DE102021200311A1 - VTOL Vehicle Propeller Assemblies Retainer, VTOL Vehicle Propeller Assemblies Retainer System, VTOL Vehicle - Google Patents

Abstract

The invention relates to a holding device for propeller assemblies of VTOL vehicles, a holding device system for propeller assemblies of VTOL vehicles and a VTOL vehicle with at least one such holding device and/or at least one such system. It is provided that a deformable and/or adjustable holding device (12) provided for propeller assemblies (20) of VTOL vehicles (10). When arranged on a VTOL vehicle (10), the holding device (12) can be deformed and/or adjusted from a first position into at least one second position, so that a propeller arrangement (20) arranged on the device (12) can be moved from a first flight operating position can be changed into at least one second flight operating position. In addition, a holding device system for propeller arrangements (20) of VTOL vehicles (10) and such a VTOL vehicle (10) is presented.

Description

The invention relates to a holding device for propeller arrangements of VTOL vehicles, a holding device system for propeller arrangements of VTOL vehicles and a VTOL vehicle with at least one such holding device and/or at least one such system.

In the future, new mobility concepts will increasingly be designed and designed using a wide variety of flying objects, with special flying objects being available in particular for shorter distances and smaller transport units to be moved. Such flying objects are increasingly able to take off and land vertically, with semi-autonomous operation also being possible.

These so-called VTOL flying objects (VTOL=Vertical Take-Off and Landing) can be, for example, airplanes, drones, rockets or similar flying objects or mixed forms thereof. Such flying objects have, among other things, the ability to take off vertically or take off from the ground and land vertically or quasi-vertically without the need for special runways.

An important aspect of such VTOL flying objects or VTOL flying devices is to develop them in such a way that a high degree of maneuverability is guaranteed with stable flight behavior at the same time during a wide variety of flight conditions. This requirement turns out to be demanding and is closely linked to choosing both a clever positioning of the center of gravity and a well-founded arrangement of the propellers.

Since both the optimal positioning of the center of gravity and the optimal arrangement of the propellers vary greatly for the individual flight phases, compromises have to be made when determining these two properties in the development stage.

Until now, the layout of the propellers/rotors has often been determined by the design process. In most cases, attention is paid to an appropriate aerodynamic design of the components, so that as many optimal flight conditions as possible can be provided.

With regard to the choice of the center of gravity, there are already initial approaches that provide a variable center of gravity by means of a movable additional mass. In this case, an additional additional mass is provided on the flying object, which is arranged displaceably so that a different center of gravity is set depending on the position of this additional mass, with these positioning processes being able to be used accordingly for controlling actions.

Examples from the existing state of the art are presented in more detail below.

That's from the pamphlet EP 2 336 022 A2 a changeable duct of a duct fan for a VTOL flying object can be taken as known. This duct is configured to change shape depending on the vehicle's flight mode, thereby improving the thrust per unit of energy for the duct fan.

From the pamphlet U.S. 2019/0061934 systems and processes for winged drone platforms can also be seen as known. Various techniques are provided in particular for winged drone platforms. In an example, a drone can be provided. The drone may include a drone body, multiple wings, multiple bladed propeller assemblies, and a drone controller. The wings can be coupled to the drone body and configured to generate lift when the drone moves in a first direction of travel. The tiltable propeller assemblies can each be carried by one of the blades, can include a propeller and a propeller power plant connected to the propeller, and can be configured to move between at least a first position and a second position. The drone controller may instruct the tiltable propeller assemblies to move between at least the first position and the second position. Additional systems and related methods are also provided.

From the pamphlet EP 3 594 113 A1 a device for adjusting the center of gravity of an aircraft taking off and landing vertically can also be found. The technology presented relates to a device for adjusting the center of gravity of a vertical take-off and landing aircraft based on its current mode of operation. The device may include a movable support movable between a plurality of positions, an energy storage module attached to the movable support, and an actuator connected to the movable support and receiving a control signal indicative of the current mode of operation. The movable support is movable between the different positions by the actuator based on the control signal indicative of a change in the current operating mode, one position having a focus in one Operating mode and a different position associated with a different center of gravity in a different operating mode.

