Landing platform for landing a drone

Abstract

In the case of a landing platform (1) for landing a drone (2), it is proposed that the landing platform (1) has a first surface structure (3) which is fastened in an upper region (4) of a frame (5), wherein the first surface structure (3) is at least at a first distance (6) from a standing surface (7) of the landing platform (1), and wherein the first surface structure (3) is predefinably shock-absorbingly arranged with respect to the standing surface (7).

Description

[0001] Landing platform for landing a drone

[0002] The invention relates to a landing platform for landing a drone according to the preamble of claim 1.

[0003] Drones are important aircraft and are used for a variety of purposes. On ships, drones are used in particular for reconnaissance of the surroundings as well as for detailed monitoring of weather and atmospheric conditions.

[0004] Drones are landed on ships in open areas, meaning areas of the ship that are not built upon or otherwise used. On ships equipped with a helicopter landing pad, this is also used for drone operations. While it is possible to pinpoint and navigate to the landing spot with sufficient accuracy when landing a drone on a ship's helicopter landing pad, damage to the drone, or even its total loss, can occur during the landing process. Landing a drone on a ship at sea differs from landing on land. Gusts of wind, slipstream, and especially the ship's movements in the water make a controlled landing difficult. Errors during landing can lead to damage to the drone or even its total loss.Even with ordinary gravity waves, a safe and non-destructive landing of a drone on a helicopter deck is practically impossible.

[0005] For drones operating on land, the possibilities for a safe landing are highly dependent on the local terrain. Uneven ground conditions, such as rocky terrain with numerous sharp edges, can create a situation where a safe or undamaged landing of the drone is impossible from the outset. Especially for military drones carrying weapons systems, an accident in a sharp-edged area can have serious consequences, as it could lead to an explosion or firing of the weapons system, posing a high risk of casualties to nearby friendly troops.The object of the invention is therefore to provide a landing platform for landing a drone of the type mentioned above, with which the aforementioned disadvantages can be avoided, and with which a safe landing of a drone on uneven surfaces, in particular a ship in gravity waves and / or a surface of sharp-edged rocks, can be carried out without loss.

[0006] According to the invention, this is achieved by the features of claim 1.

[0007] This enables the safe landing of a drone on an irregular surface, i.e., a surface that does not maintain a constant position in three-dimensional space during the landing process, and / or which has a high degree of roughness. Specifically, roughness is considered high if the distance between two adjacent elevations, as well as their amplitude, is at least 20% of the diameter of the drone for which the landing platform is intended. Preferably, the landing platform in question allows landing on an irregular, discontinuous surface.

[0008] This enables a drone to land safely on a moving surface during the landing process, especially a vehicle such as a truck, a train, a tracked vehicle and / or a ship.

[0009] This makes it possible to land a drone on a surface that undergoes movements in all directions of a three-dimensional coordinate system during the landing process. Furthermore, rotational oscillations around any axis of the three-dimensional coordinate system can also occur.

[0010] This makes it possible, in particular, to land a drone on a ship in the open sea. Landing on a ship can thus be carried out even in typical heavy seas or rougher conditions. On warships, landings are also possible during combat or abrupt course changes. This allows drones to be landed and launched safely and without damage using simple landing gear or stands. The shock-absorbing landing surface prevents the drone from being accelerated vertically after touchdown to such an extent that it would be permanently ejected from the landing platform. In other words, after landing, the drone is either not thrown upwards at all, or it is not thrown or hurled with such force or distance that it would not land on the platform and be damaged or lost entirely.

[0011] This also makes it possible to land a drone safely and without damage on a stable surface with irregular elevations and depressions, the structure of which is such that direct contact with the drone – even during a controlled landing – would lead to severe damage or total destruction of the drone. This not only prevents the drone's destruction but also saves lives by preventing the unintentional activation of a drone's weapon system due to uncontrolled ground contact. Furthermore, it saves the lives of friendly troops, as the drone remains available for further operations. This also allows a drone to be landed on slopes or in swamps.

[0012] The dependent claims relate to further advantageous embodiments of the invention.

