Patent Publication Number: US-2015078620-A1

Title: Aircraft, Methods for Providing Optical Information, Method for Transmission of Acoustic Information and Method for Observing or Tracking an Object

Description:
Aircraft, methods for providing optical information, method for transmission of acoustic information and method for observing or tracking an object 
     The present invention relates to an aircraft, particularly an aerostat, a method for providing optical information to a person in the surrounding of the flying aircraft, a method for providing optical information about an object and/or for surveying an object by the aircraft, a method for transmission of acoustic information by the aircraft and a method for observing or tracking an object by the aircraft. 
     Aircraft are machines using support from the air in order to fly in the air. 
     A differentiation of aircraft can be made between aerostats and aerodynes, wherein aerostats use buoyancy to float in the air. Well-known examples of aerostats are the “Zeppelins”. 
     Further developments in that field of technology relate to special applications of the aerostats. 
     Aerostats have the main characteristic of creating buoyancy with a lighter-than-air gas such as helium or hydrogen. The density difference between the lighter-than-air gas and the surrounding air creates buoyancy force that lifts the aerostat or significantly decreases its weight. For this purpose, the lighter-than-air gas must be stored in a container. Such container may be provided as a semi-rigid or rigid construction (airship) or as a non-rigid construction that keeps shape due to overpressure of the inside gas (blimp). 
     Aerostats or aerostatic systems are constructed in different sizes varying from 30 cm to 245 m and in different designs, for example in a cigar-like shape. 
     From U.S. Pat. No. 4,848,705, herewith incorporated by reference, an aircraft designed for use in outer space is known. The aircraft comprises actuation units located on a rigid structure that is characterized by a tetrahedron shape. 
     U.S. Pat. No. 5,082,205, herewith incorporated by reference, discloses an aircraft having a spherical body, wherein the spherical body contains the lighter-than-air-gas. Actuators of the aircraft are positioned outward on the end of a rigid structure in one plane. Obviously, such aircraft is not rotatable around the longitudinal axis. The centre of gravity (CG) is most likely in the lower part of the aircraft, which warrants a defined stability position of the system, particularly an asymptotically stable equilibrium point. 
     U.S. Pat. No. 5,383,627, herewith incorporated by reference, describes an airship characterized by different shapes of the cross sections in each spatial dimension. Thus, the drag coefficient as well as other fluid dynamic properties differ in relation to the movement in different directions. Additionally, mechanical properties such as the principal moments of inertia substantially vary as well depending on the respective spatial dimension. 
     The same applies for the aircraft known from U.S. Pat. No. 7,055,777, herewith incorporated by reference, wherein the center of gravity is also not collocated with the center of buoyancy in the aircraft. Further, actuators are placed in one plane on the surface of the aircraft&#39;s hull. 
     The aircraft described in US 20 070 023 581, herewith incorporated by reference, is able to move straight in space in arbitrary orientations and rotate simultaneously around an arbitrary axis. Keeping stationary in arbitrary positions or orientations is also possible. These functions are realized by six actuation units mounted on a central body. However, that aircraft is not an aerostat. 
     Multi rotor systems as shown in US 20 070 023 581, herewith incorporated by reference, consume a lot of energy to maintain their position in the air and have therefore short flight duration. Additionally, they are dangerous when falling down due to breakdowns or other problems. 
     Fixed-wing aircraft have the disadvantage not being able to perform slow movements or hover. However, existing aerostatic systems are very slow and sensitive to wind. 
     In most existing aerostats the centre of buoyancy is not coincident with the centre of gravity. This results in a stable flight orientation. Changing this orientation requires a considerable amount of energy. 
     Further, most existing aerostat systems do have an ellipsoidal or cigar shape. This design significantly reduces the wind resistance in one direction, but also increases the wind resistance in the directions perpendicular to this main direction as well. Additionally, most airships can easily adjust their yaw angle, but there is also a limited possibility to adjust the pitch angle and the roll angle. 
     Further, various situations are known in which information from and/or an object have to be provided, preferably from or to an elevated position. 
     Based on this background, it is the objective of the invention to provide an aircraft with small power consumption during a long flight time, in combination with flexible maneuverability and the ability to provide or acquire information for or about objects. 
     As a solution of the above mentioned problems an aircraft is provided as claimed in claim  1 . Preferred embodiments of that aircraft are claimed in dependent claims  2  to  11 . 