Predetermined shapes of individual components or of entire assemblies of such VTOL vehicles, for example rigid propeller arms or the like, mean that there is a fixed, predetermined direction of thrust relative to a cabin. Thus, different optimal arrangements, for example of the propellers, cannot be flexibly adjusted for the respective flight phases. An optimal arrangement in connection with a hovering flight or a forward turning flight can therefore only be achieved in a rough approximation. Therefore, optimal stability and maneuverability cannot be achieved in each individual flight phase. These circumstances also mean that if one propeller fails, for example, correspondingly high thrust requirements occur or exist on the individual additional propellers in order to ensure maneuverability and, for example, a stable emergency landing. The high thrust requirements result in a high powertrain weight, which has a disadvantageous effect on the maximum possible range, especially in electrically operated VTOL vehicles.

The use of an additional mass or a device which, for example, changes existing components of the aircraft with regard to their installation position in each case to regulate the center of gravity leads to an improvement in maneuverability. However, this improvement comes at the cost of the increase in weight and the resulting reduction in range. If existing components or assemblies are used to shift the center of gravity, a maximum shift of the center of gravity is limited. It can therefore be assumed that this shift cannot be rated as sufficient to ensure optimal maneuverability with stable flight behavior at the same time.

The invention is now based on the object of providing a holding device for propeller arrangements of VTOL vehicles and a holding device system for propeller arrangements of VTOL vehicles, by means of which optimum stability and maneuverability of VTOL vehicles can be flexibly achieved for different flight phases.

In a preferred embodiment of the invention, it is provided that a holding device for propeller arrangements of VTOL vehicles is provided. This holding device comprises a first area for arranging the holding device on a base body of a VTOL vehicle and/or on at least one assembly coupled to the base body of the VTOL vehicle. In addition, this holding device comprises a second area, which is located opposite the first area, for arranging a propeller arrangement. In addition, when it is arranged on the VTOL vehicle, the holding device can be reversibly deformed and/or adjusted in a user-defined manner from a first position into at least one second position, so that a propeller arrangement arranged in the second area can be changed from a first flight operating position into at least one second flight operating position, so that a VTOL vehicle equipped with this holding device can be controlled in a defined manner by means of this holding device.

Such a holding device thus includes any properties to be integrated into a VTOL vehicle, so that basic functionalities of the vehicle can be guaranteed. The basic functionalities of the vehicle include, for example, an overall stable structure and a stable design of all built-in components to ensure safe flight operations. In other words, the holding device presented is always designed in any embodiment such that a stable and reliable arrangement, for example on the base body of the VTOL vehicle, as well as a stable and reliable arrangement of the propeller arrangement is ensured.

Due to the deformability or adjustability and a directly automatic changeability of the arranged propeller arrangement, it is possible to flexibly achieve optimal stability and maneuverability of VTOL vehicles, which have such a holding device with a propeller arrangement arranged thereon, for different flight phases.

Any embodiment variant of an arrangement of the propeller arrangement on the presented holding device is provided in such a way that a change in position of the holding device necessarily causes the desired change in the positioning of the propeller arrangement.

Instead of a propeller arrangement, any drive units that can be exchanged for this purpose can also be arranged on the device, with the connection being carried out in such a way that the functionality presented remains intact.

In this context, a user-defined creation of the functionality is to be understood, for example, as meaning that a position change is actively brought about, for example by a controller tion of the device automatically changing the position of the propeller assembly can be effected. A user-defined reversible deformability can also be caused by a special installation position of the device and a flexible material portion of the device.

Deformability goes beyond a purely mechanical change in the first position, for example. In particular, an initial shape of the holding device can thus be deformed in such a way that a second shape or other shapes that differ from the initial shape are set at least temporarily.

The first and second areas are, for example, spaced apart from one another and connected to one another by means of an intermediate area. It is also conceivable that the areas at the respective ends, which are not intended for the respective arrangement, touch at least partially. For the aforementioned stability of the basic structure of the VTOL vehicle, the areas can be designed differently depending on the use and task of the vehicle.

