GB2605454A

GB2605454A - Drone Landing System

Info

Publication number: GB2605454A
Application number: GB2104770.9A
Authority: GB
Inventors: J Crockford Chris
Original assignee: Digital and Future Technologies Ltd
Current assignee: Digital and Future Technologies Ltd
Priority date: 2021-04-01
Filing date: 2021-04-01
Publication date: 2022-10-05
Anticipated expiration: 2041-04-01
Also published as: GB202104770D0; GB2605454B

Abstract

A drone landing system comprises a first landing surface 104 parallel to and fast with a second landing surface 110 (the landing surfaces are arranged back-to-back and unitary or rigidly joined). Securing means (e.g. electromagnet(s) and/or mechanically engaging means, e.g. rotatable hooks, slidable bars) releasably secure a drone 130 to the first landing surface. A rotation mechanism revolves the landing surfaces between a first position in which the first landing surface is exposed to receive a drone and a second position in which the first landing surface is within a housing. The first landing surface, together with the attached first UAV, may be rotated by 180 degrees, exposing the second landing surface to receive a second drone. A deployable concertina cover may protect landing surfaces from rain. A robotic arm (156, figure 5A) may reposition a drone, load/unload a payload 132 while the drone is stowed, remove/insert a drone battery.

Description

Drone Landing System

S FIELD

This invention relates to a drone landing system and a method of operating a drone landing system.

BACKGROUND

The use of drones is becoming increasingly common, particularly in industries in which logistics play an important role. Such industries include package delivery, transportation, healthcare, the military, warehouse management, and transportation.

Herein, drone refers to an aerial vehicle that is remote controlled, autonomous, or some combination of remote controlled and autonomous.

Many conventional drones are able to land on any suitable surface, for example, on any substantially flat, unobstructed area. Landing a drone without requiring any specific landing apparatus located on the ground may be preferable in some instances, for example where infrastructure may be difficult or costly to install. However, landing drones on any suitable flat area does not make efficient use of the available landing space. Furthermore, conventional drone loading/unloading can be labour intensive and subject to human error.

There is a need for an improved drone landing system.

SUMMARY OF THE INVENTION

According to the present invention there is provided a drone landing system comprising: a first landing surface comprising securing means for releasably securing a drone to the first landing surface, a second landing surface parallel to and fast with the first landing surface, a housing, and a rotation mechanism configured to rotate the first and second landing surfaces between a first position in which the first landing surface is exposed to receive a further drone and a second position in which the first landing surface is within the housing.

The rotation mechanism may be configured to rotate the first and second landing surfaces by 180 degrees between the first and second positions.

The rotation mechanism may be configured to rotate the first and second landing surfaces only if a drone is secured to one or both of the first and second landing surfaces.

The rotation mechanism may be configured to rotate the first and second landing surfaces about an axis parallel to the first and/or second landing surfaces.

In the first position, the first landing surface may form an upper exterior surface of the housing and, in the second position, the second landing surface may form an upper exterior surface of the housing.

The securing means may be configured to, when a drone is present on the first landing surface, mechanically engage with the drone.

The securing mechanism may comprise one or more rotatable hooks configured to, when a drone is present on the first landing surface, rotate to a position in which the 30 one or more rotatable hooks mechanically engage with the drone.

The one or more rotatable hooks may be configured to rotate to a position beneath the first landing surface when no drone is present on the first landing surface.

The securing means may comprise one or more slidable portion: when a drone is present on the first landing surface, slide to a position in which the one or more slidable portions mechanically engage with the drone.

S The securing means may comprise one or more recesses in the first landing surface for receiving corresponding protrusions on the drone.

The securing means may further comprise one or more locking pins configured to engage with corresponding one or more holes in the drone.

The securing means may comprise one or more electromagnets.

The securing means may be configured to determine that a drone has landed on the first landing surface by determining if an emf induced in the electromagnets exceeds a predetermined threshold The drone landing system may further comprise a loading mechanism configured to load a payload into a drone secured to the first landing surface and/or unload a payload from a drone secured to the first landing surface.

The loading mechanism may be within the housing and is configured to, when the first landing surface is in the first position, load a payload into a drone secured to the first landing surface and/or unload a payload from a drone secured to the first landing surface.