[0013] The invention is described in more detail with reference to the enclosed drawings, in which only preferred embodiments are shown by way of example. These show:

[0014] Fig. 1 shows an axonometric representation of a first preferred embodiment of a physical landing platform;

[0015] Fig. 2 shows an axonometric representation of a second preferred embodiment of a physical landing platform;

[0016] Fig. 3 shows a sectional view of a landing platform and a drone on approach; Fig. 4 shows a spring element in sectional view; and

[0017] Fig. 5 shows another embodiment of a drone in a tilted position.

[0018] Figures 1 to 3 each show a landing platform 1 for landing a drone 2, comprising a first surface structure 3 which is attached in an upper area 4 of a frame 5, wherein the first surface structure 3 has at least a first distance 6 to a base surface 7 of the landing platform 1, and wherein the first surface structure 3 is arranged in a predefinable shock-damped manner relative to the base surface 7.

[0019] This enables a safe landing of a drone 2 on a discontinuous surface, i.e., a surface that does not maintain a constant position in three-dimensional space during the landing process, and / or which has a high roughness. In particular, roughness is considered high if the distance between two adjacent elevations and their amplitude are at least 20% of the diameter of a drone 2 for which the landing platform 1 is intended. Preferably, the landing platform 1 enables landing on an irregular, discontinuous surface.

[0020] This enables a safe landing of a drone 2 on a moving surface during the landing process, in particular a vehicle such as a truck, a railway, a tracked vehicle and / or a ship.

[0021] This makes it possible to land a drone on a surface that undergoes movements in all directions of a three-dimensional coordinate system during the landing process. Furthermore, rotational oscillations around any axis of the three-dimensional coordinate system can also occur.

[0022] This makes it possible, in particular, to land a drone 2 on a ship in the open sea. This allows landing on a ship even in typical heavy seas or rougher conditions. On warships, landing during combat or an abrupt change of course is also possible. Drones 2 can thus be landed and launched safely and without damage using simple landing gear or stands. The shock-absorbing landing surface or first surface structure 3 prevents the drone 2 from being accelerated vertically so strongly after landing that it would permanently detach from the landing platform 1. In other words, after landing, the drone 2 is either not thrown upwards at all, or not thrown as forcefully or far.thrown so that they would no longer land on landing platform 1 and would be damaged or completely lost.

[0023] This also makes it possible to land a drone 2 safely and without damage on a stable surface with irregular elevations and depressions, the structure of which is such that direct contact with the drone 2 – even during a controlled landing – would lead to severe damage or complete destruction of the drone 2. This not only prevents the destruction of the drone 2, but also saves lives by preventing the unintentional activation of a weapon system due to uncontrolled ground contact. Furthermore, it saves the lives of friendly troops, as the drone 2 remains available for further deployment. This also allows the drone 2 to be landed on slopes or swamps.

[0024] This allows drones without a landing system or landing gear to be landed safely and without damage. This also allows drones to be fully designed for their intended use, as more mass is available for sensors and / or payload.

[0025] The landing platform 1 is a device designed and suitable for a drone 2 to land on it and preferably also to take off from it. A drone 2 is an unmanned, autonomous, or remotely controlled aircraft. Preferably, the drone 2 is a "Vertical Take-Off and Landing Unmanned Aerial Vehicle," abbreviated VTOL UAV or VTUAV. The drone 2 preferably has at least two, preferably four, and preferably more than four rotors. The drone may also have fixed wings.

[0026] Preferably, the drone 2, for which the landing platform 1 is designed and configured, is a drone 2 of weight class 1 according to the classification of the US Department of Defense from 2011, and consequently has a maximum weight of 20 kg. In a further development of the invention, the landing platform 1 can also be configured such that drones 2 of weight class 2 with masses between 20 kg and 150 kg can land safely on it.

[0027] The landing platform 1 has a first surface structure 3, which represents the intended landing area or landing target point or landing site for the drone 2. The first surface structure 3 comprises a two-dimensional textile product. This product may have surface coatings. The first surface structure 3 exhibits a certain degree of flexibility perpendicular to its taut surface. As a result, the movement of the drone 3 upon contact with the first surface structure 3 during the final moments of the landing process is not abruptly stopped, but rather slowed down and decelerated by the deformation of the first surface structure 3.