Due to the flexible, user-defined reversible deformability and/or adjustability of the device and a thereby automatically changing flight operating position of the propeller arrangement arranged in the second area, controllability of the VTOL vehicle can be achieved in a surprisingly simple manner, so that the center of gravity of the vehicle can be varied to any flight situation is adjustable with regard to a respective maximum stability and/or maneuverability and/or an efficiency of an energy reserve for a corresponding range.

In other words, a VTOL vehicle that is equipped with such a holding device can be controlled in a defined manner by means of this holding device, so that optimal settings can be achieved for the respective flight situation. In this way, a flexible response to a wide variety of flight situations is possible, so that no compromises have to be made, such as those that occur with a rigid arrangement of components.

In this way, for example, noise emissions can be reduced due to optimal settings to be made. Optimal flight operations can thus always be guaranteed, so that a range of the VTOL vehicle can be maximized.

A VTL vehicle which has such a holding device can also be converted into efficient flight operation if, for example, a propeller fails. If a propeller fails, it is possible to reposition a propeller arrangement, which is arranged on the VTOL vehicle using the presented holding device, such that lower thrust and power reserves are required to compensate for the failure. Due to the lower thrust and power reserves, an increase in efficiency and thus a maximization of the range can be provided. This is particularly advantageous in the case of a propeller failure, which is relevant to certification.

By deforming or adjusting the holding device, a targeted change in the center of gravity and a change in the respective arranged propeller arrangements can be achieved. This enables an improvement in maneuverability and increased stability in every flight position. In addition, more efficient flight maneuvers and thus gains in range can be achieved through optimal alignment. The flexible adaptation to the respective flight conditions can also lead to a reduction in noise emissions.

The holding device presented can be used both for use with swiveling and fixed propeller arrangements and is suitable or designed for the respective case.

In a further preferred embodiment of the invention, it is provided that a holding device system for propeller arrangements of VTOL vehicles is provided. Such a holding device system comprises at least three holding devices according to one of claims 1 to 6, wherein at least one of the three holding devices is selected from a holding device according to one of claims 3, 5 or 6. The holding device system comprises a control and computing unit which is designed to be coupled with the at least one holding device, which is selected from one of the holding devices according to one of claims 3, 5 or 6, so that a user-defined deformability and/or adjustability of this at least one holding device can be brought about by means of the control and computing unit, so that a respective propeller arrangement arranged in the second area can be changed from a first flight operating position into at least one second flight operating position, so that a VTOL vehicle equipped with this holding device system can thus be controlled in a defined manner by means of the holding device system. The advantages mentioned above also apply, insofar as they can be transferred, to the presented holding device system.

Since at least one holding device is designed to be actively deformable and/or adjustable, the presented holding device system offers a particularly simple and efficient way to flexibly bring about an optimal setting of a center of gravity of the VTOL vehicle and/or an optimal setting of the propeller arrangement, depending on the flight situation. The other holding devices can have passive adjustability/deformability, for example. Examples of more than four holding devices are also conceivable.

The number of holding devices in such a holding device system can be defined, for example, depending on the intended use. For example, four or more holding devices can also be provided. In particular, four holding devices are conceivable, since a wide use of such a holding device system in corresponding VTOL vehicles with four drive units is conceivable.

A further preferred embodiment of the invention provides that a VTOL vehicle is provided which comprises at least one holding device according to one of claims 1 to 6 and/or at least one system according to one of claims 7 to 9. The advantages mentioned above also apply to the presented VTOL vehicle, insofar as they can be transferred.

Further preferred configurations of the invention result from the remaining features mentioned in the dependent claims.

In a further preferred embodiment of the invention, it is provided that the at least one second operational flight position differs from the first operational flight position in at least one plane or differs from the first operational flight position in at least two planes and/or the reversible deformability of the holding device by means of a user-defined Torsional stress of the holding device can be effected and/or wherein the holding device comprises a control unit by means of which the deformability and/or adjustability can be effected.

It is provided, for example, that the deformability and/or the adjustability of the holding device and the associated change in the operational flight position in the simplest form takes place, for example, only in a specific plane.

Based on an installation position of the device, this can result, for example, in a rotational or translational movement of the device, with this movement correspondingly causing the change in the flight operating position, which is also only carried out in a specific plane.

