Patent Description:
Current transportation systems are increasingly clogged and polluting, with city centres and urban areas frequently overcrowded with conventionally-powered public transport, delivery lorries (trucks), and privately owned vehicles. These conditions are detrimental to the economy and the environment, in particular with regard to particulate pollution and climate change.

These problems may be alleviated to some extent by the use of small, short-range, vertical take-off and landing aircraft, which may be manned or unmanned ("drones"), and which may be used for transportation of people and goods. Such aircraft may be electricallypowered, or comprise hybrid power systems which combine different energy sources, and are therefore more "eco-friendly" than conventional fossil-fuelled aircraft. These kinds of aircraft may also find utility in settings other than towns and cities, for example in humanitarian aid in Disaster Emergency Management, and in military applications.

The flights of these aircraft will need to be effectively and safely managed in controlled airspace by the aviation authorities. Furthermore, the aircraft will require ground infrastructure, for take-off and landing, passenger and cargo handling, charging/refuelling, and so on. The present disclosure aims to address this infrastructure need, in an efficient, flexible, robust, and cost-effective manner.

Also, there is increasing emphasis in the infrastructure sector on sustainability and low environmental impact.

In this context, it may be preferable to work with the landscape rather than to change it.

<CIT> discloses an unmanned operation system for a vertical take-off and landing unmanned aerial vehicle, the system comprising a confirmation member, a position measurement member, a terrestrial station member, and a remote control unit, such that an unmanned aerial vehicle can be safely protected from external factors such as rain or snow and sunlight when the unmanned aerial vehicle is stored, a battery can be charged or replaced, fuel can be supplied and necessary task equipment can be replaced or freight can be mounted and loaded and unloaded, the unmanned aerial vehicle transmits data to and stores the same in a control member of a terrestrial station and can transmit the same to another device according to a request, position information enabling the unmanned aerial vehicle to take-off and land accurately can be provided, and a flying unmanned aerial vehicle and state information of a surrounding environment can be monitored, and thus an unmanned terrestrial operation system enabling an unmanned aerial vehicle to operate without a pilot can be provided or an unmanned aerial vehicle can be operated by assisting a pilot.

<CIT> discloses a City Autonomous Airport (CAA) and means to handle autonomously booking of Aero-cars aerial containers reception and parcels delivery according to a specific selected root managed via GPS and controlled path programs. The (CAA) consists of: Terminal <NUM> to manage passenger's flights via multiple types of Aero-cars through a landing or take-off yards or elevator terminal, and handling aerial containers in the same. Terminal <NUM> handles the reception of the dropped containers from remotely controlled aircrafts toward elevator inlets to be distributed by pick-up drones to shelves and autonomous ground stations in multiple floors, and handled as aerial parcel sets to delivery drones on top of elevator ends. Terminal <NUM> is a yard type handling of containers and distributing their parcels content via UAVs. Terminal <NUM> is managing the operation of the CAA via multiple types of autonomous UAVs, robots.

<CIT> discloses an apparatus for storing airplanes that includes a first airplane parking floor at a first elevation, a second airplane floor at a second elevation, and an elevator. The first airplane parking floor defines a vacant region within a notional circle circumscribing the first airplane parking floor and defining a notional circumcenter. The first floor is rotatable about the circumcenter for selective angular alignment of one of several first airplane parking floor regions or the vacant region with a fixed sector of the circle. The second airplane parking floor is rotatable, at the second elevation, about the circumcenter for selective angular alignment of one of several second airplane parking floor region with the vacant region. When so aligned, the second airplane parking floor region may be vertically translated by the elevator between the second elevation and the vacant region at the first elevation.

<CIT> discloses a storage unit for an Unmanned Aerial Vehicle (UAV). The storage unit includes a container, a UAV landing platform, and a receptacle. The container is provided for enclosing the UAV. The receptacle is positioned above the UAV landing platform and it includes at least one inclined surface for guiding a landing UAV to a predetermined UAV landing position on the UAV landing platform.