[0028] The first surface structure 3 can be designed as a watertight and airtight sheet. Preferably, however, the first surface structure 3 has a definable plurality of air or water passage openings. This prevents the first surface structure 3 from being excessively deflected by wind or set into vibrations, especially resonant vibrations. This also prevents long-term exposure to water, which would lead to residual sagging and / or fatigue failure of the first surface structure 3.

[0029] Preferably, the first surface structure 3 comprises a mesh, which preferably has a water-repellent coating. Particularly preferably, the first surface structure 3 is designed as a net. This allows for both high strength and high air permeability. Furthermore, it exhibits a very low tendency to oscillate with the surrounding winds.

[0030] This can further support the landing of the drones by partially entangling the landing drone in the net, thus preventing it from being thrown back up by a vibration of the surface structure 3.

[0031] Preferably, the surface structure 3 exhibits a dynamic elongation (rope elongation or net elongation) of between 25% and 44%. Preferably, the surface structure 3 exhibits a static elongation (rope elongation) of between 8% and 12%. The relevant elongations are to be determined according to the test specifications for climbing ropes, EN 892.

[0032] Due to its elasticity or flexibility, the surface structure 3 can expand in all three axes. This expansion results in a damped rebound. Although this expansion could vary under the same force, it nevertheless provides a safe and controlled deceleration of the drone 2 during the landing process, even in the case of lateral or horizontal deviations from a vertical landing. This can be further achieved by a preferred embodiment of the surface structure 3, in which it sags in a predefinable manner when unloaded and in a horizontal orientation. This is shown schematically in Fig. 3.

[0033] Preferably, in a purely static state loaded with the maximum mass of the drones 2 to be landed, the surface structure 3 exhibits a lateral angle 36 to the inner surface of the frame 5, which is between 50° and 65°. It should be noted that in Fig. 3 the surface structure 3 is not loaded by a drone 2 or a test weight. In a loaded state, the surface structure 3 would essentially have the shape of a downwardly inclined pyramid.

[0034] Drones 2 with different dimensions are known. As already explained, the landing platform 1 is specifically designed and configured for drones 2 with a certain maximum weight. Furthermore, a specific embodiment of the landing platform 1 is preferably provided for drones 2 of specific dimensions. Preferably, the first surface 3 has a square, pentagonal, hexagonal, or circular base. This allows the drone 2 to land in different orientations relative to the first surface 3. Preferably, the first surface 3, in the preferred embodiment with a square base, has side lengths that are at least three times greater than the width or length of the drone, including its rotor blades. Preferably, the preferably square surface 3 has side lengths between 1.8 m and 3 m.

[0035] The landing platform 1 has a frame 5 which supports the first surface structure 3. The frame 5 is a three-dimensional body. The frame 5 has an upper section 4 and a base 7. The base 7 is specifically part of a lower section of the frame 5.

[0036] The first surface structure 3 is arranged within the upper region 4. The upper region 4 is preferably not the uppermost surface or edge of the frame 5, but rather the region that is bounded on one side by this uppermost surface or edge. As shown in Fig. 3, the edges 30 of the surface structure 3 can be located significantly below the uppermost surface of the frame 5. Preferably, the upper region 4 extends between the uppermost surface of the frame and the preferably present frame openings 8.

[0037] The surface structure 3 is arranged or attached to or within the upper area 4. The actual load-bearing attachment can be formed, in particular, by means of a predefinable number of straps 29, which encircle the uppermost surface of the frame 5 and are attached to an outer side surface of the frame 5. Alternatively, the straps 29 can also extend through openings in the frame. The other ends of the straps 29 are connected to the edges 30 of the surface structure 3. This allows the elongation of the straps 29 to also be used to dampen the landing forces. Preferably, the straps 29 have a dynamic elongation of between 25% and 44%. Preferably, the straps 29 have a static elongation of between 8% and 12%. The relevant elongations are to be determined according to the test specifications for climbing ropes, EN 892.

[0038] Preferably, a spring element 28 is arranged in a predefinable number of the belts 29 in order to further enhance the braking properties of the belts 29. Fig. 4 shows a preferred design of such a spring element 28. According to a further embodiment, essentially the entire circumference of the first surface structure 3 is connected to the respective opposing parts of the frame 5, for example by welding or bonding.

[0039] The frame 5 has a base 7. This is the area formed by the lower parts or the lower surface of the frame 5, on which the landing platform 1 stands in a horizontal position on a flat surface.