In other words, an at least partial lateral deflection of the device leads to an associated lateral deflection of the propeller arrangement, in each case based on their starting positions. Instead of a lateral deflection, an at least partially vertical deflection is conceivable. For example, an exclusively vertical deflection can be carried out, so that the deformability and/or the adjustability of the holding device and the associated change in the flight operating position only take place in a specific plane. These simple forms are suitable for applications which already manage with a manageable flexibility with regard to the presented functionality of the device. These devices can be implemented cost-effectively with limited material outlay.

A combination of these two examples results in the second flight operation position differing from the first flight operation position in at least two levels. In contrast to the first example, it is therefore possible to implement more setting options, so that more complex reactions to more complex flight situations can also be provided.

A user-defined torsional stress on the holding device can be brought about, for example, by temporarily twisting the two areas in opposite directions. In this way, additional possibilities can be achieved with regard to the second flight operating position, so that the possibilities of an even finer control of the VTOL vehicle, which has such a holding device, result.

The control unit is designed to determine an optimal shape/adjustment of the holding device on the basis of a current flight attitude and a desired flight maneuver and then to effect it. Depending on the complexity, such a determination can be calculated in real time or based on characteristic maps provided by manufacturers. The insert is suitable for both swiveling and fixed propeller arrangements. Such a control unit can be coupled to the VTOL vehicle in any way, so that at least one control command can also be used directly from a corresponding device in the VTOL vehicle or a device controlling the VTOL vehicle for the functionality of the presented holding device.

It is also provided in a further preferred embodiment of the invention that the holding device is at least partially in the first Region and/or at least partially in the second region and/or at least partially between the first and the second region comprises piezoelectric material, so that the user-defined deformability of the holding device can be brought about at least partially by means of an applied electrical voltage.

In other words, an actively controlled deformability can be achieved by means of the piezoelectric material provided in each case, which ensures the targeted deformability when an electrical voltage is applied. This piezoelectric material can, for example, be provided in the form of piezo actuators or in a similar manner. For example, the piezoelectric material is provided in the form of respective piezo elements, so that the desired deformability is achieved due to the interaction of these individual piezo elements.

The use of piezoelectric material enables a particularly fine adjustment of the device, so that a particularly small-scale control of differing flight operating positions can be provided. In addition, the necessary voltage to be applied can thus be effected easily, resulting in a particularly user-friendly holding device during an application, for example during flight operations. Thus, in a surprisingly simple manner, the holding device can be made deformable during flight operations, in order to automatically bring about corresponding flight operation positions of arranged propeller arrangements.

Furthermore, in a further preferred embodiment of the invention it is provided that the holding device comprises elastic material at least partially in the first area and/or at least partially in the second area and/or at least partially between the first and the second area, so that at least partially due to Load during flight operation of the first area and / or the second area and / or an intermediate area between the first and second area, the user-defined deformability of the holding device can be effected.

Depending on the quantity and position of this elastic material in the device, a respective user-defined deformability can be brought about in connection with the loads that occur during flight operations. This type of user-defined deformability is in this respect a passive deformation of the holding device, which, however, can also be provided in a user-defined manner due to the deliberately chosen material arrangement in the holding device. This embodiment offers the advantage that no active control is required, since the desired effect always occurs when the corresponding load occurs during flight operations. In this respect, this embodiment can be produced cost-effectively and offers reliable functionality, since the desired operating states are established on the basis of active physical principles.

In addition, in a further preferred embodiment of the invention, it is provided that the holding device comprises at least one adjustment mechanism, by means of which the holding device can be coupled at least partially to the base body of the VTOL vehicle and/or to the at least one structural unit coupled to the base body of the VTOL vehicle , so that a user-defined adjustability of the holding device can be brought about by means of the adjustment mechanism, at least partially due to a load during flight operation of the first area and/or the second area and/or an intermediate area between the first and second area.

