An aircraft system with at least one electric motor

Abstract

An aircraft (1) according to the invention comprises at least one electric motor (2). The aircraft also comprises a power source (3). Further, the aircraft comprises an additional power source (5, 8) arranged to be used as a power source during take-off of the aircraft.

Description

[0001] AN AIRCRAFT SYSTEM WITH AT LEAST ONE ELECTRIC MOTOR

[0002] Field of the invention

[0003] The invention relates to an aircraft with at least one electric motor. In particular, the invention relates to drones and eVTOL aircraft.

[0004] Prior art

[0005] Aircraft, such as drones and eVTOL (electric vertical take-off and landing) aircraft, have at least one electric motor. The power source Is normally a battery for supplying energy to the electric motor / s. Ascent of the aircraft from the ground to the flight altitude consumes a relatively high amount of energy. This affects the operating distance of the aircraft.

[0006] Brief description of the invention

[0007] The aim of the invention is to eliminate disadvantages of prior art. This is achieved in the way presented in the independent claim.

[0008] The aircraft system according to the invention comprises at least one electric motor. The aircraft also comprises a power source. Furthermore, the aircraft comprises an additional power source arranged to be used as a power source during take-off of the aircraft.

[0009] List of figures

[0010] In the following, the invention will be described in more detail with reference to the figures in the appended drawings, wherein

[0011] Fig. 1 shows an example of an aircraft according to the invention. Description of the invention

[0012] Figure 1 shows an example of an aircraft system according to the invention, comprising at least one electric motor. In the example of the figure, the aircraft 1 is a drone, but it may also be a different type of aircraft, such as an eVTOL aircraft.

[0013] The aircraft (drone) according to the example has several electric motors 2, but in another embodiment, the aircraft may have only one electric motor. Further, the aircraft has a power source 3. The aircraft also has an additional power source 5, 8 arranged to be used as a power source during take-off of the aircraft.

[0014] The power source of a drone, an eVTOL aircraft or another corresponding aircraft 3 is normally a battery for supply ing energy to the electric motor / s. The solution according to the invention also has an additional power source 5 which may be a battery or a capacitor. The capacitor may be a so-called supercapacitor.

[0015] The additional power source 5 is used as a power source for the electric motor or motors during take-off of the drone or corresponding aircraft. Thus, the energy needed for take-off from the ground / starting platform to the desired flight altitude is supplied by the additional power source. When the aircraft starts is actual flight after the take-off, it changes over to use the actual power source 3. An electric / electronlc unit 6 takes care of changing the supply of energy to the electric motor / s for the power source 3 instead of the additional power source 5. Because the energy needed for the take-off is not supplied by the power source 3, the flight time and / or flight distance of the aircraft 1 will be longer.

[0016] The additional power source 5 may remain attached to the frame 4 of the aircraft during the entire flight. It is also possible to remove the additional power source 5 from the frame of the aircraft after the take-off. Thus, the flight time and / or flight distance of the aircraft 1 can be extended to some extent even more, because the additional power source is not carried along during the actual flight, and the aircraft is thus lighter in weight.

[0017] The additional power source (such as a battery or a capacitor) 5 can be freely jettisoned from the aircraft. Thus, the means for attaching the additional power source will be released under the control of the electric / electronlc unit, and the additional power source will fall freely by gravity to the ground. A free-falling power source is suitable for e.g. military purposes, whereby it can be jettisoned either at the location of the take-off or at a later stage. Thus, the flight time and / or flight distance can be increased further. Particularly in military use, the free-fall battery is an easy and convenient solution.

[0018] The additional power source can also be jettisoned from the aircraft 1 in a controlled manner. Thus, the additional power source is provided with a parachute. When the means for attaching the additional power source are released under the control of the electric / electronic unit, the additional power source will fall towards the ground, whereby the parachute will unfurl as well. The additional power source will descend to the ground by the parachute.

[0019] The additional power source may also be an external power source 8. That is, the figure also shows a second embodiment for the aircraft system according to the invention. Such a power source is connected to the actual aircraft 1 by means of an electric cable 7. Thus, the energy needed for take-off of the aircraft is supplied by an external power source 8 which may be a battery, an electric generator, a fixed recharging point / socket, etc. For example, in a warfare area, the electric energy can be supplied by automobile batteries, a mobile generator, or the like.

[0020] The electric cable 7 is connected to the aircraft by a connector 9. The connector is, for example, of the plug / socket type. Thus, part of the connector is integrated in the frame 4 of the aircraft.

[0021] The electric / electronic unit 6 is configured to direct the electric energy supplied via the electric cable / connector to the electric motor / s of the aircraft. The connection to the electric motor / s may be arranged in a quite straightforward way, particularly if the voltage level of the electric energy produced by the external power source 8 is the same as the voltage level used by the electric motor / s. In case of a difference between the voltage levels, an inverter is used, which may thus be a part of the electric / electronic unit 6. The inverter will convert the voltage of the external power source to be suitable for the electric motor / s. Such a method can be called an indirect connection.

[0022] After the aircraft has reached the desired flight altitude, the electric cable can be detached. This may be arranged to take place automatically when the length of the cable runs out, at which point the connector 9 will open. The connector is thus arranged such that the connection will open when it is subjected to a sufficient traction force. The connection is thus designed not to open too early. Therefore, the connection has to be openable in a suitable way. In another embodiment, the electric / electronic unit 6 is configured to control an actuator in the connector, for opening the connector. Thus, the electric cable 7 will detach and fall to the ground. It should also be noted that when the electric cable is connected to the aircraft, the power source (such as a battery) can be recharged by the external power source 8. In other words, It is possible that the energy needed by the aircraft during its take-off as well as the energy for recharging the battery can be supplied by the external power source.

[0023] In some embodiments, the cable 7 does not need to be disconnected / detached from the aircraft. This applies to, for example, drones used for maintenance of buildings, if no measures are needed at a height, ^distance exceeding the length of the cable. It is thus possible to apply the external power source during the entire flight time.

[0024] In this description, the electric / electronic unit 6 is presented as a single unit, but in practice it may also consist of several units. An inverter was already mentioned above. The electric / electronic unit may comprise, for example, a circuit board, several circuit boards, a memory unit / units, a processor, etc. Various sensors may be included in or connected to the electric / electronic unit, such as a height sensor or sensors for detecting the altitude of the aircraft. The sensor data can be used in the changeover of the power source (e.g. after the take-off when changing over to use the power source instead of the additional power source). The changeover of the power source may also be remote controlled. Thus, a user on the ground operates a remote-control unit for the drone or other aircraft for changeover of the power source. The remote-control unit has radio communication with the electric / electronic unit.

[0025] Thus, the electric / electronic unit is / can be arranged to be capable of changing the energy supply to the electric motor / motors over from the additional power source to the power source intended for the actual flight of the aircraft.

[0026] Because the take-off of the aircraft (e.g. drone or eVTOL aircraft) consumes a considerable amount of energy compared with horizontal flight, it is economical and advantageous to use the solution according to the invention. Thus, the operating distance / time of the drone, eVTOL aircraft or other corresponding aircraft can be increased even to a significant extent.

[0027] In the light of the examples presented above, it is obvious that an implementation according to the invention can be achieved by a variety of solutions. In other words, the invention can be implemented with many different embodiments within the scope of the independent claim.

Claims

C la ims1. An aircraft system comprising at least one electric motor and also comprising a power source, characterized in that it comprises an additional power source arranged to be used as a power source during take-off of the aircraft.

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