Abstract:
An aircraft includes at least three drive units, each of which has a first rotor and a first, rotary speed-controlled electrical motor, suitable for driving the first rotor during operation of the aircraft. Each of the drive units has at least a second rotor and at least one second, rotary speed-controlled electrical motor, suitable for driving the second rotor during operation of the aircraft in a rotational direction that is opposite to the rotational direction of the first rotor of each drive unit. Autonomous means for controlling the location and position of the aircraft are also provided.

Description:
BACKGROUND OF THE INVENTION 
     FIELD OF THE INVENTION 
     The present invention relates to an aircraft which has at least three drive units, which each have a first rotor and a first electric motor whose rotation speed is controlled, suitable for driving the first rotor during operation of the aircraft, and comprises means for autonomous attitude and position control of the aircraft. 
     Aircraft of the type mentioned initially are already known in various embodiments from the prior art. For example, at this point, it is intended to describe an aircraft which was developed several years ago, is in the form of a microdrone and has four drive units, each having a rotor in order to produce lift. The known aircraft furthermore comprises electronic attitude control, which, for example, allows the aircraft to assume a hovering flight attitude. The aircraft can be controlled by varying the rotation speeds of the electric motors, with each electric motor being operated individually by a central control unit. 
     One disadvantage of the four-rotor aircraft which are known from the prior art is that they are designed to be relatively large in order to allow them to transport a specific payload. 
     This is the purpose of the present invention. 
     BRIEF SUMMARY OF THE INVENTION 
     The present invention is based on the object of providing an aircraft of the type mentioned initially which, while retaining the payload, is more compact than the four-rotor aircraft known from the prior art. 
     This object is achieved by an aircraft including at least three drive units, which each have a first rotor and a first electric motor whose rotation speed is controlled, suitable for driving the first rotor during operation of the aircraft, and means for autonomous attitude and position control of the aircraft. The dependent claims relate to advantageous developments of the present invention. 
     An aircraft according to the invention is distinguished in that each of the drive units has at least one second rotor and at least one second electric motor whose rotation speed is controlled, suitable for driving the second rotor during operation of the aircraft, in a rotation direction which is opposite the rotation direction of the first rotor of the respective drive unit. 
     Instead of four drive units each having one rotor, the aircraft according to the invention has at least three drive units each having at least two rotors, which are driven in pairs in opposite directions. The advantage of this measure is that the aircraft can be made more compact than the aircraft known from the prior art, while retaining the payload. This measure advantageously allows the diameter of the aircraft to be reduced by about 30%. Since at least three drive units, each having two rotors, are provided, efficient position and attitude control can be provided for the aircraft. The provision of at least two rotors per drive unit furthermore has the advantage of improved redundancy. If, for example, one rotor of the drive unit fails during operation of the aircraft, the remaining second rotor can provide sufficient thrust in order to move the aircraft or to maintain its position. The electric motors are preferably brushless and have no transmission. The means for autonomous attitude and position control of the aircraft may, for example, have gyroscopic sensors and acceleration sensors in addition to a central control unit. Furthermore, the aircraft can preferably have one or more of the sensor means mentioned below (also in combination):
         rotation rate sensors,   acceleration sensors,   barometric sensors   magnetometric sensors,   Ultrasound sensors,   GPS sensors,   optical sensors.       