Thus, instead of a deformable functionality, a passive adjustment mechanism for the holding device is also conceivable. A passive adjustment mimic is conceivable, among other things, by guiding a movably suspended holding device, which can also be referred to as a propeller arm, in an obliquely arranged groove or the like under essentially vertical spring tension. A load on the holding device or at least one area of the holding device in the vertical direction then results in a slight, vertical deflection, which in turn results in a pivoting movement of the holding device in an advantageous direction due to the obliquely arranged groove, which results according to the groove alignment. Further explanations for the design of the adjustment mechanism with regard to the trajectory and the trajectory guidance are conceivable. The groove or a comparable receptacle is then provided, for example, in the base body of the VTOL vehicle or in a component that is arranged on the VTOL vehicle. A slight deflection can occur, for example, in the range between 10 and 80 mm. It is true that such a passive adjustment mimic allows only a clearly limited adjustment to a particular flight situation, since the shape or the positioning of the holding device changes solely on the basis of the load. On the other hand, a particularly reliable functionality that is independent of human input commands is thus provided. A complex design and dimensioning is not necessary, as would be necessary when using elastic material.

Such a special adjustment mechanism can be transferred from an activated state to an at least partially blocked state by means of a blocking unit or the like. For example, the transition between these two states can also be imagined to be stepless, so that deflection occurs only to a limited extent as a function of a setting value of the blocking unit. Such a blocking unit can also be provided in any other adjustment mechanism in a correspondingly adapted variant in order to convert the respective adjustment mechanism from an activated state into an at least partially blocked state. Depending on the design of the adjustment mimics, for example the selection of the spring component, a user-defined adjustability can be provided so that the associated functionality only occurs in a defined manner with corresponding loads in flight operations.

In a special form of this adjustment mechanism, controllability by means of a coupled control unit is also conceivable. In other words, a purely passive adjustment option can be effected in this way by means of actuators or the like, for example. It is also conceivable that a controlled blocking unit is provided for this purpose, so that a continuously controllable blocking unit then effects the desired adjustment of the adjustment mechanism.

Furthermore, in another preferred embodiment of the invention, it is provided that the holding device comprises piezoelectric material at least partially in the first region and/or at least partially in the second region and/or at least partially between the first and second regions, so that at least partially by means of an applied electrical voltage, the user-defined deformability of the holding device can be brought about and/or wherein the holding device comprises elastic material at least partially in the first area and/or at least partially in the second area and/or at least partially between the first and the second area, so that at least The user-defined deformability of the holding device can be brought about partly due to a load during flight operation of the first area and/or the second area and/or an intermediate area between the first and second area and/or the holding device being at least est comprises an adjustment mimic, by means of which the holding device can be coupled at least partially to the base body of the VTOL vehicle and/or to the at least one structural unit coupled to the base body of the VTOL vehicle, so that at least partially due to loading in flight operation of the first area and/or or of the second area and/or an intermediate area between the first and second area, a user-defined adjustability of the holding device can be brought about by means of the adjustment mechanism.

To the extent that they can be transferred, the aforementioned advantages also apply to each of these special variants of the holding device presented. The respective hybrid solutions between the individual concepts, which stand alone, also allow a further possibility of numerous further adjustment possibilities, so that a particularly fine adjustment of the arranged propeller arrangement with regard to a current flight situation can be realized by means of such holding devices with several adjustment functionalities.

Furthermore, in a further preferred embodiment of the invention, it is provided that the control and computing unit, which is provided in the holding device system, is also designed to be coupled to a central control and computing unit of a VTOL vehicle on which the holding device system is arranged , So that the user-defined deformability can be triggered based on at least one transmitted piece of information from this central control and computing unit. In this way, the system presented can also be used for control of the VTOL vehicle that goes beyond stabilization or optimization. Other control systems can thus be replaced, so that a greater range of the VTOL vehicle can be achieved due to a lower weight, for example.

Finally, in a further preferred embodiment of the invention, it is provided that in a special variant of the holding device system, the deformability can be brought about by means of at least one piece of information calculated in real time by the control and computing unit. Alternatively, it is conceivable that the at least one piece of transmitted information from the central control and processing unit of the VTOL vehicle can be assigned to a control routine stored in the control and processing unit, so that the desired deformability can be brought about by executing the assigned control routine. An assignment of available control routines offers the advantage of clear scenarios, which are clearly foreseeable and thus support forward-looking and safe flight operations. The control routines provided can be provided in the form of specified characteristic diagrams, which are specified by the manufacturer, for example. User-defined input by a user in advance is also conceivable, with the settings then being selectable in relation to a particular use.