The loading mechanism may comprise robotic arm arranged on the first landing surface.

The robotic arm may be configured to reposition a drone on the first landing surface 30 such that the drone is positioned to be secured by the securing means.

The robotic arm may be configured to rotate between the first and the second landing surfaces to load a payload into a drone secured to the first and second landing surfaces and/or unload a payload from a drone secured i second landing surfaces.

The drone landing system may further comprise a control unit configured to receive one or more control signals and determine whether a drone has landed on the first landing surface in dependence the one or more control signals, wherein the one or more control signals may comprise one or more of: a signal indicative of an increase in the weight borne by the first landing surface, a signal indicative of the securing means engaging with a drone, a radio signal from a landed drone or an air traffic controller, an input from a user.

The drone landing system may further comprise a control unit configured to receive one or more control signals and determine whether a drone is secured to the first landing surface in dependence the one or more control signals, wherein the one or more control signals may comprise one or more of: a signal indicative of the securing means engaging with a drone, a radio signal from a landed drone or an air traffic controller, an input from a user.

The housing may comprise a deployable cover configured to, when deployed, cover the first and second landing surfaces.

The deployable cover may comprise a hemispherical concertina or rectangular concertina cover.

There is also provided a method of operating a drone landing system, the drone landing system comprising a first landing surface, a second landing surface parallel to and fast with the first landing surface, and a housing, the method comprising: landing a drone on the first landing surface, securing the drone to the first landing surface, and rotating the first and second landing surfaces such that the drone is rotated with the first landing surface so as to become housed within the housing and the second landing surface is exposed to receive a further drone.

DESCRIPTION OF THE DRAWINGS

The present invention will now be described by way of example with reference to the accompanying drawings. In the drawings: Figure 1A shows a schematic diagram of an example drone landing system.

Figure 1B shows a schematic diagram of an example drone landing system during rotation.

Figure 2A shows a schematic diagram of an example landing surface of the drone landing system with securing means, including a landed drone.

Figure 2B shows a schematic diagram of an example landing surface of the drone landing system with a further exemplary securing means, including a landed drone.

Figure 2C shows a schematic diagram of an example landing surface of the drone landing system during rotation.

zo Figure 2D shows a schematic diagram of an example landing surface of the drone landing system after rotation, in which a second landing surface is receiving a further drone.

Figure 3 shows a schematic diagram of an example drone landing system including a loading mechanism.

Figure 4 a schematic diagram of an example drone landing system including a loading mechanism comprising a moving means.

Figure 5A shows a schematic diagram of an example drone landing system including a loading mechanism comprising a robotic arm.

Figure 5B shows a schematic diagram of an example drone landing system including a loading mechanism comprising a robotic arm during rotation.

Figure 6 shows an example method of operating the drone landing system.

DETAILED DESCRIPTION

The following description is presented to enable any person skilled in the art to make and use the invention and is provided in the context of a particular application. Various modifications to the disclosed embodiments will be readily apparent to those skilled in the art.

The general principles defined herein may be applied to other embodiments and applications without departing from the spirit and scope of the present invention. Thus, the present invention is not intended to be limited to the embodiments shown but is to be accorded the widest scope consistent with the principles and features disclosed herein.

Figure 1A shows an exemplary drone landing system 100. The system 100 comprises a housing 102 and a first landing surface 104. The housing 102 may comprise an aperture 106, in which the first landing surface 104 is disposed. The first landing surface 104 may form an upper exterior surface of the housing 102 (in certain configurations of the system 100). The upper surface of the housing 102 and/or the first landing surface 104 may be horizontal in relation to the ground in the configuration shown in Figure 1A. The first landing surface 104 is suitable for receiving a drone and may be substantially flat.

The drone may be a helicopter, for example, a quadcopter. While the present invention is particularly suitable for vertical take-off and landing (VTOL) aircraft, the invention may also be used with conventional take-off and landing (CTOL) aircraft, short take-off and landing (STOL) aircraft, short take-off and vertical landing (STOVL) aircraft, or aircraft that combine the functionality of any of these types of aircraft (such as tilting rotor or tilting jet nozzle aircraft).