     In one preferred embodiment, it is possible for the first rotors of at least two drive units to have a common rotation plane. In particular, it is also possible for the first rotors of all the drive units to have a common rotation plane, in order to improve the flying characteristics of the aircraft. 
     In one preferred embodiment, it is possible for the second rotors of at least two drive units to have a common rotation plane. Furthermore, in one particularly preferred embodiment, it is possible for the second rotors of all the drive units to have a common rotation plane. This measure allows the flying characteristics of the aircraft to be improved further. 
     The rotation planes of the first and second rotors may in particular be oriented essentially parallel to one another. 
     The first and second rotors of at least one of the drive units are preferably separated from one another in the axial direction. In one advantageous embodiment, it is also possible for the first and second rotors of each of the at least three drive units to be separated from one another in the axial direction. 
     In one preferred embodiment, the first and second rotors of at least one of the drive units can be arranged coaxially. It is particularly preferable for the first and second rotors of each of the at least three drive units to be arranged coaxially. 
     In one advantageous embodiment, it is possible for the aircraft to have a support for the drive units, which support comprises a number of supporting arms to each of which at least one of the drive units is fitted. The supporting arms may, for example, extend away from a centerpoint of the support in the radial direction. 
     In one preferred embodiment, the support may comprise a base body to which the supporting arms are fitted. For example, parts of the central control unit, sensor means, transmitter and receiver means for communication of the aircraft with a ground station can be accommodated within the base body. 
     In order to simplify the assembly and the disassembly of the aircraft, it is possible for the supporting arms to be detachably fitted to the base body, in particular by means of quick-release fasteners. 
     In order to avoid damage to the rotors of the drive units in the event of a collision with an obstruction, one particularly preferred embodiment provides for the aircraft to comprise a collision protection device for the rotors. This measure makes it possible, for example, to prevent one of the rotors from breaking on contact with an obstruction. 
     In order to simplify the disassembly of the aircraft, it is possible in one advantageous embodiment for the collision protection device to be detachably fitted to the support, in particular to be detachably fitted to the supporting arms. For example, one or more plug or clip connections can be provided in order to detachably fit the collision protection device to the supporting arms. 
     In one advantageous embodiment, the collision protection device may comprise at least one rotor protection ring which extends along the outer circumference of the aircraft. For example, it is also possible for the collision protection device to comprise a first rotor protection ring and a second rotor protection ring, which extend along the outer circumference of the aircraft. In a further variant, more than two rotor protection rings may also be provided. The rotor protection ring or rings may, for example, be produced from plastic. 
     The rotor protection rings are preferably oriented essentially parallel to one another. Furthermore, the rotor protection rings can be connected to one another by a number of holding crossmembers. The holding crossmembers, which preferably extend orthogonally with respect to the plane of the rotor protection rings, can be detachably fitted to the supporting arms. 
     In order to prevent damage to the aircraft during landing, in one advantageous embodiment it is possible to provide for the aircraft to have a landing frame which can preferably be plugged on, and is therefore designed to be detachable. 
     Different payloads can be transported with the aid of the aircraft proposed here. For example, the aircraft can be used to transport one or more cameras and/or sensors for environmental analysis, in order to take airborne photographs, or to record environmental analysis data. 
     In order to allow the payloads, which can be transported by means of the aircraft, to be interchanged in a simple manner, one particularly advantageous embodiment proposes that the aircraft have an interchangeable payload module. 
    
    
     
       Further features and advantages of the present invention will become evident from the following description of preferred exemplary embodiments and with reference to the attached figures, in which: 
       BRIEF DESCRIPTION OF THE SEVERAL VIEWS OF THE DRAWING 
         FIG. 1  shows a schematic illustration of the basic functional principle of an aircraft according to the present invention; 
         FIG. 2  shows a perspective view of an aircraft according to one preferred exemplary embodiment of the present invention. 
     
    
    