     Further, it is provided a method for providing optical information to a person in the surrounding of the flying aircraft as claimed in claim  12 , a method for providing optical information about an object and/or surveying of an object by means of the flying aircraft as claimed in claim  13 , a method for transmission of acoustic information by means of the flying aircraft as claimed in claim  14  and a method for observing or tracking an object, wherein the object is observed and/or tracked by a camera of the flying aircraft as claimed in claim  15 . 
     According to the invention, an aircraft is provided having a spherical body that generates buoyancy or which may generate buoyancy when filled with gas, wherein the aircraft further comprises four actuation units arranged on the surface of the body for movement of the aircraft in a translation and/or rotation through the air, and at least one camera arranged on or in the surface of the body. 
     In a preferred embodiment, the spherical body has the shape of a hollow ball filled or fillable with gas lighter than air. Accordingly, the aircraft is an aerostat, having preferable the shape of a blimp, particularly of a balloon. Due to the four actuation units of the aircraft, the aircraft can be moved in an arbitrary direction and/or rotated simultaneously. The camera is directed by rotating the aircraft. 
     Particularly, the arrangement of actuation units on the surface of the body is configured to provide the actuation force of the respective actuation unit at a position having a distance between 101% . . . 120% of the radius of the body, preferably 103% . . . 108%. 
     The body is at least partially filled with gas characterized by a lower density than air. Hence, the buoyancy of the aircraft is based on lighter-than-air-technology/principle. 
     Preferably, the gas is helium. 
     In a preferred embodiment, the gravity F g  and the buoyancy force F b  of the aircraft fulfill the following condition: 
       F g =1 . . . 1,2 F b . 
     Preferably, the aircraft is made marginally heavier than air to allow safe landing in case of motor or electronics breakdown, for example the gravity F g  is 2 . . . 5% stronger than the buoyancy force F b . 
     Preferably, the aircraft&#39;s center of gravity exactly coincides with the center of buoyancy of the aircraft, wherein the center of buoyancy is the position where the resulting buoyancy force acts. The center of gravity is where the resulting gravity force acts. 
     In one embodiment of the aircraft, the four actuation units are positioned in a first tetrahedral alignment on the body. 
     In a preferred solution, the aircraft further comprises at least one energy supply unit, wherein the camera or cameras and the energy supply unit or energy supply units are arranged in a second tetrahedral alignment on and/or in the body. Accordingly, the energy supply unit or units and the camera or a plurality of cameras form together a second tetrahedron. The energy supply unit or units and the camera or a plurality of cameras can be at least a part of a payload of the aircraft, which may comprise additionally or instead sensors, actuators and modules for entertainment and interaction. 
     The energy supply unit may have battery packs, for instance three battery packs. Alternatively, the energy supply unit may have a power supply using fuel cells, solar panels, combustion engines or other solutions. 
     In that embodiment, the center of gravity of the system of actuation units should substantially coincide with the center of gravity of the system of cameras and energy supply units. 
     Preferably, the center of gravity of the system of actuation units exactly coincides with the center of gravity of the system of cameras and energy supply units. 
     That is, the system of actuation units and the payload as mentioned above are arranged in such a manner that the center of gravity (CG) of the aircraft substantially coincides with the center of buoyancy (CB) of the aircraft. 
     This means that if the actuation units are arranged in a first tetrahedral alignment, the center of gravity of the first tetrahedral alignment substantially coincides with the center of gravity of the second tetrahedral alignment. 
     Thus, the center of gravity of the system of actuation units arranged in the first tetrahedral alignment substantially coincides with the center of gravity of the system of cameras and energy supply units arranged in the second tetrahedral alignment. 
     Preferably, the distance between the respective positions of the centers of gravity of the first tetrahedral alignment and the second tetrahedral alignment should be less than 5% of the diameter of the body. A typical size of the body is a diameter of about 2.7 m. 
     In a preferred embodiment, a respective actuation unit has a propeller and a motor connected to the propeller. 
     An arrangement of the shaft of the propeller substantially perpendicular related to a radial axis extending radially with regard to the body is advantageous, wherein the shaft of the propeller is also rotatable about the radial axis. Particularly, the blades of the propeller are rotatable about the propeller shaft, wherein the shaft is substantially perpendicular, preferably exact perpendicular, with regard to a radial axis perpendicular to a fictive plane extending tangentially to the surface of the body. Further, the shaft is rotatable about that radial axis in order to direct the thrust of the propeller in a desired direction parallel to a tangent on the surface of the body at the position of the actuation unit. 