The first landing surface 104 is rotatable about an axis 108. Axis to the upper surface of the housing 102 and/or the first landing surface 104. Axis 108 may be horizontal in relation to the ground. As shown in Figures 1A and 1B, the axis 108 may run through the centre of the first landing surface 104. Disposing the axis 108 in the centre of first landing surface 104 reduces the energy required to cause rotation. However, axis 108 may be off-centre, for example at an edge of first landing surface 104. In order for the first landing surface 104 to be able to rotate, the size of aperture 106 is sufficient so as not to impede rotation of the first landing surface 104.

Housing 102 may be sunk into the ground such that the upper surface of the housing 102 is flush with the ground. For example, housing 102 may be sunk into the surface of a runway or taxiway.

Figure 1B shows the drone landing system 100 in a configuration in which the first landing surface 104 is rotating about axis 108. It should be apparent that the first landing surface 104 should be arranged in the housing 102 such that there is sufficient ground clearance so as not to impede the rotation of the first landing surface.

The rotation of the first landing surface 104 is effected by a rotation mechanism 112.

Rotation mechanism 112 comprise an electric motor. The rotation mechanism 112 may be controlled by a control unit 118. The rotation mechanism 112 may be configured to rotate the first landing surface 104 by 180 degrees.

The first landing surface 104 may be circular, as shown in Figures 1A and 1B, but may have an alternative shape such as rectangular. A rectangular, for example square, landing surface may be preferable to a circular landing surface in applications where ingress of rainwater is a concern. For example, where the first landing surface 104 is rectangular and the axis 108 passes through the centre of the first landing surface 104 and through two opposing edges of the first landing surface 104, the gap between the edges of aperture 106 and the edges of the landing surface perpendicular to the axis can be smaller than the gap between the edges of the aperture 106 and the edges of the landing surface parallel to the axis. This is due to the latter of these gaps needing to be larger to accommodate the rotation of the first landing surface 104.

The housing may comprise a deployable cover configured to, w the first and second landing surfaces. The deployable cover may be configured to move between a stowed position and a deployed position. In the deployed position, the cover may be disposed over the first and second landing surfaces in order to protect them from rain. In the stowed position, the deployable cover is arranged so as to not obstruct the landing and take off of drones from the first and second landing surfaces. The deployable cover may comprise a hemispherical concertina or rectangular concertina cover wherein the deployable cover folds in and out between the stowed and deployed positions.

Figures 2A to 2D shows schematic views of the landing area of the system 100 during operation. In Figure 2A, a drone 130 is shown landed on the first landing surface 104. Drone 130 carries payload 132. The payload 132 may be disposed on an upper portion of drone 130. The system 100 may comprise the drone 130.

The first landing surface 104 comprises securing means 114, 116 for releasably securing a drone to the first landing surface 104. The securing means 114, 116 enable a drone to remain in place on the first landing surface 104 during rotation, i.e. the securing means 114, 116 enable a drone to remain in a fixed position relative to the first landing surface 104 during rotation.

The securing means 114, 116 may mechanically engage with a drone. For example, the securing means 114, 116 may comprise one or more rotatable hooks, as shown in Figure 2A. The rotatable hooks may be configured to, when a drone is present on the first landing surface 104, rotate to a position in which the one or more rotatable hooks mechanically engage with the drone. The rotatable hooks may be configured to, when a drone is not present on the first landing surface 104, rotate to a position beneath the first landing surface 104. The securing means 114, 116 may comprise one or more slidable portions configured to, when a drone is present on the first landing surface, slide to a position in which the one or more slidable portions mechanically engage with the drone. The slidable portions may comprise bars or rods. Securing means 114, 116 may be driven by geared rods disposed within the first landing surface 104.

Figure 2B shows a further example of mechanically engaging 116. As shown in this example, the securing means 114, 116 may comprise one or more recesses in the landing surface. The one or more recesses have a concave shape, for example a conical, hemispherical, or pyramidal. The recesses are arranged to receive complementarily shaped convex protrusions on the drone. The interaction between the one or more concave recesses and the convex protrusions causes a self-centring effect, resulting in each landed drone being located at the same position on the first landing surface 104. The recesses and protrusions need not have exactly complementary shapes (e.g. a conical recess and a conical protrusion) to provide the self-centring effect. Provided the recesses and protrusions do not have significantly different dimensions, the self-centring effect will occur. As also shown in Figure 2B, each recess in the landing surface may comprise a locking pin configured to releasably engage with a corresponding hole on the drone. Said locking pin(s) ensure that the drone is secured to the first landing surface 104 and that therefore the drone will remain in place upon rotation of the first landing surface.

