Flying object

The invention relates to a flying object, in particular a remote-controlled small flying object with at least one supporting surface, with at least one propeller drive pair and one weight, the position of which can be varied along the flying object to change the center of gravity of the flying object, according to the preamble of claim 1.

[0002] Such a flying object is known from WO 2008/007147 A1. In this case, a tilting element under the flying object was embedded as the weight. With proper positioning of this tilting element, it is possible to implement the suspension condition of the flying object. In addition, this flying object is equipped with a supporting structure, a control system and in each case a control surface.

[0003] United States patent application US 2005/0173592 A1 discloses closed carrier elements for aircraft.

[0004] Letter DE 295 02 677 U1 discloses a compact aircraft with bearing panels and front panels that form a closed wing structure. In addition, the document WO 2009/095696 A2 discloses a flying object on which the control panels are axially arranged with a plurality of steering units. The disadvantage here is the fact that such flying objects or small flying objects can only be put into motion after a long trial period. In addition, such flying objects are relatively bulky, e.g. due to the rear boom for the control and / or pivoting arrangement of the weight. The transport of such a flying object is thereby hindered. In addition, there is a danger that this flying object may be easily damaged during transport and / or during unfavorable flight maneuvers.

[0005] Thus, the possibilities of using a flying object, for example as a reconnaissance drift, are significantly reduced.

[0006] Therefore, this problem serves as the basis for the creation of this invention, more specifically the refinements of a remotely controlled small flying object of the type described above, so that a more robust and compact design with improved flight characteristics is realized. Starting from the features of the preamble of patent claim 1, the task will be solved by characteristic features.

[0007] Especially advantageous, in the case of the remote-controlled small flying object according to the invention, is the bearing surface above which there is a plane formed by axes of rotation of the propeller drives for generating lift, in particular for taking off and / or landing.

[0008] Due to this, a very compact construction is possible. In addition, due to the proposed positioning of the bearing surface relative to the propeller drives, a large lifting force is already created at the site, which promotes a very low takeoff and / or landing speed, in particular due to the Custer effect. This flying object is particularly suitable as a vertical launch and / or landing object. The term propeller will also be used instead of the rotor or other forms of aerodynamic engines.

Preferably, the bearing surface is arranged as an upper bearing surface above the lower support surface, wherein in particular the upper bearing surface and the lower bearing surface are integrated to form a hull-free flying object with only one closed bearing panel. In the case of the closed carrier plane design, English also the "closed wing", the upper and lower bearing surface are permanently assigned to two, disposed distal ends of the bearing surfaces, in particular through the total depth of the upper bearing surface and / or the bottom surface a carrier using lateral surfaces, spaced apart. You can give up the hull, such as with conventional flying objects. It's conducive to stable, and thus improved flight behavior. Therefore, a flying object can be controlled more easily. For example, learning how to use such a remote controlled flying object is absorbed faster. In addition, a more compact and durable structure is realized through the closed bearing panel.

[0010] The flying object has a light weight, in particular less than 1 kg. In addition, this flying object is formed essentially of a support panel. This limits the risk of damage to the flying object, in particular unmanned, remotely controlled flying object, during transport and / or unfavorable aerial maneuvers. Preferably, the flying object is made as a flying wing. With the construction of a flying wing or quasi-flying wing, it is avoided to use protruding parts such as the rear boom, which further reduces the risk of damage during transport and / or flight. The upper bearing surface and the lower bearing surface can be positioned completely on top of each other, thus allowing an even more compact design.

[0011] According to a further embodiment, the closed support panel is made as a ring wing or a box wing. Preferably the annular pistol is made as a vertical ring-like shape, in such a way that an open tube and / or open ring is formed in the fore and aft direction of the flight from the front and rear. Ringwinged flippers and rectangular wing are known designs of support flaps that support robust construction and / or stable behavior during flight. In addition, the construction of the bearing brackets of this type exhibits good load-bearing characteristics, so that low starting speeds are possible. The bearing surfaces and / or the support panel can be made of a film that is light and cheap. When using a foil, it can be rolled during transport. When assembled, it is simply unwound and pulled onto the frame of the structure. An alternative or addition to the use of a film may also be the use of carbon fiber or other suitable fiber-reinforced fibers (fiber-reinforced composites). This promotes high stability at low weight.