     In order to adjust the rotation angle of the propeller axis, the actuation unit comprises an angle adjusting means. Thus, the direction of the thrust generated by the respective propeller is adjustable. Hence, the aircraft can be accelerated in a translation and/or rotation movement simultaneously by the four propellers. 
     Furthermore, a system of a plurality of aircraft is provided, wherein the plurality of aircraft forms a swarm. 
     A further aspect of the present invention is a method for providing optical information to a person in the surrounding of the flying aircraft, wherein an image is projected onto the inner surface of the hollow body in such manner that the image is visible on the outer surface of the body. This can be achieved by a projector in the hollow body projecting an image or movie onto the inside of the hull of the body. Due to transparency of the hull, the image is visible from the outside of the body. In a similar way, an optical information can be provided by projecting an image onto the outer surface of the hull by one or more beamers positioned outside the aircraft, especially on the ground. 
     Further, a method for providing optical information about an object and/or surveying an object is provided, wherein an image of the object is recorded by a camera of the flying aircraft. In case of surveying or measuring an object, the dimensions of the object shown in the image are used for surveying. Taking optical information and/or surveying may be carried out with static or moving objects. 
     A further aspect of the invention is a method for transmission of acoustic information by means of the flying aircraft, wherein the aircraft comprises at least one microphone and/or a loudspeaker, and acoustic information is provided by the loudspeaker of the aircraft and/or acoustic information is recorded by the microphone of the aircraft. 
     Especially in case of providing acoustic information by the loudspeaker, the aircraft may be used as a guide. 
     The invention also relates to a method for observing or tracking an object, wherein the object is observed and/or tracked by a camera of the flying aircraft. The information about the object and/or its movement is transferred by the aircraft. 
     The advantages of the aircraft according to the invention are as follows: 
     A flying camera is provided, having the following properties:
         good wind resistance; i.e. flight manoeuvres are possible up to wind of Beaufort 2,   high agility; i.e. arbitrary combinations of translation and rotation in three-dimensional space are possible. Also hovering and slow movement may be carried out in order to enable image capturing of the surrounding,   sufficient loading capacity; i.e. enough payload for a good camera used for capturing aerial images or other equipments as well as fast electronics and/or storage devices. The storage device should have a capacity at least for 1 h of HD video,   small energy consumption; i.e. long flight time. Due to buoyancy, the present aircraft should have a flight time of at least one hour and preferably much longer,   safety; i.e. small risk of damage of persons, objects and the aircraft itself. The system is safe enough to fly over a crowd.       

     Further, the aircraft should be locatable by GPS. Preferably, the aircraft should be able to follow GPS waypoints. 
     In a special embodiment, the aircraft comprises more than four actuation units arranged on the surface of the body for movement of the aircraft in a translation and/or rotation through the air. Further, the aircraft may be provided without a camera. 
     In a preferred embodiment, the centre of gravity of the proposed system coincides with the centre of buoyancy. Therefore, arbitrary orientations are possible with very little energetic effort. Further, the proposed system has a spherical hull resulting insubstantially equal fluid dynamic properties in any direction. The proposed system can take every position in any of the three angles and maintain it. 
     A major advantage of the proposed system is the long flight time compared to other systems with similar characteristics. It is achieved by the helium-filled hull that generates a lift due to the smaller density of helium compared to the one of air. 
     In comparison to multi rotor systems or fixed-wing systems, the actuators do not need to generate the lift, which leads to less power consumption and therefore a long flight time. The product is made slightly heavier than air to allow safe landing in case of motor or electronics breakdown. 
     Preferably, the hull has two valves, one large valve usable for fast deflation and one small valve equipped with a bung usable for inflation. The large valve is sealed with a rope and is the entry place for a inner pressure sensor, which monitors inner pressure constantly for safety reasons. 
     The energy supply is provided by three battery packs; alternatively power supply using fuel cells, solar panels, combustion engines or other solutions would be possible. As no lift has to be generated to stay in the air despite gravity influence, less actuation power is needed resulting in longer flight time and a decreased noise level due to actuation when compared to other systems. This is very desirable for many applications. 
     Another benefit of the aerostatic design concerns the safety. In case of breakdown, the weight of the system is still zero or slightly above leading to a smaller resulting crash damage in comparison to other systems. This is especially important for applications where the system is used above people or animals or sensitive environments. 