As an addition or alternative to mechanical engagement, the securing means 114, 116 may comprise one or more electromagnets. The electromagnets may be configured to generate a magnetic field only when a drone is present on the first landing surface 104. The electromagnets may generate a magnetic field when a drone is not present on the first landing surface 104. One or more magnets in disposed on/in the drone can cause a change in the magnetic field in the electromagnets as the drone lands. Therefore, the electromagnets may be configured to determine whether a drone has landed on the first landing surface 104 by determining if an emf induced in the electromagnets exceeds a predetermined threshold.

As shown in Figure 2A, the system 100 comprises a second landing surface 110, parallel to and fast with the first landing surface 104. In other words, the first and second landing surfaces 104, 110 are arranged back-to-back and are a unitary body or are rigidly joined. The rotation mechanism 112 is configured to rotate the first landing surface 104 and the second landing surface 110 between a first position in which the first landing surface 104 is exposed to receive a drone and a second position in which the first landing surface 110 is within the housing 102. Conversely, in the first position, the second landing surface 110 is within the housing 102 and, in the second position, the second landing surface 110 is exposed to receive a above, the first landing surface 104 may form an upper exterior surface of the housing 102 in the first position. In the first potion, the upper surface of the housing 102 and/or the first landing surface 104 may be horizontal in relation to the ground in the configuration shown in Figure 1A.

The first landing surface 104 and/or the second landing surface 110 may comprise one or more markers indicating the desired position for a drone to land. The one or more markers may be located at the desired position or they may convey information indicative of the desired position. The one or more markers may convey information regarding the weight capacity of the drone landing system. The one or more markers may comprise QR codes, lights, or reflective strips. The one or more markers may be arranged in a predetermined pattern. The predetermined pattern may be read by image capture devices on a drone. The predetermined pattern may be asymmetric to allow a drone to unambiguously determine its orientation relative to the one or more markers.

Figure 2C shows the system 100 in transition between the first and the second positions, where the first and second landing surfaces 104, 110 and a drone 130 secured by securing means 114, 116 are rotating clockwise about axis 108, as illustrated by the dotted arrows. Figure 2D shows the system 100 in the second position, where the first landing surface 104 (and therefore the secured drone 130) are within the housing 102. The second landing surface 110 is exposed to receive a further drone 140.

The second landing surface 110 may comprise a securing means 118, 120 for releasably securing a drone to the second landing surface 110. Securing means 118, 120 may be of the same kind as securing means 118, 120, or the securing means may be of different types. Securing means 118, 120 may engage with a drone mechanically and/or magnetically as described above for the securing means 114, 116 of the first landing surface 104.

Providing a first landing surface 104 able to rotate to reveal a second landing surface 110 advantageously allows a drone on the first landing surface 104 to be stowed for loading/unloading and maintenance while maintaining the ability drone.

The housing 102 and/or the landing surfaces may comprise a mesh or latticelike structure. Using a mesh structure reduces the overall weight of the system 100 when compared to solid structure made of the same material. Using a mesh structure also allows the drone landing system 100 to be deployed on vegetation, for example grass, without blocking sunlight from reaching the vegetation.

The system 100 may further comprise a loading mechanism 150. An exemplary loading mechanism 150 is shown in Figure 3. The loading mechanism 150 is configured to load a payload into a drone secured to the first landing surface 104 and/or unload a payload from a drone secured to the first landing surface 104. The loading mechanism 150 may comprise a robotic arm configured to load/unload the payload. The loading mechanism 150 may be configured to remove and/or insert a battery or fuel cell from/into a drone secured to the first landing surface.