[0012] According to a further embodiment, the upper bearing surface, the lower bearing surface and / or the support panel are made as rigid, foil or inflatable. The advantage of the rigid construction of the side surfaces and / or the support panel is a particularly stable and durable construction. In an alternative embodiment, the bearing surfaces and / or the support panel can be made inflatable, so that the flying object takes up little space, which facilitates transport. The bearing surfaces and / or the support panel may be designed such that during the flight using an air jet, for example similar to a paraglider, they are made as self-inflating ones or are made of inflatable, closing chambers or tanks. These chambers or tanks may be filled with air or cargo, to provide the propulsion and / or energy supply means to the flying object. For example, the chambers or tanks may contain hydrogen to supply the fuel cell associated with the object.

[0013] Preferably, propeller pairs of propeller drives that serve to generate an air flow above the upper bearing surface and / or the lower bearing surface are located in the length direction before or after both bearing surfaces. Thus, two propellers of two propeller drives are located, in view of the predicted direction of flight, ahead of or behind one or more bearing surfaces and / or a bearing panel. Two or more pairs of propeller drives are preferably provided. Preferably, one or more pairs of propeller drives are coaxially located. During operation, high velocity air is conducted and / or sucked in, over both bearing surfaces of the airfoil, through the rotating propellers already during a standing position or at a very low flight speed of the flying object. As a result, a particularly low start speed is achieved. When laying the upper bearing surface, which is located above the lower support surface, twice as large surface area can be used for generating the drive as compared to the construction with only one bearing surface. Preferably, a flying object in the form of a small flying object can take off from the hand. In particular, this flying object is made as a flying object for vertical takeoff and / or vertical landing (VTOL: vertical take-off and landing). [0014] Preferably, the propeller drive pair is located between the upper bearing surface and the lower bearing surface. As a result, the risk of damage to the propeller drives is reduced, since they are at least partially surrounded by both bearing surfaces and / or the bearing panel. Also, With this type of propeller drive, it is possible to implement small diameters of propellers with simultaneous air flow through the upper and lower bearing surface. [0015] Furthermore, the upper bearing surface and / or the lower bearing surface are located between the axis of rotation of the propeller drive and the maximum spread of the propeller. This ensures that, during operation, high speed air using a propeller is guided over the top face of the lower bearing surface and / or over the upper bearing surface. This favors a low take-off speed, and in particular the formation of a flying object as a flying object for vertical take-off and landing.

[0016] Preferably, the propeller propellers in the circumference of the periphery of the propellers are at least partially surrounded by a propeller shield. This reduces the risk of damage to the propellers during transport and / or during the flight. Propellers of many propeller drives may each time be surrounded by a prop shield, especially as in the case of a duct fan, or the propellers are covered with one common propeller cover. In the case of separate propeller guards, it is possible to connect separate elements of the prop shield with the use of oblique safety supports.

Furthermore, the prop shield can be, with the use of securing pillars, permanently connected to one or more support surfaces or to the support panel, which enhances the robust and compact design. Preferably, the construction of the flying object is made as semi-rigid. Thanks to this, the danger of a resonant effect is significantly reduced. In particular, the support panel lies within the propeller cover. In particular, the maximum height and width of the support panel is determined by the height and width of the propeller shroud.

[0018] Preferably, the static thrust of the enclosed propeller is larger than the static sequence of the non-driven propeller, which further promotes a low start speed. The propeller shield may, for example, have a cylindrical section, in the shape of a tube, identical or similar to the shape of the airfoil or bearing surfaces. Preferably, the support panel has a smaller height than the propeller guard and is moved downwardly relative to the axis of the cover. This promotes air flow through the upper side of the upper bearing surface and / or the lower bearing surface.

[0019] According to a further embodiment, the weight is located centrally, in particular between propeller drives, on the bearing surface. By using a weight, for example, the object is trimmed relative to the transverse axis, in particular to compensate for the different weight distribution. The weight advantageously serves to stabilize opposing gusts and negative aerodynamic effects. In addition, the weight can be used to control the flying object along its transverse axis, which makes it possible to control the flight altitude. In particular, due to the variable position of the weight, it is possible to abandon the rear boom for the control system, such as for example horizontal and / or vertical ballasts.

[0020] The weight can be moved linearly along the flying object along its central axis, or it can be rotated by means of a rotary mechanism about a transverse axis of the flying object, for example using an actuator or an ultrasonic motor. Preferably, the weight is located in particular below the upper support surface and is pivotably mounted about the transverse axis and is connected to the bearing surface and / or the support panel. As a result, the weight and the rotating mechanism are at least partially protected against external influences owing to the upper bearing surface and / or the lower bearing surface or the bearing panel. The weight can be adapted to receive equipment elements, e.g. control, sensors, batteries, payload, etc.