[0040] The surface structure 3 is designed and attached to the frame 5 such that it has a first distance 6 to the base 7. When the landing platform 1 is statically loaded with the maximum drone mass for which it is designed or intended, the first distance 6 is preferably between 35% and 60%, and in particular between 40% and 50%, of a second distance 37 between the edges 30 of the surface structure 3 and the base 7, see Fig. 3.

[0041] The frame 5 can be designed as a completely enclosed body. Preferably, however, the frame 5 is designed to be predictably air-permeable and preferably has open, air-permeable side walls. This air permeability reduces drag. Furthermore, the generation of lift can be reduced and / or specifically controlled.

[0042] To achieve air permeability, the frame 5 preferably has a predefinable number of frame openings 8. The number of frame openings 8 and their respective areas can vary considerably. In the preferred embodiment, which is also shown in Figures 1 to 3, it has proven advantageous to have eight frame openings 8 circumferentially in the frame 5, each of a certain size. Regardless of the number of frame openings 8, it has proven advantageous if the total opening area of ​​all frame openings 5 ​​is between 75% and 95% of the surface area of ​​an enclosing body of the frame 5 that abuts the frame 5. This enclosing body completely encompasses the frame 5. Preferably, the frame 5 has a predefinable number of support legs 9.These are arranged between the upper section 4 and the base 7, connecting them. In this configuration, which is also shown in Figures 1 to 3, the upper section 4 is designed as a fully enclosed square ring. The same applies to the base 7, which is also designed as a fully enclosed square ring. The upper section 4 is positioned parallel to the base 7. The legs 9 are arranged or positioned between these two fully enclosed rings, which may also have other base shapes. Together with the upper section 4 and the base 7, the legs 9 enclose the frame openings 8.

[0043] The frame openings 8 can be designed to be completely unobstructed, meaning they are free of any device fixed within them. This is also the case in the preferred embodiment shown in Figures 1 to 3. In a further development of the invention, a second surface structure is arranged in a predefinable number of the frame openings 8, preferably in all of them. In particular, the second surface structure has similar or identical features to the first surface structure 3.

[0044] The frame 5 can have different structural designs. The frame 5 can be designed as a truss, particularly from metal and / or plastic parts. In particular, the truss can be designed to be hinged. Hinges, ball bearings, and / or mechanical locks are arranged between the individual struts of the truss. A frame 5 constructed in this way can also have mechanical damping elements. For example, springs can be arranged between unfolded parts, which, in the operating position, create a predefined dynamic resistance and also assist the assembly process when a folded frame 5 is erected.

[0045] It has proven advantageous if the frame 5, i.e., the upper section 4 and the base 7, and preferably also the legs 9, is designed as an inflatable hollow frame. The basic concept is similar to a dinghy or an inflatable tire. This design has the advantage of being easy to manufacture and control. Furthermore, it is easily foldable and therefore easy to store, as it can be accommodated in various open spaces. Transporting an uninflated hollow structure on the deck of a ship is easy, as the wind has little surface area to act upon and hardly any lift is generated that could be detrimental to the person carrying it.

[0046] The uninflated hollow frame can be fully grasped by a person carrying it and pressed against their body, making it significantly easier to carry than a metal truss. In its deflated state, the hollow frame is easy to position and inflate. The still-empty frame can be easily positioned and secured at the desired location. Furthermore, people can stand on these points to check its position before it is secured. It is then inflated using compressed air.

[0047] The compressed air can originate from a compressed air line on the ship or from an air pump 15 on the landing platform 1. Furthermore, the landing platform 1 can have a compressed air tank 22, which is connected to the hollow frame. However, this transition from the storage state to the operational state typically occurs without any human intervention and has a virtually non-existent error rate, since the hollow frame has no joints and no mechanical locking or securing devices.