As shown in Figure 3, the loading mechanism may be configured to load a payload into a drone secured to the first landing surface 104 and/or unload a payload from a drone secured to the first landing surface 104 when the first landing surface 104 is in the second position. However, the loading mechanism may be configured to load a payload into a drone secured to the first landing surface 104 and/or unload a payload from a drone secured to the first landing surface 104 when the first landing surface 104 is in the first position, i.e. prior to the first landing surface 104 rotating. To enable unloading/loading when the first landing surface 104 is in the first position, the first landing surface 104 may further comprise an aperture through which the loading mechanism 150 can access a payload on the drone. Said aperture may be permanently open, or may be openable/closable by way of a trapdoor or iris door.

The loading mechanism 150 may comprise a raising mechanism 152 configured to raise and lower itself. The raising mechanism 152 may be configured to move a portion of the loading mechanism 150 vertically. The raising mechanism 152 may comprise a scissor lift arrangement (as shown in Figure 3), a pneumatic lift arrangement, or a hydraulic lift arrangement. This raising mechanism 152 enables the loading mechanism 150 to lower into a position in which it does not obstn first landing surface 104, the second landing surface 110 and any attached drones, and to raise into a position in which it is able to perform its loading/unloading function.

The loading mechanism 150 may comprise movement means 154 configured to move the loading mechanism 150. The movement means 154 may be configured to move the loading mechanism 150 perpendicular to the motion provided by the raising mechanism 152. The movement means 154 may be configured to move the loading mechanism 150 horizontally. The movement means 154 may comprises wheels and optionally a track, as shown in Figure 3.

Figure 4 shows an example of system 100 in which a loading mechanism 150 comprises movement means 154 comprising wheels and a track. The loading mechanism 150 may be configured, via the movement means 154, to deliver the payload to the exterior of the housing 102.

Figure 5A shows an example in which the loading mechanism 150 comprises a robotic arm 156 arranged on the first landing surface 104. The robotic arm 156 may be configured to load and/or unload a payload into/from a drone on the first landing surface 104. The robotic arm 156 may be configured to, when in the first position, reposition a landed drone. The robotic arm 156 may be configured to, when in the first position, reposition a landed drone such that the drone is able to be secured by the securing means 114, 116. Providing the robotic arm 156 as the loading mechanism 150 allows loading and unloading from a drone to performed when the system 100 is in the first or the second position. The robotic arm 156 may be configured to, prior to the first landing surface 104 being rotated, adopt a position in which it does not obstruct the rotation. For example, such a position may comprise a folded and/or retracted position.

The robotic arm 156 may be configured to rotate between the first and second landing surfaces 104, 110, such that the robotic arm 156 can load/unload to/from drones on the first and the second landing surface 104, 110. This rotation allows a single robot arm 156 to load and unload on either surface. Figure 5B shows an example where the robotic arm 156 is configured to rotate about the first and second landing surfaces 104, 110 when the first and second landing surfaces 104, 110 a position, between the first and second positions. The robotic arm 156 may be configured to rotate about the first and second landing surfaces 104, 110 when the first and second landing surfaces 104, 110 are in the first or second position. To accommodate this rotation, the landing surfaces and/or the housing may comprise an opening to allow the robotic arm 156 to pass through.

The loading mechanism 150 may alternatively comprise a separate robotic arm on each landing surface 104, 110 The control unit 118 may be configured to receive one or more control signals and determine whether a drone has landed on the first landing surface 104 in dependence the one or more control signals, wherein the one or more control signals comprise one or more of: a signal indicative of an increase in the weight borne by the first landing surface 104, a signal indicative of the securing means 114, 116 engaging with a drone, a radio signal from a landed drone or an air traffic controller, an input from a user. The signal indicative of an increase in weight borne by the first landing surface 104 may be determined by one or more sensors in the first landing surface 104.

Additionally or alternatively, the control unit 118 may be configured to receive one or more control signals and determine whether a drone is secured to the first landing surface in dependence the one or more control signals, wherein the one or more control signals comprise one or more of: a signal indicative of the securing means engaging with a drone, a radio signal from a landed drone or an air traffic controller, an input from a user. The signal indicative of the securing means 114, 116 engaging with a drone may comprise a signal generated in response to induced emf in the electromagnets exceeding the predetermined threshold (as described above) or a signal indicating that the securing means are in a position where the securing means 114, 116 mechanically engage with the drone.