The presented device and the presented system can each be used in connection with any vertical mobility, for example in connection with urban air mobility. Both a mobility for the Transport of people as well as goods of any kind imaginable. In other words, the presented components and the presented VTOL vehicle can be used for air freight transport. For example, the VTOL vehicle may include any personal aircraft functions in the context of vertical mobility. The presented holding devices are designed to support or effect attitude and center of gravity control of a VTOL vehicle on which they are arranged.

Unless stated otherwise in the individual case, the various embodiments of the invention mentioned in this application can advantageously be combined with one another.

• 1 eine schematische Darstellung von einer Draufsicht auf ein VTOL-Fahrzeug mit Haltevorrichtungen in einem ersten Betriebszustand;
• 2 eine schematische Darstellung von einer Draufsicht auf ein VTOL-Fahrzeug mit Haltevorrichtungen in einem zweiten Betriebszustand;
• 3 eine schematische Darstellung von einer Frontsicht auf ein VTOL-Fahrzeug mit Haltevorrichtungen in einem ersten Betriebszustand;
• 4 eine schematische Darstellung von einer Frontsicht auf ein VTOL-Fahrzeug mit Haltevorrichtungen in einem zweiten Betriebszustand;
• 5 eine schematische Darstellung von einer Haltevorrichtung.

The invention is explained below in exemplary embodiments with reference to the associated drawings. Show it:

• 1 a schematic representation of a plan view of a VTOL vehicle with holding devices in a first operating state;
• 2 a schematic representation of a top view of a VTOL vehicle with holding devices in a second operating state;
• 3 a schematic representation of a front view of a VTOL vehicle with holding devices in a first operating state;
• 4 a schematic representation of a front view of a VTOL vehicle with holding devices in a second operating state;
• 5 a schematic representation of a holding device.

1 shows a schematic representation of a plan view of a VTOL vehicle 10 with holding devices 12 in a first operating state. In a variant of such a VTOL vehicle 10 that is not shown in detail, it is conceivable that only three holding devices 12 are provided in a first operating state. In this case, it is also conceivable that the three holding devices 12 are each at the same distance from an adjacent holding device, resulting in a VTOL vehicle 10 that can be controlled particularly reliably. In another variant, also not shown in detail, it is also conceivable that the respective distances between the three holding devices 12 vary as desired, so that a correspondingly advantageous variant can be used depending on the area of application. This can be associated, for example, depending on the additional load to be transported and the associated technical requirements. Other technical features, such as a maximum speed to be reached or the like, can also characterize a corresponding position of the at least three holding devices 12 as advantageous. The respective holding devices 12 are each shown with a first area 14 for arranging the respective holding devices 12 on a base body 16 of the VTOL vehicle 10 and each with a second area 18 present opposite the first area 14 for arranging respective propeller arrangements 20 . When arranged on the VTOL vehicle 10, the holding devices 12 can be reversibly deformed and/or adjusted in a user-defined manner from a first position to at least one second position, so that a respective propeller arrangement 20 arranged in the second region 18 can be moved from a first flight operating position to at least one second flight operating position can be changed, so that the VTOL vehicle 10 can be controlled in a defined manner by means of these holding devices 12 . In an embodiment variant that is not shown in detail, the holding devices 12 can also be arranged on a component that is not shown in detail, which in turn can be arranged on the base body 16 .

In an embodiment variant that is not shown in detail, the holding devices 12 are each part of a holding device system. In other words, such a holding device system, not shown in detail, comprises, for example, at least four holding devices 12 according to one of claims 1 to 6. It is also conceivable that such a holding device system, not shown in detail, comprises, for example, at least three holding devices 12 according to one of claims 1 to 6. It is conceivable that at least one of the four (or the three) holding devices 12 is selected from a holding device 12 according to one of claims 3, 5 or 6. It is also conceivable that such a holding device system not shown in detail has a control not shown in detail. and computing unit, which is designed to be coupled to the at least one holding device 12, which is selected from one of the holding devices 12 according to one of claims 3, 5 or 6, so that the control and computing unit can be used to achieve user-defined deformability and/or Adjustability of this at least one holding device 12 can be effected, so that a respective propeller arrangement 20 arranged in the second area 18 can be changed from a first flight operating position to at least one second flight operating position, so that a VTOL vehicle 10 equipped with this holding device system is thus defined by means of the holding device system is controllable.