     In addition to the aerostatic concept another major property contributes to the system&#39;s performance. The proposed system is preferably designed to have very similar, ideally identical properties in all directions of space. This especially applies for the following properties: 
     The centre of buoyancy and the centre of gravity are coincident. For a perfect sphere the centre of buoyancy is exactly the centre of the sphere, resulting in that no torques act on the system regardless of its orientation in the gravity field. Therefore, the system is stable but not asymptotically stable. Small disturbances such as wind result in movements that have to be compensated by the actuators if the position shall be maintained. For this reason a control system is implemented, which is explained in more detail below. 
     The three principal moments of inertia are very similar, ideally identical. Accordingly, rotational properties are equal in every direction of space, i.e. the inertia moments are identical and there are no cross-couplings. These would result in unstable rotational directions and other problems. 
     The efficiency of the actuation system is evenly distributed in every direction of space, i.e. rotational and translational movements can be performed with the same efficiency in every direction of space. This property is achieved by the tetrahedral motor alignment, which is explained in more detail below. 
     The maximum resulting forces and torques of the actuation units are very similar in every spatial direction. Also, this property is achieved by the tetrahedral motor alignment. 
     In a three-dimensional space, six degrees of freedom (DoF) are available. The actuation units of the aircraft can be rotated about an axis perpendicular to the body surface, and their thrust can be adjusted. Therefore, they have two degrees of freedom. To acquire six degrees of freedom, three actuation units are required in order to move the aircraft along one of the three axes and rotate about one of the axes simultaneously. 
     However, in order to optimize the movements and for fail-safety it is preferred to use four actuation units. 
     In order to guarantee very similar translational and rotation efficiencies in every direction of space, a tetrahedral alignment of those four actuation units was chosen, i.e. they are located on the vertices of an imaginary tetrahedron of maximal size that is inserted into the spherical hull. 
     As eight degrees of freedom are available, two degrees of freedom are remaining for every non-singular direction. Therefore, optimizations regarding the motor allocation (e.g. direction and strength of thrust of each actuation unit) can be made. 
     A usual real flying system is made out of discrete components such as motors or electronic devices. Their masses are usually concentrated in very small volumes and cannot be distributed on larger areas. To achieve omnidirectionality as described above, a method is needed to place discrete mass points on a spherical surface. The aircraft according to the invention has a centre of gravity located in the middle of the sphere and identical principal moments of inertia. Even distribution of the mass points is required to achieve such a configuration. 
     Such a distribution is realized by insertion of an imaginary tetrahedron of maximal size into a hollow sphere, wherein the mass points are placed on its four vertices and on the hull surface. 
     The aircraft according to the invention comprises two such tetrahedrons. The four identical actuation units are located on the vertices of the first tetrahedron. The three accumulators and an electronic platform of very similar, ideally identical weights are placed on the vertices of the second tetrahedron. The weights of other small components on the hull such as handles, valves or cables are compensated by positioning based on an algorithm, wherein the masses and/or their positions on the edge points are slightly changed. 
     With the alignment described above it is possible to decouple translation and rotation completely. This is important because on the basis of this property the camera can be directed in an arbitrary direction regardless of the current flight trajectory. The system is arranged for automated flying. For instance, the aircraft can be programmed to fly around an object while simultaneously rotating to keep the camera directed at the object. The imagery can be automatically analyzed to find a moving object, and the aircraft can be automatically directed to move straight and/or rotate in order to keep the camera focused on the moving object. 
     An important distinction to other systems is also that images of the scenery above the objects can be taken. 
     As the system is stable but not asymptotically stable, a control system is needed in order to stabilize it. Small disturbances such as wind must be compensated. 
     The control system is realized by the actuation units acting as actuators and various sensors on the hull surface. They include magnetoscopes, gyroscopic sensors, pressure sensors, temperature sensors, GPS sensors and acceleration sensors. 
     In order to steer eight degrees of freedom simultaneously, algorithms are needed for the handling of the system. Therefore, different control modes are implemented which permit controlling the trajectories and the orientation of the system using tablet computers with touch screens, 3D-mouses and RC-devices. Manual modes, direct control and assisted modes, e.g. working with GPS waypoints are available. A three-channel communication concept is implemented. Piloting is possible via a Xbee link from the ground station laptop to the aircraft. As a safety backup, a signal of a standard remote control can always bypass the laptop signal. 
     Image transmission is done by Wi-Fi. As image streaming is always done with lossy compression, a solid state disk on board of the aircraft stores high quality images uncompressed to guarantee best quality for vision algorithms. 