[0048] Another advantage of the rapid positioning of landing platform 1 is that a helicopter landing pad on a ship can be used only temporarily without blocking it for too long or preventing a helicopter from being deployed soon, since landing platform 1 does not need to be permanently positioned there. The operational capability of a ship can be further enhanced by designing landing platform 1 with a hollow frame. If such a landing platform 1 with an inflated hollow frame is positioned and secured on a helicopter landing pad, it can be cleared very quickly in an emergency where the landing pad is needed immediately, as lives would otherwise be at risk, simply by releasing, for example, cutting, the fastenings of landing platform 1.Due to the low mass of the hollow frame compared to its surface area, it is then blown by the wind, such as the slipstream, from the helicopter landing pad into the sea. This leads to the loss of landing platform 1, but also to the saving of lives.

[0049] In addition to the possibility of fully inflating the cavity or up to a certain internal air pressure, it is also preferably provided to only partially inflate it. The internal pressure would then be the ambient air pressure, with the cavity only being filled to a maximum of 90% by volume.

[0050] The design of landing platform 1 with a hollow frame allows for further deployment, enabling it to float directly on a Newtonian fluid, such as water, or a non-Newtonian fluid, such as quicksand or in swamps. In this case, landing platform 1 only needs to be anchored in place to prevent it from drifting during the landing process.

[0051] As already mentioned, it is preferably intended that the landing platform 1 be attached to a surface. Preferably, fastening cords 20 and / or receiving openings for fastening cords 20 are arranged on the frame 5, in particular on the base 7.

[0052] It is provided that the first surface structure 3 is arranged with predefined, and in particular aperiodic, shock damping relative to the base 7. The moving mass acting on the first surface structure 3 is therefore reliably decelerated. Preferably, this shock damping has a damping coefficient D of at least 0.9, and in particular at least 1. The damping coefficient D is a measure of the damping of an oscillating system. The particularly preferred aperiodic shock damping prevents the drone from oscillating back.

[0053] Shock absorption can be implemented or caused in different ways. It can be achieved through a passive arrangement and / or an active arrangement. According to a first embodiment, shock absorption is achieved through a corresponding design of the geometry of the inflatable frame 5 and the inflatable support legs 9. The frame 5 itself acts as the shock absorber. For this purpose, it is provided, for example, that flow resistance elements, such as controllable and adjustable valves or throttles, are located inside the frame 5, particularly in the support legs 9.

[0054] According to a further development of this first embodiment, a predefinable number of the support legs 9 have predefinable adjustable leg lengths and / or spring constants and / or damping constants. Such active properties can be implemented in various ways, and the respective support legs 9 have corresponding controllable devices. Preferably, the landing platform 1 has a first control and / or regulation unit for controlling and / or regulating the leg lengths and / or the spring constants and / or the damping constants of the support legs 9. This first control and / or regulation unit is connected to the frame 5, in particular to a predefinable number of the support legs 9.

[0055] According to a second preferred embodiment of the shock absorption system, a predetermined number of distance and / or deflection limiters 10, which are only capable of withstanding tensile loads, are arranged between the upper area 4 and the base 7. This is illustrated in Figures 2 and 3. In a simple embodiment, the distance and / or deflection limiters 10 can be designed as ropes. Different ropes have different elongations. In particular, the deflection limiters 10 are designed as semi-static ropes and have an elongation of 3% to 5%, especially between 3.5% and 4.2%. Such ropes are used, for example, in caving. This results in a gentle absorption of the internal movements of the frame 5 and prevents the drone 2 from being thrown back after landing. Furthermore, this prevents over-oscillation.

[0056] A distance and / or deflection limiter 10 can also be designed to be adjustable and connected to the first control and / or regulation unit, which allows adjustment of its length and / or its spring constants and / or its damping constants.

[0057] Preferably, the distance and / or deflection limits 10 are of such a length that they are not under tension when the landing platform is unloaded. This allows for a slight or limited rebound after a drone has landed.

[0058] According to a third preferred embodiment or implementation of the shock absorption system, the stiffness of the frame 5 is predictably reduced shortly before contact with the drone 2. During its idle state on the deck of a ship or on the ground, the hollow frame is fully inflated and under a predictable internal gas pressure, in particular atmospheric pressure. This allows for high stiffness and stability of the frame. When sensors detect, or when information exchange with the drone 2 indicates, that it is about to land on the first surface 3—for example, when it is only one meter away—the gas pressure within the inflated frame 5 is predictably reduced. This effectively and easily prevents the drone 2 from being thrown back up from the first surface 3.Furthermore, an air outlet valve on the hollow frame can be set to a controlled open state. This results in a controlled collapse of the frame 5. In principle, this would behave like an air cushion rescue device used by firefighters. However, in the present invention, the damping would be controlled and adjustable with regard to the degree of damping or braking.