2 shows a schematic representation of a plan view of a VTOL vehicle 10 with holding devices 12 in a second operating state. This is the in 1 already presented VTOL vehicle 10, the same reference numerals as in 1 are valid. Relative to the plane of the image, the holding devices 12 shown above are shown deformed in a clockwise direction, so that the respective propeller assemblies 20 arranged in the second area 18 are shown changed from a first flight operating position to at least a second flight operating position, so that the VTOL vehicle 10 can be controlled in a defined manner by means of these holding devices 12 is. This deformability can be brought about, for example, on the basis of piezo material, not shown in detail, in the holding devices 12 . The controllability of this piezo material can be brought about by means of an applied electrical voltage. It is conceivable that control units of the holding devices 12 that are not shown in detail can be used for this. It is also conceivable that the holding devices 12 are coupled to a central processing unit (also not shown) of the VTOL vehicle 10 and that this then effects the deformability. It is also conceivable that the holding devices 12 are components of a higher-level holding device system with control, which then controls the voltage to be applied in order to control the piezo material accordingly for the deformability of the holding devices 12 .

3 shows a schematic representation of a front view of a VTOL vehicle 10 with holding devices 12 in a first operating state. This is the in 1 VTOL vehicle 10 already presented, with the same reference numbers as in 1 are valid. The same functional relationships apply as discussed in the previous figures.

4 shows a schematic representation of a front view of a VTOL vehicle 10 with holding devices 12 in a second operating state. This is the in 1 VTOL vehicle 10 already presented, with the same reference numbers as in 1 are valid. The same functional relationships apply as discussed in the previous figures. The decisive difference is that the deformed holding device 12 (on the left, in relation to the image plane) is deformed upwards, so that a respective propeller arrangement 20 arranged in the second area 18 can be changed from a first flight operating position to at least a second flight operating position, so that the VTOL -Vehicle 10 can be controlled in a defined manner by means of these holding devices 12.

5 shows a schematic representation of a holding device 12. This holding device 12 comprises piezo material, not shown in detail, in particular in a first and second area 14, 18. It is conceivable that when an electrical voltage is applied, the respective areas 14, 18 in can be rotated in opposite directions according to the directional arrows 22 shown, so that a reversible deformability of the holding device 12 can be brought about by means of a user-defined torsional stress on the holding device 12 . A propeller arrangement not shown in detail, which is arranged in the second region 18, can thus be changed from a first flight operating position to at least one second flight operating position, so that a VTOL vehicle 10 equipped with this holding device 12 can be controlled in a defined manner by means of this holding device 12.

Reference List

10

VTOL vehicle

12

holding device

14

first area

16

base body

18

second area

20

propeller arrangement

22

directional arrow

QUOTES INCLUDED IN DESCRIPTION

This list of documents cited by the applicant was generated automatically and is included solely for the better information of the reader. The list is not part of the German patent or utility model application. The DPMA assumes no liability for any errors or omissions.

Patent Literature Cited

• EP 2336022 A2 [0009]
• US2019/0061934 [0010]
• EP 3594113 A1 [0011]

Claims (10)