     DESCRIPTION OF THE INVENTION 
     First of all, reference is made to  FIG. 1 , which schematically illustrates, in a highly simplified form, the basic functional principle of an aircraft  1  which is designed according to the present invention as a so-called microdrone. 
     The aircraft  1  has a support  2  which, in this exemplary embodiment, has three supporting arms  20 ,  21 ,  22  which extend outwards in the radial direction from a common centerpoint. A respective drive unit  30 ,  31 ,  32  is arranged on each of the three supporting arms  20 ,  21 ,  22 . Each of the three drive units  30 ,  31 ,  32  comprises a first rotor  40  and a second rotor  41 , which are indicated only schematically as ellipses in  FIG. 1 . As can be seen, the first and second rotors  40 ,  41  of the drive units  30 ,  31 ,  32  are each arranged coaxially in this exemplary embodiment. The first and second rotors  40 ,  41  of the drive units  30 ,  31 ,  32  are in this case separated from one another in the axial direction such that, during operation of the aircraft  1 , the first rotors  40  of all the drive units  30 ,  31 ,  32  rotate jointly on a first rotation plane  11 , and the second rotors  41 , rotate jointly on a second rotation plane  12 , which is oriented essentially parallel to the first rotation plane  11 . 
     Each of the three drive units  30 ,  31 ,  32  in this exemplary embodiment has two electric motors  50 ,  51 , whose rotation speed is controlled and which preferably have no transmission, and which in particular may be electronically commutated direct-current motors. In this exemplary embodiment, an electric motor  50 ,  51  whose rotation speed is controlled is therefore in each case associated with each rotor  40 ,  41  of the drive units  30 ,  31 . 
     During operation of the aircraft  1 , the first rotors  40  and the second rotors  41  of the drive units  30 ,  31  rotate in opposite directions. As is indicated by arrows in  FIG. 1 , the first rotors  40  of the three drive units  30 ,  31 ,  32  may, for example, rotate in the counterclockwise direction on the rotation plane  11 , while their second rotors  41  rotate in the clockwise direction on the rotation plane  12 . 
     Both the position and the movement of the aircraft  1  can be controlled by individual setting of the rotation speeds of the electrics motors  50 ,  51  of each of the three drive units  30 ,  31 ,  32 . For this purpose, the aircraft  1  has a central control unit, which is not shown explicitly here, that is coupled to the electric motors  50 ,  51  whose rotation speeds are controlled, such that they can be operated individually. Each electric motor  50 ,  51  preferably has an associated rotation-speed controller, which is connected to the central control unit such that the rotation speeds of all the electric motors  50 ,  51  of the drive units  30 ,  31 ,  32  can be varied on an individually controlled basis. Suitable sensor means are provided in order to record flight data and operating data of the aircraft  1 , and these will be described in more detail further below. 
     Autonomous attitude and position control of the aircraft  1  can be achieved by the measures described above and by appropriate design of the programming software of the central control unit. The aircraft  1  proposed here may, for example, carry out hovering flight. The central control unit allows controllability of the aircraft  1  in all three spatial directions and, furthermore, rotation of the aircraft  1  about its vertical axis. This is done by individual variation and matching of the rotation speeds of the electric motors  50 ,  51  of the drive units  30 ,  31 ,  32  to the respective flight situation. 
     The physical design of the aircraft  1  with three drive units  30 ,  31 ,  32 , each having two coaxially arranged rotors  40 ,  41  which rotate in opposite rotation directions during operation makes it possible to provide an aircraft  1  which is physically more compact than the aircraft which are known from the prior art and normally have four or more drive units. This makes it possible to move a large payload over a comparatively long flight time. The provision of two electric motors  50 ,  51 , whose rotation speeds are controlled, per drive unit  30 ,  31  furthermore has the advantage that the aircraft  1  has improved redundancy. For example, if one of the electric motors  50 ,  51 , whose rotation speeds are controlled, of one of the drive units  30 ,  31 ,  32  fails, the second electric motor  50 ,  51  can still provide sufficient thrust in order to prevent the aircraft  1  from becoming uncontrollable and, for example, crashing. 
     As already mentioned above, the aircraft  1  has a plurality of sensor means in order, for example, to allow the position of the aircraft  1  and the current flight data and operating data to be recorded. For example, the aircraft  1  may have one or more of the sensor means (also in combination) mentioned below:
         rotation rate sensors,   acceleration sensors,   barometric sensors,   magnetometric sensors,   Ultrasound sensors,   GPS sensors,   optical sensors.       