<CIT> discloses a self-service multistoried hanger confined within a building having a plurality of circular storage platforms supported therein for independent turning movement in vertically spaced concentric relation adjacent an elevator lift platform; locking means for such building and means for receiving and discharging airplanes to and from selected segmental storage sectors of a selected one of said storage platforms comprising: a. an electrical drive motor drivingly connected to each of said storage platforms; b. an electrical circuit connected to one side of each of said electrical drive motors; c. a coded card indexer connected to the other side of each of said electrical drive motors for controlling the latter to turn a preselected one of said storage platforms and move a selected storage sector thereof into a position for contiguous relation with the elevator platform. a commutator having a storage space band in said electrical circuit between said indexer and each of said drive motors and provided with a gap coded to a particular storage sector for each of said storage platforms; e. means on said commutator operatively associated with said indexer and the drive motor of a preselected one of said storage platforms for advancing said commutator in timed relation with the turning of said preselected storage platform and for breaking said electrical circuit at said gap upon arrival of the particular selected storage sector into a position for contiguous relation to said elevator platform; f. a door opening the front wall of such building at ground level adjacent that edge of said elevator platform opposite the storage platforms; g. a door mounted on the front wall of such building for closing the door opening therein; h. a lock on said door for locking the same relative to the opening in said front wall, said lock including a normally open master switch in the main circuit between the source of electrical current and the electrical circuit to said indexer and the drive motors controlled thereby; and i. key means assigned to each tenant to such hangar for unlocking said lock and closing said master switch.

<CIT> discloses a helicopter hangar with an automatic lifting apron. The helicopter hangar comprises a parking apron, side walls, a first top plate, a second top plate, a bearing seat, a stepping motor, a planetary gear speed reducer, a connecting plate and the like. Lifting equipment is arranged below the parking apron and can assist the parking apron in moving up and down. The side walls are of a vertical flat plate structure, the number of the side walls is two, the two side walls are arranged on the two sides of the parking apron, each side wall is connected with a connecting plate in a sliding mode, the connecting plates on the two sides are hinged to the first top plate and the second top plate through hinge shafts respectively, and the first top plate is capable of rotating around the hinge shafts of the first top plate. Power equipment is arranged on the connecting plate to assist the first top plate and the second top plate to rotate, the lifting equipment is arranged on the connecting plate to assist the connecting plate to move up and down, a rear garage plate of a vertical plate structure is arranged on the rear sides of the two side walls, the rear garage plate is fixed between the two side walls, and the front side of each side wall is connected with a garage door through a hinge. The hanger has the advantages of being multifunctional, and resource-saving.

According to an aspect of the disclosure, there is provided a lift structure for an aerodrome structure, comprising: an upstanding tubular frame comprising an upper ring located over a base ring and supported thereon by columns; a platform located within the tubular frame; and a lift mechanism arranged to raise and lower the platform between the base ring and the upper ring, wherein: the columns are spaced apart from each other to provide a side opening for loading an aircraft onto the platform and unloading an aircraft therefrom when the platform is in a lowered position; and the platform provides a take-off and landing pad for an aircraft when the platform is in a raised position.

As used herein, "aerodrome structure" (or in US English: "airdrome") means a structure or installation from which flight operations take place, including the departure (i.e. take-off) and arrival (i.e. landing) of aircraft and the loading and unloading of passengers and/or cargo. The structure may (or may not) additionally be arranged to accommodate aircraft storage, aircraft maintenance facilities, aircraft refuelling/recharging facilities, passenger accommodation such as a passenger lounge, and air traffic control facilities.

The lift structure forms a core assembly of the aerodrome structure. During in-service operation, the platform of the lift structure enables the loading, unloading, take-off, and landing, of aircraft. As will be explained later herein, the lift structure and its platform also perform a key role in the construction of the aerodrome structure itself, prior to entry into operational service.

The lift structure may comprise base support cross-members located within the base ring and connected thereto, the lift mechanism being located beneath the platform and supported by the base support cross-members.

The platform may comprise discrete first and second platform parts; and the lift mechanism may be arranged to raise and lower the first and second platform parts independently of each other in one mode of operation.