The control unit 118 may be any kind of device, machine or dedicated circuit, or collection or portion thereof, with processing capability such that it can execute instructions. A processor may be any kind of general purpose or dedicated processor, such as a CPU, GPU, system-on-chip, state machine, media processor, an application-specific integrated circuit, a programmable los programmable gate array (FPGA), or the like. A computer or computer system may comprise one or more processors. The control unit 118 may comprise an internet-ofthings interface. In this example, the control unit 118 may receive control signals from a user located remotely.

The signal indicative of the securing means 114, 116 engaging with a drone may comprise a signal generated in response to induced emf in the electromagnets exceeding the predetermined threshold (as described above) or a signal indicating that the securing means are in a position where the securing means 114, 116 mechanically engage with the drone. Where the control signals comprise a radio signal from a landed drone or an air traffic controller, an input from a user, the system 100 may comprise an antenna to receive said control signals.

The drone landing system 100 allows for efficient use of space for landing drones as the horizontal space needed to allow the landing of one drone can be utilized for the landing of two drones. Furthermore, rotating the landing surfaces to stow a drone within the housing 102, allows the stowed drone to loaded/unloaded and/or service, while that drone is in an enclosed space, protected from the elements, while allowing a second drone to be landed. If necessary, the first drone (on the first landing surface 104) and the second drone (on the second landing surface 110) can be loaded/unloaded and/or serviced at the same time, with one on the upper landing surface and the other on the lower landing surface.

The loading mechanism 150 allows for a drone to be loaded/unloaded while said drone is stowed. The loading mechanism 150 reduces or eliminates the need for manual loading/unloading. The use of a loading mechanism 150 also improves the safety of the system 100, as having human workers to load/unload into/from a stowed drone can be dangerous giving the moving parts of the rotatable landing surfaces.

Figure 6 illustrates an exemplary method of operating the system 100 as described above.

At step 602 a first drone is landed on the first landing surface 1C controlled by the drone if the drone is autonomous or by a user if the drone is remote controlled At step 604, the first drone may be repositioned on the first landing surface 104. As described above, this may be performed by a robotic arm 156. This step may also be performed manually by a user. However, in particular when using an autonomous drone which are able to land at a predetermined position reliably, repositioning of the drone may not necessary.

At step 606, the first drone is secured to the first landing surface 104. This may be done by the securing means 114, 116 as described above.

At step 608, the first and second landing surfaces 104, 110 are rotated such that the first drone is within the housing and the second landing surface is exposed to receive a further drone. This rotation may be described as a rotation from the first position to the second position, as defined above.

At step 610, a payload is unloaded from the drone and/or a payload may be loaded into the drone. As described above, this may include loading or unloading a battery or fuel cell to or from the drone.

At step 612, the earlier steps may be repeated in respect of a further drone on the second landing surface 110. Regardless of whether a drone is landed on the second landing surface 110, in step 612 the first and second landing surfaces 104, 110 are rotated back to the first position.

At step 614, the first drone may be released from the first landing surface 104. The securing means 114, 116 may disengage (e.g. mechanically or magnetically) from the drone. ss At step 616, the first drone may take off from the first landing surface 104. As with step 602, this step may be controlled by the drone if the drone is autonomous or by a user if the drone is remote controlled.

While the inventions described herein are particularly suited for the industries listed in the background section, i.e. package delivery, transportation, healthcare, the military, warehouse management, and transportation On particular the aviation industry), it should be apparent that the advantages of the present invention can be obtained in other industries, or where drones are used for personal use.

The applicant hereby discloses in isolation each individual feature described herein and any combination of two or more such features, to the extent that such features or combinations are capable of being carried out based on the present specification as a whole in the light of the common general knowledge of a person skilled in the art, irrespective of whether such features or combinations of features solve any problems disclosed herein, and without limitation to the scope of the claims. The applicant indicates that aspects of the present invention may consist of any such individual feature or combination of features. In view of the foregoing description it will be evident to a person skilled in the art that various modifications may be made within the scope of the invention.