[0021] According to a further embodiment, the control is provided for directing the flying object, in particular using a remote control, wherein the position during flight with respect to the longitudinal axis and / or the height axis of the flying object can be adjusted using the difference between the driving forces, preferably between the number of rotations or the angle of propeller propeller setting. In addition, the in-flight position with respect to the transverse axis can be adjusted by moving the weight. The change of the flight position around the longitudinal axis, the height axis and / or the transverse axis of the flying object is therefore carried out without the control surfaces. Thanks to this, the danger of damage is reducedduring the transport and / or during the flight of the flying object. The position of the flying object in flight is controlled only by the propulsion, more precisely by the number of propeller shaft rotations and by the distribution of the weight along the flying object.

[0022] For control by a number of revolutions, it is necessary that at least one or more pairs of propeller drives are provided. In this case, the propeller drives of a pair of propeller drives are positioned relative to each other as spaced from the center of the flying object in such a way that they are inverted from each other. For example, if the number of revolutions of the first propeller drive is reduced, the driving force generated by the propeller drive also decreases. If at the same time the number of revolutions of the second propeller drive is maintained or increased from the initial level of the first propeller drive, the driving force of the second propeller drive will be greater than the driving force of the first propeller drive. As a result, the flying object rotates about its height axis towards the first propeller drive.

[0023] Preferably, control means and / or energy supply means are included in the support surface or in the bearing pad. As control means, for example, at least one antenna is provided. In addition, or as an alternative, a solar cell may be provided as an energy supply medium. As an energy supply means, an antenna can also be used, the energy being transmitted through microwaves. The batteries can be recharged with the means for energy supply. Preferably, the control means and / or the means for energy supply are made as a transponder, in particular RFID (radiofrequency identification), in particular with a return channel.

[0024] According to an independent and independent form of the invention according to the invention, the energy supply means are made as a field for receiving energy for the laser beam. Thus, for example, the batteries of the flying object can be charged remotely using a laser beam. Preferably, a plurality of energy fields are provided, in particular adjacent to one another. Thanks to such a solution, it is possible to implement self-orienting laser beam guidance, thanks to which the loading process is facilitated. In addition, control with automatic distance control is provided for many energy fields next to each other. This means that the further away is a flying object, the wider the laser beam is and the more radiation fields will be exposed to receive energy. The closer the flying object is, the more concentrated and narrow the laser beam is. This leads to the laser beam getting to a smaller number of fields to receive energy. This effect is useful for adjusting the distance.

[0025] It is particularly advantageous to use the flying object according to the invention as a remotely controlled reconnaissance drone, preferably monitoring means are provided on this reconnaissance drone. As monitoring means, for example, imaging sensors can be attached to the weight, the front edge of the bearing surface and / or the airfoil and / or to the front edge of the propeller guard. Thanks to its compact and lightweight design, the flying object can be conveniently transported by one person, for example in a backpack. In addition, the flight characteristics are stable in such a way that the operation of the drone is manageable in a shorter time than in the case of commonly used flying models. As for the flight characteristics, the low start speed is a special advantage. This allows you to start with your hand, thanks to which the flying object is ready to take off at any time and in any terrain. A special landing gripper is not needed.

[0026] Next, the invention will be explained by means of the given embodiments in connection with the drawings. In addition, further preferred embodiments, advantages and applicability of the invention will be shown using the descriptions, examples and drawings below. Furthermore, all features described and / or represented in the figures are an essential object of the invention in themselves or in any combination, regardless of the representation in the claims or their summary. The content of the claims is also part of the description.

[0027] It is nevertheless pointed out that the invention is by no means limited to the examples given. They present:

Fig. 1 a schematic front view of a flying object according to the invention,

Fig. 2 is a schematic side view of a flying object according to the invention, partly in section, according to Fig. 1, and

Fig. 3 is a schematic plan view of a flying object according to the invention, partly in section, according to Figs. 1 and 2.

[0028] Fig. 1 shows a schematic front view of a flying object according to the invention or a small flying object 10. The flying object 10 is made asymmetrical with respect to the elevation axis 11 and has two propeller drives 12, 13 each with one propeller 14. In the example shown here the propellers 14 in the area of ​​the outer periphery are surrounded by a propeller shield 15. In this case, a single propeller shroud 15 is provided for each propeller 14 of both propeller drives 12, 13. A possible alternative to propellers 14 of propeller drives 12, 13 are separate propeller cover elements that can be connected to each other for stabilization.

[0029] According to the front view according to Fig. 1 or with regard to the predicted flight direction of the flying object 10, a closed support panel 16 is provided behind the propeller shield 15. In the embodiment shown here, the support panel 16 is made as a crow flap 16. A flying object 10 is made without an additional hull, i.e. as hulled. The support flap 16 has an upper bearing surface 17 which is located above the lower bearing surface 18. The height of the support panel 16 is smaller than the height of the propeller shroud 15. In the embodiment herein, the height of the bearing panel 16 is approximately 1/3 smaller than the height of the propeller shield 15.