     The measurement data recorded by the sensor means during operation of the aircraft  1  is supplied to the central control unit and is processed further by the latter. If necessary, the central control unit then sends individual control signals to the electric motors  50 ,  51 ,  52  of the drive units  30 ,  31 ,  32  in order to individually vary their rotation speeds. 
     The aircraft  1  proposed here can be used to transport different payloads, for example one or more cameras or sensors for recording environmental data (gas sensors, radiological sensors or the like). The aircraft  1  preferably has an interchangeable payload module which, in particular, is detachably fitted to the support  2  in order that the payload can easily and quickly be interchanged. 
     Furthermore, the aircraft  1  comprises transmitter and receiver means which are suitable for transmitting data (for example a video signal from the camera and/or sensor signals) from the aircraft  1  to ground transmitting and receiving station, and/or for receiving control signals from a ground transmitting and receiving station. 
       FIG. 2  shows a perspective illustration of one preferred exemplary embodiment of the aircraft  1 , which is illustrated only schematically and in a highly simplified form in  FIG. 1 . The aircraft  1  is a microdrone which is designed such that its physical size is so compact that, for example, it can even fly into a building. 
     The figure once again shows a support  2  which, in this exemplary embodiment, has a central essentially cylindrical base body  23 . Three supporting arms  20 ,  21 ,  22  are fitted to an outer envelope surface of the base body  23  and extend away from the base body  23  in the radial direction. In order to allow the aircraft  1  to be disassembled again if required, the three supporting arms  20 ,  21 ,  22  are detachably fitted to the base body  23  in this exemplary embodiment. In order to simplify assembly and disassembly of the aircraft  1 , the supporting arms  20 ,  21 ,  22  can preferably be fitted in an interlocking manner to the base body  23 , with the aid of quick-release fasteners. 
     Once again, one of a total of three drive units  30 ,  31 ,  32  is fitted to each of the three supporting arms  20 ,  21 ,  22 . Each of the three drive units  30 ,  31 ,  32  in each case comprises a first two-bladed rotor  40  and a second two-bladed rotor  41 , which is separated from the first rotor  40 . The two rotors  40 ,  41  of the drive units  30 ,  31 ,  32  are each arranged coaxially one above the other while, during operation of the aircraft  1  on the basis of the basic functional principle as explained above with reference to  FIG. 1 , the first rotors  40  of all the drive units  30 ,  31 ,  32  rotate on a common rotation plane, and the second rotors  41  of the drive units  30 ,  31 ,  32  likewise rotate on a common rotation plane. 
     Each of the three drive units  30 ,  31 ,  32  has two electric motors  50 ,  51 , whose rotation speeds are controlled and which are each associated with one of the two rotors  40 ,  41  and drive them independently of one another, and cause them to rotate, during operation of the aircraft  1 . The electric motors  50 ,  51  whose rotation speeds are controlled are preferably designed without any transmission and can, in particular, be electronically commutated direct-current motors. As already mentioned above, the first rotors  40  of the drive units  30 ,  31 ,  32  are each driven in the opposite directions to the second rotors  41  during operation of the aircraft  1 . The direct-current motors  50 ,  51  are operated individually by the central control unit of the aircraft  1  in order, if required, to vary their rotation speeds. 
     In order to simplify the fitting of the rotors  40 ,  41  to the supporting arms  20 ,  21 ,  22 , assembly means which require no tools can preferably be provided. For example, grooves can be provided with an O-ring, with the grooves each extending around a driver pin of the electric motors  50 ,  51 . The base body  23  may, for example, have an electrical identification for coding of the electric motors  50 ,  51  in order in this way to simplify assembly of the aircraft  1 . 
     Furthermore, the aircraft  1  has a housing  7  in which, for example, the payload, such as a camera, sensors for the recording of environmental data or the like, can be accommodated. 
     By way of example, the central control unit, one or more sensor means as well as transmitter and receiver means can be accommodated in the housing  7  or in the base body  23  of the support  1 . 
     In order to allow the position and current flight data of the aircraft  1  to be recorded, the aircraft  1  has one or more of the sensor means (also in combination) listed by way of example below:
         rotation rate sensors,   acceleration sensors,   barometric sensors,   magnetometric sensors,   Ultrasound sensors,   GPS sensors,   optical sensors.       

     In order to make it possible to avoid damage to the rotors  40 ,  41  in the event of a collision with an obstruction, the aircraft  1  in this exemplary embodiment has a rotor protection device  6  which extends along the outer circumference of the aircraft  1 . The rotor protection device  6  has a first rotor protection ring  60  and a second rotor protection ring  61 , which are separated from one another in the axial direction with the aid of three holding crossmembers  8 . The two protection rings  60 ,  61  are preferably detachably fitted—for example via a plug connection or clip connection—to the holding crossmembers  8 . The holding crossmembers  8  may themselves likewise be detachably fitted—for example via a plug connection or a clip connection—to the supporting arms  20 ,  21 ,  22 . 
     On its underneath, the aircraft  1  may furthermore have a landing frame, which is not explicitly illustrated here, that can be preferably be plugged on and which, inter alia, can prevent damage to the aircraft  1  during landing.