     The first communication channel is RC. This robust technology is used for emergency control. Xbee is characterized by long range and enough data rate to transmit control commands and telemetry. Wi-Fi is used for the transport of imagery due to its high bandwidth. This combination provides high safety and flexibility in use. 
     As the system is safe, it can be used for flying over people in different situations without compromising their safety. This ability is important for the applications such as taking souvenir images or movies of people in amusement parks; flying over crowds at events or in amusement parks to record statistical data or to provide images for human controllers (surveillance tasks), or interaction applications with people such as motion detection, communication with people, tracking people or objects. 
     The necessary equipment for the last point, e.g. loudspeakers or microphones can easily be integrated. The aircraft may also carry an advertisement message. 
     Due to its special appearance, the aircraft attracts the attentions of humans. 
    
    
     
       In the following, the present invention is described with regard to the examples shown in the attached illustrations. 
         FIG. 1  shows the aircraft of the present invention together with the tetrahedral alignments, 
         FIG. 2  shows a side view onto the aircraft, 
         FIG. 3  shows a perspective viewing of the actuation unit of the aircraft, 
         FIG. 4  shows the aircraft taking optical information of an object, and 
         FIG. 5  shows the aircraft flying above a crowd. 
     
    
    
     The preferred embodiment of the aircraft is a spherical body  10  or blimp with a non-rigid structure shown in  FIGS. 1 and 2 . The aircraft is moved using the thrust generated by actuation units  20 , wherein in  FIG. 1  only the positions of the actuation units  20  are shown but no details of the actuation units. There are all in all four actuation units  20  on the surface  12  of the spherical body  10 , arranged in a first tetrahedron or first tetrahedral alignment  40 . 
     Each of the actuation units  20  comprises a propeller  21 , as shown in  FIG. 3 . 
     The propellers  21  can thrust tangentially to the spherical body  10 , and have two degrees of freedom. The magnitude of the thrust or actuation force  26  can be adjusted by an angle adjusting means  27 , wherein a position motor  29  adjusts the direction of the thrust tangential to the hull  11  by rotating a position shaft  28 . A slip ring  31  or coiling cables (which can be n-times wound) transmit the electrical power and signals through the position shaft  28  from energy supply units  60  or accumulators fixed on the hull  11  (blimp-static) to the thrust motor  24  that rotates. The momentum is transmitted from the position motor  29  to the position shaft  28  by a gear mechanism  32 . 
     Thus, the actuation units  20  never have to be turned back into the initial position, i.e. only little delays in the actuation system may arise. However, the usage of only n-times rotatable servo motors is not excluded from the invention. 
     The direction of thrust can be changed due to the ability of the actuation unit  20  to rotate around the radial axis  25  positioned radially to the centre of the spherical body  10 . In addition to the actuation units  20 , an electronic unit  70  is placed on the hull  11 . It includes fast electronics such as a central processing unit and sensors. Energy supply units  60  or accumulators are also provided. The electronic unit  70  and the accumulators form a second tetrahedron or second tetrahedral alignment  80 . In order to take imagery in every direction of space, the whole system is reoriented. The camera  50  or cameras are connected rigidly to the system and are not movable. The aircraft can be compared to an eye, wherein the pupil can be compared to the camera  50  and the eyeball is the lighter-than-air-gas-filled hull  11 . In order to redirect the eye, not the pupil is moved but the whole eyeball is redirected. 
     The aircraft can move straight in every direction of space and is able to simultaneously rotate around every axis in three-dimensional space. There is no coupling between the translational and the rotational movement. Due to the spherical shape, the tetrahedral alignment of motors and the weight distribution on the hull  11 , the mechanical properties in different directions are very similar, ideally identical. 
     This means that the centre of gravity CG exactly is located in the centre of the spherical body  10 , thus no torque is acting on the system in regard to the center of the sphere. In a non-ideal system this does not apply for the geometric center of the sphere but for the center of buoyancy (CB). As there is no gravitational moment of force acting on the system and no asymptotically stable position, all orientations in space are stable but not asymptotically stable. Thus, the system is able to keep stationary in the air in arbitrary positions with very little, ideally no, energy consumption. 
     Another consequence of the weight distribution on the hull  11  is that the principal moments of inertia are very similar, ideally identical in every direction of space. This means that rotational properties are identical for every rotational axis. As a result, some mechanical phenomena such as unstable rotational axis do not occur in this system. 
     Due to the spherical shape and the motor alignment, the fluid dynamic properties such as the drag coefficient are very similar in every direction of space. Another idea is to use impellers instead of propellers  21 . The impellers are considerably smaller and already offer a kind of protection ring, thereby reducing the weight of the actuation units. A further embodiment of an actuation unit is a jet engine. 