Claims

CLAIMS1. A drone landing system comprising: a first landing surface comprising securing means for releasably securing a drone to the first landing surface; a second landing surface parallel to and fast with the first landing surface; a housing; and a rotation mechanism configured to rotate the first and second landing surfaces between a first position in which the first landing surface is exposed to receive a further drone and a second position in which the first landing surface is within the housing.
2. The drone landing system of claim 1, wherein the rotation mechanism is configured to rotate the first and second landing surfaces by 180 degrees between the first and second positions.
3. The drone landing system of claim 1 or claim 2, wherein the rotation mechanism is configured to rotate the first and second landing surfaces only if a drone is secured 20 to one or both of the first and second landing surfaces.
4. The drone landing system of any preceding claim, wherein the rotation mechanism is configured to rotate the first and second landing surfaces about an axis parallel to the first and/or second landing surfaces.
5. The drone landing system of any preceding claim, wherein, in the first position, the first landing surface forms an upper exterior surface of the housing and, in the second position, the second landing surface forms an upper exterior surface of the housing.
6. The drone landing system of any preceding claim, wherein the securing means are configured to, when a drone is present on the first landing surface, mechanically engage with the drone.
7. The drone landing system of any preceding claim, wherein the securing mechanism comprises one or more rotatable hooks configured to, when a drone is present on the first landing surface, rotate to a position in which the one or more rotatable hooks mechanically engage with the drone.
8. The drone landing system of claim 7, wherein the one or more rotatable hooks are configured to rotate to a position beneath the first landing surface when no drone is present on the first landing surface.
9. The drone landing system of any preceding claim, wherein the securing means comprise one or more slidable portions configured to, when a drone is present on the first landing surface, slide to a position in which the one or more slidable portions mechanically engage with the drone.
10. The drone landing system of any preceding claim, wherein the securing means comprise one or more recesses in the first landing surface for receiving corresponding protrusions on the drone.
11. The drone landing system of claim 10, wherein the securing means further 20 comprise one or more locking pins configured to engage with corresponding one or more holes in the drone.
12. The drone landing system of any preceding claim, wherein the securing means comprise one or more electromagnets.
13. The drone landing system of any claim 12, wherein the securing means are configured to determine that a drone has landed on the first landing surface by determining if an emf induced in the electromagnets exceeds a predetermined threshold.
14. The drone landing system of any preceding claim, further comprising a loading mechanism configured to load a payload into a drone secured to the first landing surface and/or unload a payload from a drone secured to the first landing surface.
15. The drone landing system of claim 14, wherein the loading mechanism is within the housing and is configured to, when the first landing surface is in the first position, load a payload into a drone secured to the first landing surface and/or unload a payload from a drone secured to the first landing surface.
16. The drone landing system of claim 14 or claim 15, wherein the loading mechanism comprises a robotic arm arranged on the first landing surface.
17. The drone landing system of claim 16, wherein the robotic arm is configured to reposition a drone on the first landing surface such that the drone is positioned to be secured by the securing means.
18. The drone landing system of claim 16 or claim 17, wherein the robotic arm is configured to rotate between the first and the second landing surfaces to load a payload into a drone secured to the first and second landing surfaces and/or unload a payload from a drone secured to the first and second landing surfaces.
19. The drone landing system of any preceding claim, further comprising a control unit configured to receive one or more control signals and determine whether a drone has landed on the first landing surface in dependence the one or more control signals, wherein the one or more control signals comprise one or more of: a signal indicative of an increase in the weight borne by the first landing surface, a signal indicative of the securing means engaging with a drone, a radio signal from a landed drone or an air traffic controller, an input from a user.
20. The drone landing system of any preceding claim, further comprising a control unit configured to receive one or more control signals and determine whether a drone is secured to the first landing surface in dependence the one or more control signals, wherein the one or more control signals comprise one or more of: a signal indicative of the securing means engaging with a drone, a radio signal from a landed drone or an air traffic controller, an input from a user.
21. The drone landing system of any preceding claim, wherein the housing comprises a deployable cover configured to, when deployed, cover the first and second landing surfaces.s
22. The drone landing system of claim 21, wherein the deployable cover comprises a hemispherical concertina or rectangular concertina cover.
23. A method of operating a drone landing system, the drone landing system comprising a first landing surface, a second landing surface parallel to and fast with the first landing surface, and a housing, the method comprising: landing a drone on the first landing surface; securing the drone to the first landing surface; and rotating the first and second landing surfaces such that the drone is rotated with the first landing surface so as to become housed within the housing and the second landing surface is exposed to receive a further drone.