[0059] According to a preferred embodiment of the invention, the landing platform 1 has an air-permeable enclosure 12, which is arranged on the upper area 4.

[0060] The enclosure 12 is funnel-shaped. The base of the enclosure 12 facing away from the first surface structure 3 is therefore larger than the base of the first surface structure 3. Furthermore, the enclosure 12 does not overlap the first surface structure 3. The approach direction to the first surface structure 3 is therefore not obstructed by the enclosure 12.

[0061] The enclosure 12 further reduces the probability of a drone 2 being damaged after landing. Even if the drone 2 were to be thrown sufficiently high after landing, for example by waves, it would in most cases be caught by the enclosure 12. The height of the enclosure 12 influences its containment capacity. Different enclosures 12 are preferably designed for use in different seas. For example, a lower enclosure 12 height is sufficient for use in the Mediterranean Sea in summer than for use in the North Atlantic in winter.

[0062] The enclosure 12 can be a separate, independent component, separate from the frame 5, which is merely attached to the frame 5. Preferably, the enclosure 12 is permanently attached to the frame 5. Particularly preferred—especially when the frame 5 is designed as an inflatable hollow frame—is that the enclosure 12 is also designed as an inflatable enclosure 12. It has proven advantageous to manufacture the enclosure 12 and the frame 5 as a single unit. This increases operational safety without increasing operational effort. Only a single inflation process is necessary, without any joining of two parts.

[0063] The enclosure 12 is an air-permeable enclosure 12. This air permeability can be achieved in different ways, as already explained in connection with the frame 5. Preferably, the enclosure 12 has a predefinable number of enclosure openings 13. Regarding the preferred designs of the enclosure openings 13, reference is made to the corresponding descriptions of the frame openings 8. These are also shown in Figures 1 to 3.

[0064] In accordance with the preferred embodiments of the frame 5, it is also preferably provided for the enclosure 12 that the total opening area of ​​all enclosure passage openings 13 is between 75% and 95% of the surface area of ​​an enclosing body of the enclosure 12.

[0065] Furthermore, it is preferably provided that a third surface structure 14 is arranged in a predefinable number of the fence openings 13, preferably in all fence openings 13. Regarding the implementation of the third surface structure 14, reference is made to the descriptions of the first surface structure 3. The third surface structure 14 offers the advantage that it minimizes both the flow resistance of the fence 12 and the occurrence of damage to the drone 2.

[0066] For the purpose of controlling the approach of the drone 2 or determining its position, it is preferably provided that a predefinable number of landing aid markers 18 are arranged on the upper area 4 of the frame 5 and / or on the upper surface 17 of the fence 12. A landing aid marker 18 is a location marker that can be detected and / or read by means of an optical camera or optical sensor, an acoustic sensor, a radar device, a transponder reader, or similar. These sensors can all interact or be combined.

[0067] The landing platform 1 is designed to interact with a specific type of drone 2 or a specific drone 2. In addition to the dimensions of the landing platform 1 being adapted to the specific drone type, it is further preferably provided that the drone 2 has at least one sensor unit for detecting the landing aid markings 18, or that the landing aid markings 18 are adapted to the sensor unit for detecting landing aid markings of the respective drone 2. It may also be provided that the landing aid markings 18 are interchangeable, thus enabling the system to react to different drones.

[0068] Fig. 5 shows a preferred embodiment of the landing platform 1. In the area of ​​the base 7, this platform has a predefinable, rigid base frame 35, which is preferably rotatably mounted on a base rail 34. A support element 33 is arranged on the rigid base frame 35, which is either tiltable or has an adjustable length, allowing a predefinable ground angle 38 to be set. This allows the landing platform 1 to be predefinably tilted. This makes it possible to react to the prevailing weather conditions. This prevents the drone from being blown away from the landing platform 1 by the wind. This also allows drones in the form of fixed-wing aircraft to be caught. This also facilitates the positioning of the landing platform 1 even on sloping terrain, such as hillsides in mountains.

[0069] The following are principles for understanding and interpreting the disclosure in question.