[0030] Furthermore, the support panel 16 is displaced downwards relative to the propeller shroud 15, starting from a central, symmetrical arrangement. In this case, the nose piece 16 does not protrude, however, beyond the perimeter of the propeller shroud, but remains within this circumference.

To the underside 19 of the upper bearing surface 17, asymmetrical with respect to the elevation axis 11, the propeller drives 12, 13 are spaced from each other. In addition, a weight 20 is provided centrally on the underside 19. The weight 20, in the illustrated embodiment, is attached to the underside 19 by means of a rotary link 21. In this case, this rotary link 21 allows the weight 20 to rotate about the transverse axis 22.

[0032] Fig. 2 is a schematic side view of a flying object 10 according to the invention in a partial cross-section according to Fig. 1. In the embodiment shown, the weight 20 protrudes forward from the propeller shroud 15 in the direction of the flight direction foreseen in this example. The side surface 27, which extends through the common depth of the upper and lower bearing surface 17, 18, is located at the distal ends of the bearing surfaces each.

[0033] On the lateral surface 27 of the bearing panel 15, control means 23 are shown schematically in this case. These control means 23 on the carrier plate 15 are in this case designed as an integrated antenna 23 and serve to receive a control signal for remote control unmanned flying object 10.

[0034] Fig. 3 shows a schematic plan view of a flying object according to the invention in a partial cross-section according to Figs. 1 and 2. On the upper bearing surface 17, for example, a means 24 for receiving energy is shown schematically. This means 24 for receiving energy on the embodiment shown in this case is made as a solar cell 24.

[0035] The flying object 10 is made asymmetrical with respect to the longitudinal axis 25. Furthermore, the upper bearing surface 17 has an asymmetrically arranged cut-out with respect to the longitudinal axis 26. This cutout 26 is made substantially V-shaped and tapers towards the weight 20. The smallest cutting width 26 corresponds to the width of the weight 20 to allow the weight 20 to protrude above the upper bearing surface 17 during rotation of the weight 20 about the transverse axis 22. On the example shown in this case, the lower bearing surface 18 also has a notch 26 which is not shown here in order to allowing the weight 20 to protrude over the lower bearing surface 18 as the weight 20 rotates about the transversal axis 22. [0036] The operation of the flying object 10 will be approximated from Figures 1 to 3:

If the unmanned aerial vehicle 10 is to be used as a reconnaissance drone, it is equipped with appropriate monitoring measures. These monitoring means may be an integral part of the weight 20. The energy required for the functioning of the monitoring means, as well as for the control of the flying object 10 is guaranteed by batteries and / or one or more means 24 for energy supply.

[0037] The size and weight of the flying device 10 is such that the flying device 10 can be transported by one person, for example in a backpack. Control of the flying object 10 takes place using a remote control that can be operated by one person. The remote control signals will be recorded and transmitted by the control means 23.

In this case, the control is carried out in such a way that the flying object 10 is rotated around the longitudinal axis 25 and / or the height axis 11, the propeller drives 12, 13 being driven with a different number of revolutions. Due to these different numbers of rotations of the propeller drives 12, 13, they produce a different driving force, whereby the flying object 10 is rotated about its longitudinal axis 25 and / or its elevation axis 11. In this way it is possible to control the flight direction of the flying object 10.

[0039] In order to control the flight height of the flying object 10, the weight 20 is rotated about the transverse axis 22 of the flying object 10. In this way, the center of gravity of the flying object 10 is moved and depending on the direction of rotation, the flying object 10 is directed in the climb position or in lowering positions.

[0040] Thus, no rudder surfaces are needed to control the flying object 10, whereby the flying object 10 is particularly robust and is also conducive to high readiness for flight. Then you can also abandon the rear boom, which guarantees a compact design.

Due to the fact that the propeller 14 is arranged before or, alternatively, behind the bearing surfaces 17, 18, already during the standing position, the high speed air is conducted above the bearing surfaces 17, 18. This results in a very low speed starting, thanks to which it is possible to take off and land from the hand or hand of the operator.

List of links:

[0042]

Flying object or small flying object 11 Axis of height 12 Propeller drive 13 Propeller drive 14 Propeller

Propeller cover 16 Supporting flap

Top bearing surface 18 Lower bearing surface 19 Bottom side

Weight 21 Swivel connector 22 Transverse axis

Means for control

Means for energy supply

Longitudinal axis

Notch 27 Side surface