     Further, the actuation units may be provided in the surface of the body instead of on the surface. 
     The spherical hull  11  preferably comprises a double membrane, wherein the inner membrane is made out of polyurethane, which is helium impermeable and elastic, and the outer membrane is made of Nylon, which is robust, inextensible and producible by sewing. The inner pressure is slightly higher than the ambient pressure (about 15 mbar). 
       FIG. 3  shows a perspective viewing of the actuation unit  20  of the aircraft. 
     The actuation unit  20  comprises a propeller  21  mounted on a shaft  23  forming the propeller axis  22 , a thrust motor  24 , a protection ring  33  and an angle adjusting means  27 . 
     The angle adjusting means  27  comprises a position shaft  28 , a position motor  29 , a motor platform  30 , a gear mechanism  32  and a slip ring  31 . 
     The propeller  11  is driven by the thrust motor via the shaft  23  in order to create the thrust of actuation force  26 . The protection ring  33  is stringed with carbon wires in order to prevent any objects to come in contact with the propeller  21 , which increases the safety of the system. 
     In order to change the direction of the actuation force  26 , the actuation unit  20  comprises an angle adjusting means  27  coupled to the propeller  11  by the position shaft  28 . 
     The position motor  29  of the angle adjusting means  27  drives a gear mechanism  32 , which provides a torque to the positioning shaft  28  turning the actuation unit  20  about a radial axis  25 . Thus, the position motor  29  adjusts the direction of the thrust tangential to the hull  11  by rotating the position shaft  28 . A slip ring  31  transmits the electrical power and signals through the position shaft  28  from accumulators fixed on the hull  11  (blimp-static) to the thrust motor  24  driving the propeller  21 . 
     The slip ring  31  enables the actuation unit  20  to point in every desired direction without any constraints. An infinite number of rotations in the same direction is possible. 
     An important application of the system is taking aerial imagery of objects  100  such as natural environments, e.g. trees and forests, as shown in  FIG. 5 . These can be used for a three dimensional reconstruction later on. Apart from static objects  100 , moving objects can also be recorded. Further, the system can be used for performing inspection tasks, e.g. in tunnels or under bridges due to its ability to take images of objects  100  out of arbitrary directions. 
     The safety of the system and also its low noise when compared to usual multi rotor systems allow performing surveillance and tracking tasks of animals in parks or natural environments with the system. This means, due to the system&#39;s silent motion and safe construction, animals are neither endangered nor scared. Therefore it is ideal for observing wild life in parks. Additionally, taking imagery from very unusual perspectives becomes possible with the aircraft according to the invention. 
     The unique appearance and its excellent rotation abilities allow the aircraft to perform complex aerial manoeuvres. Such manoeuvres could be performed in swarms of smaller systems or by single aircraft. Aerial performances can also be realized for advertising. 
     Additionally to performances, the shape of the spherical body  10  also allows the aircraft to act as a display, wherein an image is projected from the inside of the hull  11  or from the ground. Here, advertisement applications are possible, too. 
     The aerial display and the aerial swarm display are applications that can be performed by this aircraft in a much better way than by prior art systems. Rotations are easy and can be performed very fast. 
     Equipped with microphones and loudspeakers, the system could be used as a robotic city or nature guide. The system can lead a customer to locations of interest and provide information. Such application may also comprise that the aircraft is positioned at a fixed location, where customers pay. After payment, the aircraft then leads the customer to locations of interest and provides information. Objects of interest and details could be highlighted by the aircraft. 
     As shown in  FIG. 6 , big events can be video recorded safely from above as the aircraft flies above the crowd  90 . 
     LIST OF REFERENCE SIGNS 
     spherical body  10   
     hull  11   
     surface  12   
     actuation unit  20   
     propeller  21   
     propeller axis  22   
     shaft  23   
     thrust motor  24   
     radial axis  25   
     actuation force  26   
     angle adjusting means  27   
     position shaft  28   
     position motor  29   
     motor platform  30   
     slip ring  31   
     gear mechanism  32   
     protection ring  33   
     first tetrahedral alignment  40   
     camera  50   
     energy supply unit  60   
     electronic unit  70   
     second tetrahedral alignment  80   
     crowd  90   
     object  100   
     gravity force F g    
     buoyancy force F b    
     center of gravity CG 
     center of buoyancy CB