[0070] Characters are usually introduced with an indefinite article "ein, eine, eines, einer". Unless the context indicates otherwise, "ein, eine, eines, einer" should therefore not be understood as a numeral.

Claims

PATENT CLAIMS 1. Landing platform (1 ) for landing a drone (2), comprising a first surface structure (3) which is attached in an upper area (4) of a frame (5), wherein the first surface structure (3) has at least a first distance (6) to a base surface (7) of the landing platform (1 ), and wherein the first surface structure (3) is arranged in a predefinable shock-damped manner relative to the base surface (7).

2. Landing platform (1) according to claim 1, characterized in that the frame (5) is designed to be predefinably air-permeable.

3. Landing platform (1 ) according to claim 1 or 2, characterized in that the frame (5) has a predefinable number of frame through-openings (8).

4. Landing platform (1) according to claim 3, characterized in that a total opening area of ​​all frame passage openings (5) is between 75% and 95% of the surface area of ​​an enclosing body of the frame (5).

5. Landing platform (1 ) according to claim 3 or 4, characterized in that a second surface structure is arranged in a predefinable number of the frame through-openings (8), preferably in all frame through-openings (8).

6. Landing platform (1 ) according to one of claims 1 to 5, characterized in that the frame (5) comprises a predetermined number of support legs (9) which connect the upper area (4) of the frame (5) with the base (7) of the frame (5).

7. Landing platform (1) according to one of claims 1 to 6, characterized in that between the upper region (4) of a frame (5) and the The base (7) contains a predetermined number of - only tensile load-bearing - distance and / or deflection limits (10).

8. Landing platform (1) according to claim 6 or 7, characterized in that a predefinable number of the support legs (9) have predefinable adjustable support leg lengths and / or spring constants and / or damping constants.

9. Landing platform (1) according to claim 8, characterized in that a first control and / or regulation unit for controlling and / or regulating the leg lengths and / or the spring constants and / or the damping constants of the legs (9) is connected to the frame (5), in particular a predefinable number of legs (9).

10. Landing platform (1 ) according to one of claims 1 to 9, characterized in that a, in particular funnel-shaped, air-permeable enclosure (12) is arranged on the upper area (4) of the frame (5), in particular that the enclosure (12) and the frame (5) are formed in one piece.

11. Landing platform (1) according to claim 10, characterized in that the enclosure (12) has a predetermined number of enclosure passage openings (13), 12. Landing platform (1) according to claim 11, characterized in that the total opening area of ​​all enclosure passage openings (13) is between 75% and 95% of the surface area of ​​an enclosure body of the enclosure (12).

13. Landing platform (1 ) according to claim 11 or 12, characterized in that a third surface structure (14) is arranged in a predefinable number of the enclosure openings (13), preferably in all enclosure openings (13).

14. Landing platform (1) according to one of claims 1 to 13, characterized in that the first surface structure (3) and / or the second surface structure and / or the third surface structure (14) have air passage openings. exhibits, and is particularly designed as a network.

15. Landing platform (1 ) according to one of claims 1 to 14, characterized in that the frame (5) is designed as an inflatable hollow frame and / or the enclosure (12) is designed as an inflatable enclosure.

16. Landing platform (1 ) according to claim 15, characterized in that the landing platform (1 ) has at least one air pump (15) to which the frame (5) and / or the enclosure (12) is connected.

17. Landing platform (1 ) according to claim 16, characterized in that a second control and / or regulation unit (16) for controlling and / or regulating an air pressure in the frame (5) and / or the enclosure (12) is connected to the at least one air pump (15) and / or at least one control valve (22).

18. Landing platform (1 ) according to one of claims 1 to 17, characterized in that the first surface structure (3) is connected to the frame (5) by means of a predetermined number of fastening cords (29), and that at least one fastening cord (29) comprises a spring element (28), in particular a predefinable adjustable one.

19. Landing platform (1 ) according to one of claims 1 to 18, characterized in that a predetermined number of landing aid markings (18) are arranged on the upper area (4) of the frame (5) and / or on a fence top surface (17) of the fence (12).

20. System comprising a landing platform (1) according to claim 19 and a drone (2), wherein the drone (2) has at least one sensor unit for detecting the landing aid markings (18).

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