Holding device (12) for propeller arrangements of VTOL vehicles (10) with a first area for arranging the holding device on a base body (16) of a VTOL vehicle (10) and/or on at least one with the base body (16) of the VTOL vehicle (10) coupled assembly and a second area (18) opposite the first area (14) for arranging a propeller arrangement (20), characterized in that the holding device (12) in an arranged state on the VTOL vehicle (10) from is reversibly deformable and/or adjustable from a first position into at least a second position in a user-defined manner, so that a propeller arrangement (20) arranged in the second region (18) can be changed from a first operational flight position into at least a second operational flight position, so that a holding device (12 ) Equipped VTOL vehicle (10) defined by means of this holding device (12) is controllable. Holding device (12) after claim 1 , wherein the at least one second operational flight position differs from the first operational flight position in at least one plane or differs from the first operational flight position in at least two planes and/or the reversible deformability of the holding device (12) can be effected by means of a user-defined torsional stress on the holding device (12). and/or wherein the holding device (12) comprises a control unit, by means of which the deformability and/or adjustability can be brought about. Holding device (12) according to one of the preceding claims, wherein the holding device (12) comprises piezoelectric material at least partially in the first region and/or at least partially in the second region and/or at least partially between the first and second regions, so that at least partially the user-defined deformability of the holding device (12) can be brought about by means of an applied electrical voltage. Holding device (12) according to one of Claims 1 or 2 , wherein the holding device (12) comprises elastic material at least partially in the first region (14) and/or at least partially in the second region (18) and/or at least partially between the first and second regions (14, 18), so that the user-defined deformability of the holding device (12) can be brought about at least partially due to a load during flight operation of the first area (14) and/or the second area (18) and/or an intermediate area between the first and second area (14, 18). Holding device (12) according to one of Claims 1 or 2 , wherein the holding device (12) comprises at least one adjustment mechanism, by means of which the holding device (12) is at least partially attached to the base body (16) of the VTOL vehicle (10) and/or to the at least one with the base body (16) of the VTOL Vehicle (10) coupled unit can be coupled, so that user-defined adjustability of the holding device (12) can be brought about by means of the adjustment mechanism, at least partially due to a load during flight operation of the first area and/or the second area and/or an intermediate area between the first and second area . Holding device (12) according to one of Claims 1 or 2 , wherein the holding device (12) comprises piezoelectric material at least partially in the first region and/or at least partially in the second region and/or at least partially between the first and second regions, so that at least partially the user-defined deformability of the Holding device (12) can be effected and/or wherein the holding device (12) comprises elastic material at least partially in the first region and/or at least partially in the second region and/or at least partially between the first and second regions, so that at least partially due to a load during flight operation of the first area and/or the second area and/or an intermediate area between the first and second area, the user-defined deformability of the holding device (12) can be brought about and/or wherein the holding device (12) comprises at least one adjustment mechanism, by means of which the halt The device (12) can be coupled at least partially to the base body (16) of the VTOL vehicle (10) and/or to the at least one structural unit coupled to the base body (16) of the VTOL vehicle (10), so that at least partially due to a load during flight operation of the first area and/or the second area and/or an intermediate area between the first and second area, a user-defined adjustability of the holding device (12) can be brought about by means of the adjustment mechanism. Holding device system for propeller assemblies of VTOL vehicles (10) comprising at least three holding devices (12) according to one of Claims 1 until 6 , Wherein at least one of the three holding devices (12) is selected from a holding device (12) according to one of claims 3 , 5 or 6 , wherein the holding device system comprises a control and computing unit, which is designed with the at least one holding device (12), which from one of the holding devices (12) according to one of claims che 3 , 5 or 6 is selected to be coupled, so that a user-defined deformability and/or adjustability of this at least one holding device (12) can be brought about by means of the control and computing unit, so that a respective propeller arrangement arranged in the second area can be moved from a first flight operating position to at least a second flight operating position can be changed, so that a VTOL vehicle (10) equipped with this holding device system can thus be controlled in a defined manner by means of the holding device system. Holding device system according to claim 7 , wherein the control and computing unit is also designed to be coupled to a central control and computing unit of a VTOL vehicle (10) on which the holding device system is arranged, so that on the basis of at least one piece of information transmitted by this central control and computing unit, the user-defined deformability can be triggered. Holding device system according to claim 8 , wherein this deformability can be brought about by means of at least one piece of information calculated in real time by the control and computing unit, or wherein the at least one transmitted piece of information can be assigned to a control routine stored in the control and computing unit, so that this deformability can be brought about by executing the assigned control routine. VTOL vehicle (10) comprising at least one holding device (12) according to one of Claims 1 until 6 and/or comprising at least one system according to one of Claims 7 until 9 .

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