The lift mechanism may be arranged to raise and lower the first and second platform parts together in another mode of operation.

The lift mechanism may comprise at least one chain link lift located beneath the platform.

The lift structure may comprise guide rails extending between the base ring and the upper ring, the platform being movably connected to the guide rails, the lift mechanism being arranged to raise and lower the platform along the guide rails between the base ring and the upper ring.

According to another aspect of the disclosure, there is provided an aerodrome structure, comprising: a lift structure as described herein above; a plurality of anchor members located on the ground around the lift structure; a plurality of radially-extending stabilisation members each comprising a first end connected to the upper ring and a second end connected to a respective one of the anchor members; and a plurality of cladding segments supported by the stabilisation members, each cladding segment spanning a gap between an adjacent pair of the stabilisation members and extending between the upper ring and the second ends of said adjacent pair of the stabilisation members, thereby to define a covered interior volume of the aerodrome structure.

The interior volume (i.e. internal space) may be segmented or partitioned to host multiple capabilities that contribute to the overall role of the aerodrome structure.

Each of the cladding segments may comprise a fabric material.

The fabric material may comprise PVC-coated polyester.

One or more of: the base ring; the platform; the guide rails; the upper ring; the columns; and the stabilisation members, may comprise aluminium alloy or steel.

The aerodrome structure may comprise a hanger structure for accommodating at least one aircraft and located adjacent to the side opening, for loading an aircraft onto the platform and unloading an aircraft from the platform when the platform is in the lowered position.

The hanger structure may comprise hanger structure roof members connected to the upper ring and upstanding hanger structure columns connected to the hanger structure roof members and to respective ones of the anchor members.

The anchor members may be configured to be height adjustable in order to position the second ends of the stabilisation members at the same height as each other from a ground datum.

According to another aspect of the disclosure, there is provided a method of constructing the aerodrome structure described herein above, the method comprising: providing the base ring on the ground; providing the lift mechanism within the base ring; attaching the platform to the lift mechanism such that the platform is located above the lift mechanism; providing the upper ring on the platform; pivotably connecting first ends of the columns to the upper ring such that the columns are in spaced relationship with each other around the upper ring and extend radially from the upper ring toward the ground; pivotably connecting the first ends of the stabilisation members to the upper ring such that the stabilisation members are in spaced relationship with each other around the upper ring and extend radially from the upper ring toward the ground; activating the lift mechanism in order to raise the platform and thus the upper ring located thereon, thereby to draw the pivotably connected columns into a substantially vertical condition and the pivotably connected stabilisation members into an inclined condition with respect to the ground; locking the first ends of the columns and the first ends of the stabilisation members into fixed relationship with the upper ring; connecting second ends of the columns to the base ring so as to be in fixed relationship therewith; providing the anchor members on the ground and connecting the second ends of the stabilisation members to the respective anchor members so as to be in fixed relationship therewith; and attaching the cladding segments to the stabilisation members.

Due especially to the provision and configuration of the height-adjustable platform, the lift structure is an essentially self-erecting structure, which additionally enables the erection of other parts of the aerodrome structure. That is, the need for cranes or other heavy lifting equipment is eliminated. Thus, the platform has a dual function: firstly, it enables the construction of the aerodrome structure; and secondly, it serves as an in-service aircraft handling platform for loading, unloading, take-off, and landing. This dual-function aspect makes the aerodrome structure highly efficient in terms of its construction and operation.

The method of constructing the aerodrome structure may comprise adjusting the height of one or more of the anchor members in order to position the second ends of the stabilisation members at the same height as each other from a ground datum.

The method of constructing the aerodrome structure may comprise: before activating the lift mechanism in order to raise the platform, connecting first ends of guide rails to the base ring such that the guide rails extend upwardly from the base ring and are in spaced relationship with each other around the base ring and the platform; and connecting the guide rails to the platform such as to allow height adjustment of the platform relative to the guide rails.

The method of constructing the aerodrome structure may comprise: after activating the lift mechanism in order to raise the platform, connecting second ends of the guide rails to the upper ring so as to be in fixed relationship therewith.

