vertical direction towards the motor control unit until the interfaces are in electrically conductive contact with each other. In particular, in this sub-step 2230, one or more of the previously described spacer elements 350 of the motor control unit 300 can simultaneously come into mechanical contact with the circuit board 202 of the flight control unit 200. In certain embodiments, establishing the mechanical contact already results in the motor control unit and the flight control unit being attached to each other, in particular detachably attached. For example, this can be achieved by a mechanical plug connection. In other embodiments, in a subsequent sub-step 2250, the flight control unit is attached to the motor control unit, in particular detachably attached. For example, this can be done, as already described, by screwing screws through the through-holes 204 into the threaded bushings 350.

[0052] In an optional and subsequent third step 2300, the flight control unit, consisting of the flight control unit and the motor control unit, is programmed and / or tested, particularly in the manner already described. In special embodiments, external testing and / or programming equipment is brought into electrically conductive contact with the flight control unit for this purpose.

[0053] In particular embodiments, the third step 2300 is carried out in one or more sub-steps. In a first sub-step 2310, an adapter unit is provided spaced from the flight control unit in one direction (e.g., vertically), in particular an adapter unit 1000 as described above. In a subsequent second sub-step 2320, the adapter unit is aligned relative to the flight control unit, in particular such that the interfaces to be connected of the flight control unit and the adapter unit are aligned with each other in the first (e.g., vertical) direction. In particular, as described above, spacer elements 1200 of the adapter unit 1000 can be aligned with through holes 204 of the flight control unit 200. In a third sub-step 2330, the adapter unit is positioned along the first (e.g., vertical) direction.moved in a vertical direction towards the flight control unit until the interfaces are in electrically conductive contact with each other, in particular as above with reference to the . Fig. 8 and Fig. 9 described. In a subsequent fourth sub-step 2340, the flight control unit is tested and / or programmed. In special embodiments, the fourth sub-step 2340 includes the encryption and / or decryption of data on a data storage device of the flight control unit, in particular as described above.

[0054] In particular embodiments, one or more of steps 2200 and 2300, or their substeps, preferably all substeps, are performed by means of a robot. In other words, in particular embodiments, method 2000 is an automated method.

Claims

[1] Flight control unit (100) for an unmanned aircraft (1), in particular for an FPV drone (1), wherein the flight control unit (100) comprises: an electronic engine control unit (300); and an electronic flight control unit (200); the electronic engine control unit (300) comprises: a first interface (310) for exchanging analog or digital electrical signals with the flight control unit (200); a second interface (320) for establishing a current-carrying connection with the battery (40); at least one third interface (330) for establishing a current-carrying connection with at least one electrical propulsion unit (20) of the unmanned aerial vehicle (1); and a power electronics unit (340) which is configured to supply one or more electric motors (24) of the electric drive unit (20) with electrical power from the battery (40) via the third interface (330) on the basis of signals received from the flight control unit (200), in particular to control their speed and / or torque; the electronic flight control unit (200) comprises: Electronic data processing equipment (210); and an interface (220) for establishing a connection for the exchange of analog or digital electrical signals with the electronic motor control unit (300); wherein the at least one third interface (330) for establishing a current-carrying connection with at least one electrical drive unit (20) of the unmanned aircraft (1) is designed as a mechanical connector. [2] Flight control unit (100) according to claim 1, wherein the first interface (310) of the motor control unit (300) and the interface (220) of the flight control unit (200) are designed as matched connectors. [3] Flight control unit (100) according to one of the preceding claims, wherein the second interface (320) is designed as a mechanical connector. [4] Flight control unit (100) according to claim 3, wherein the motor control unit (300) has one or more support capacitors (342) arranged on a circuit board base plate (302) of the motor control unit (300) for stabilizing a supply voltage provided by the battery (40). [5] Flight control unit (100) according to one of the preceding claims, wherein the flight control unit (200) has one or more additional interfaces (240) for establishing a connection for exchanging analog or digital electrical signals with means (230) for acquiring actual flight parameters and / or receiving desired flight parameters and / or with means (250) for transmitting a video signal. [6] Flight control unit (100) according to claim 5, wherein the one or more additional interfaces (240) are designed as mechanical connectors. [7] Flight control unit (100) according to one of the preceding claims, wherein the flight control unit (200) has a further interface (260) which is configured to receive digital or analog electrical signals through an external adapter board. [8] Flight control unit (100) according to one of the preceding claims, wherein the flight control unit (200) is configured to: to send electrical signals to an agent assembly (50) of the unmanned aircraft (1) in order to control one or more electrical, mechanical, electromechanical and / or electronic control elements of the agent assembly (50), wherein the signals preferably cause ignition and / or release of one or more agents (54); and / or to supply an electrical igniter of one or more active agents (54) of the active agent arrangement (50) in a switchable manner with voltage. [9] Unmanned aerial vehicle (1), in particular an FPV drone (1), comprising: a flight control unit (100) according to any one of the preceding claims; and a payload carrier (52) which is configured to accommodate at least one active agent (54), wherein the active agent (54) preferably comprises an explosive charge and a detonator. [10] Adapter board (1000) for testing electrical contacts and / or for connecting to external means for reading and / or writing data to means for data processing of the flight control unit according to any one of claims 1 to 8. [11] Kit comprising a flight control unit (100) according to any one of claims 1 to 8 or an unmanned aerial vehicle (1) according to claim 9, and an adapter board (1000) according to claim 10. [12] Method (2000) for manufacturing a flight control unit (100) for an unmanned aircraft (1), in particular for an FPV drone (1), the method comprising the steps: Providing (2100) an electronic engine control unit (300); Providing (2210) an electronic flight control unit (200); and mechanical connection (2200) of the flight control unit (200) with the engine control unit (300); where at least the step of mechanical joining (2200) is performed by a robot. [13] Method according to claim 12, wherein the mechanical connection (2200) of the flight control unit (200) with the motor control unit (300) simultaneously effects an electrically conductive connection of an interface (220) of the flight control unit (200) with an interface (310) of the motor control unit (300). [14] Method according to claim 13, wherein the electronic flight control unit (200) is provided spaced apart from the motor control unit (200) in a first direction, and wherein the flight control unit (200) is subsequently aligned in a plane perpendicular to the first direction with respect to the motor control unit (200) such that the interfaces (220, 310) to be connected of the flight control unit (200) and the motor control unit (300) are aligned with each other in the first direction; preferably wherein the alignment is carried out by a robot. [15] Method according to any one of claims 12 to 14, further comprising the step of programming and / or testing the flight control unit (100) using external testing and / or programming means, wherein the step comprises: Providing (2310) an adapter unit (1000); and electrical connection (2330) of an interface (1100) of the adapter unit (1000) with an interface (260) of the flight control unit (100); preferably wherein the steps of provisioning (2310) and / or electrical connection (2330) are performed by a robot.

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