The method of constructing the aerodrome structure may comprise assembling one or more of: the base ring; the platform; the guide rails; the upper ring; the columns; and the stabilisation members, from a plurality of discrete component parts.

According to another aspect of the disclosure, there is provided a kit of parts for the lift structure described herein above, comprising: a set of ring segments configured to be connected together to form the base ring; a set of ring segments configured to be connected together to form the upper ring; a plurality of sets of column segments, the segments of each set of column segments being configured to be connected together to form one of the columns, one of the segments in each set of column segments being configured to be connected to the base ring and another of the segments in each set of column segments being configured to be connected to the upper ring; a set of platform segments configured to be connected together to form the platform; and a lift mechanism configured to be connected to the platform.

The kit of parts may comprise a plurality of sets of guide rail segments, the segments of each set of guide rail segments being configured to be connected together to form one of the guide rails, one of the segments in each set of guide rail segments being configured to be connected to the base ring, each of the guide rails being configured to be connected to the platform.

According to another aspect of the disclosure, there is provided a kit of parts for the aerodrome structure described herein above, comprising: the kit of parts for the lift structure described herein above; a plurality of the anchor members; a plurality of sets of stabilisation member segments, the segments of each set of stabilisation member segments being configured to be connected together to form one of the stabilisation members, at least one of the segments in each set of stabilisation member segments being configured to be connected to the upper ring and another of the segments in each set of stabilisation member segments being configured to be connected to a respective one of the anchor members; and a plurality of the cladding segments.

Thus the inventive aerodrome structure uses a design philosophy encompassing a lightweight, rapidly deployable structure that comes as a contained (e.g. flat-packed) kit of parts, which can be constructed and deconstructed with minimal personnel and equipment.

The parts are pre-designed / pre-engineered / pre-fabricated for inclusion in the structure, which is modular and scalable.

In its stored (flat-packed) state the aerodrome structure has the ability to be transported (via land, sea or air) in a set of conventional haulage containers. This provides for a geographically-reusable "pop-up" infrastructure that can be positioned in either a rural, urban or city location, either at ground level or on top of a building. As a scalable, adaptable structural framework and foot print, it has a transformation capability that matches the needs of its role and the environment in which it is situated.

As drop-off and pick-up points, the operational flexibility of the aerodrome structure can ensure that Urban Air Mobility (UAM) air corridors are supplemented with safe and effective landing zones that will meet future urban aviation demands dictated by society and industry; whether there is a need to re-deploy due to population catchment changes, expanding urban environments, industrial relocations, or humanitarian aid.

In a further aspect of the disclosure, there is provided a foot for supporting a piece of infrastructure, the foot comprising:.

This allows for rapid deployment of the foot for rapid construction of infrastructure in a range of settings without the requirement to alter the landscape, or to undertake piling operations or to pour concrete.

In this way, the foot may be particularly appropriate for non-permanent structures or structures deployed rapidly, such as in disaster areas.

The foot may alternatively be termed a terrain adjustable foundation.

One particular application of the foot may be for use in supporting a structure configured for use as an airport for vertical take off and landing aircraft.

The first pair of legs may comprise a first leg and a second leg, wherein the first leg and the second leg are mutually parallel. The second pair of legs may comprise a third leg and a fourth leg, wherein the third leg and the fourth leg are mutually parallel.

The first pair of legs may be parallel to the second pair of legs.

The first pair of legs may project upwards from the first portion of the platform entirely within a first area defined by a first boundary that links the first four rods; and the second pair of legs may project upwards from the second portion of the platform entirely within a second area defined by a second boundary that links the second four rods.

The first four rods may be symmetrically disposed relative to the first base and the second four rods may be symmetrically disposed relative to the second base.

The first pair of legs may be symmetrically disposed relative to the first base and the second pair of legs may be symmetrically disposed relative to the second base.

In this way, stability of the foot may be increased.

A lower surface of the first base and a lower surface of the second base each comprise a material having a coefficient of friction that exceeds a friction threshold.

In this way, a risk of lateral slippage of the foot is reduced.

In a further aspect of the disclosure there is provided an assembly comprising a pair of feet, wherein each foot is in accordance with a foot of the disclosure. The assembly further comprises:
a connecting shaft extending between the beam of the first foot and the beam of the second foot:.

In this way, an assembly may maintain horizontality when each of the two feet is placed on separately inclined surfaces.

Fine adjustment to achieve horizontality of the beam may be achievable by further adjustment of the extent to which the first four rods extend between the first base and the first portion and by further adjustment of the extent to which the second four rods extend between the second base and the second portion.

In this way, the expectation of horizontality not just for a single foot, but across the assembly having more than one foot, may be increased.

In a further aspect of the disclosure there is provided a structure comprising a plurality of pairs of feet as already described, and a plurality of connecting shafts, wherein each pair of feet of the plurality of pairs of feet is connected to each adjacent pair of feet by a connecting shaft of the plurality of connecting shafts.

In this way, a building having a horizontal floor may be rapidly constructed on uneven ground.

In a further aspect of the disclosure there is provided a structure having a polygon plan view shape having N sides, comprising N feet in accordance with the disclosure and N connecting shafts.

All of the N connecting shafts may sit in a first horizontal plane.

A floor of the structure may be supported in the first horizontal plane.

The structure may further comprise a plurality of roof members, wherein the beam of each of the plurality of feet supports a roof member and the plurality of roof members extend radially towards a central area of the structure.

A central area of the structure may comprise a ring portion within which is located a platform for vertical take off and landing aircraft.

Any apparatus, system, or structural feature described herein may be provided as a method feature, and vice versa. Moreover, it will be understood that the present disclosure is described herein purely by way of example, and modifications of detail can be made within the scope of the claims. Furthermore, it will be understood by the skilled person that particular combinations of the various features described and defined herein may be implemented and/or supplied and/or used independently. In particular, it will be understood by the skilled person that any feature described in relation to a particular aspect herein may also be applied to another aspect described herein, in any appropriate combination.

Referring to <FIG>, an aerodrome structure <NUM> or installation according to the disclosure has the form of a shallow, truncated cone. The aerodrome structure <NUM> includes a platform <NUM> arranged to be raised and lowered, between the ground within the interior of the aerodrome structure <NUM> and an upper region or top of the aerodrome structure <NUM> (per the position of the platform <NUM> shown in <FIG>). With regard to departing aircraft, the platform <NUM> functions to move the aircraft from ground level to the top of the aerodrome structure <NUM> and provides a take-off pad for the aircraft. With regard to arriving aircraft, the platform <NUM> provides a landing pad and serves to move the aircraft from the top of the aerodrome structure <NUM> to ground level.

As can be seen in <FIG>, the platform <NUM> is one element of a lift structure <NUM> which forms a central, core assembly of the aerodrome structure <NUM>. As will be explained herein, the lift structure <NUM> and its platform <NUM> enables the construction of the aerodrome structure <NUM> itself, as well as handling the movements of aircraft when the aerodrome structure <NUM> is in-service.

The lift structure <NUM> comprises an upstanding tubular frame including an upper ring <NUM> located directly above a lower or base ring <NUM> which lies on the ground. The upper ring <NUM> is supported over the base ring <NUM> by a plurality of substantially vertical lift structure columns <NUM> which are spaced apart from each other around the circumference of the upper and base rings <NUM>, <NUM>. In this example, the lift structure comprises eight lift structure columns <NUM>. In this example, the lift structure columns <NUM> comprise steel. In this example, the upper and base rings <NUM>, <NUM> comprise steel.

The platform <NUM> is disc-shaped and is located within the tubular frame and extends laterally or horizontally, i.e. in a direction which is substantially perpendicular with the longitudinal or vertical axis of the tubular frame. The platform <NUM> has a diameter or span which is slightly smaller than that of the base ring <NUM> and the upper ring <NUM>. In this example, the platform <NUM> comprises aluminium alloy. The platform <NUM> is movably connected to guide rails <NUM> (not shown in <FIG>) which extend between the base ring <NUM> and the upper ring <NUM> and which are spaced apart around the circumference thereof. In this example, the lift structure <NUM> comprises four guide rails <NUM>. In this example, the guide rails <NUM> comprise steel.

Lift apparatus <NUM> (not visible in <FIG>) is provided beneath the platform <NUM> (i.e. between the platform <NUM> and the underlying ground) and is arranged to raise and lower the platform <NUM> between the base ring <NUM> and the upper ring <NUM>. In this example, the lift apparatus <NUM> is supported on rest plates <NUM> (not visible in <FIG>) which are arranged within the circumference of the base ring <NUM>. Further in this example, the rest plates <NUM> are themselves supported on or between ground-based base cross-beams <NUM> (not visible in <FIG>) which extend across the diameter of the base ring <NUM> and are connected thereto. In this example, the base cross-beams <NUM> comprise steel.

The spacing of the lift structure columns <NUM> and the guide rails <NUM> is configured such as to provide a side opening <NUM> of the lift structure <NUM>, for loading an aircraft onto the platform <NUM> and unloading an aircraft from the platform <NUM> when the platform <NUM> is in a lowered position, i.e. such as to be located in the region of the base ring <NUM>. When the platform <NUM> is in a raised position, i.e. such so as to be located in the region of the upper ring <NUM>, the platform <NUM> provides a take-off and landing pad for an aircraft. Thus the platform <NUM> may also be referred to as a Final Approach and Take-Off or "FATO" platform. As such, the platform <NUM> is configured to meet relevant aviation regulations. In this regard, the platform <NUM> comprises appropriate markings, navigation lighting and equipment, and a surface material which is non-slip, durable, and corrosion resistant.

Still referring to <FIG>, the aerodrome structure <NUM> further comprises Y-shaped outriggers or stabilisation beams <NUM>, which provide enhanced lateral stabilisation to the lift structure <NUM> and also form an additional structure of the aerodrome structure <NUM>. In this example, the aerodrome structure <NUM> comprises six of the beams <NUM>. In this example, the beams <NUM> comprise steel. As can be seen in the drawing, the Y-shaped stabilisation beams <NUM> slope downwardly and outwardly away from the lift structure <NUM>. The two inner ends of each Y-shaped stabilisation beam <NUM> are fixedly connected to the upper ring <NUM>, in particular at the same portions of the upper ring <NUM> to which a respective two of the lift structure columns are fixedly connected. The outer end of each Y-shaped stabilisation beam <NUM> is fixedly connected to a respective anchor member <NUM> which is in contact with the ground. An outer portion of the beam <NUM> which includes said outer end is cranked downwardly, i.e. the beam <NUM> changes in plane in side profile, such as to be inclined from the ground at a greater angle than is the mid-portion of the beam <NUM>.

The aerodrome structure <NUM> further comprises a hanger structure <NUM> for accommodating aircraft entering and leaving the platform <NUM>. The hanger structure <NUM> comprises a plurality of upstanding hanger structure columns <NUM> which are fixedly connected to a plurality of hanger structure roof members <NUM>, ends of some of the hanger structure roof members <NUM> being fixedly connected to the upper ring <NUM> of the lift structure <NUM>. An outer region of the hanger structure (i.e. to the right-hand side in the sense of <FIG>) includes an entrance/exit for aircraft to enter/leave the aerodrome structure <NUM>.

Referring again to <FIG>, the aerodrome structure <NUM> further comprises an outer covering or cladding which is attached to the Y-shaped stabilisation beams <NUM> and defines a covered inner volume of the aerodrome structure <NUM>. The cladding comprises a plurality of cladding segments <NUM>, each of the segments spanning a space between an adjacent pair of the Y-shaped stabilisation beams. In this example, the cladding segments <NUM> comprise a fabric material, more particularly a PVC-coated polyester.

In this example: the aerodrome structure <NUM> has a height at the upper ring <NUM> of about <NUM> and the upper ring <NUM> has a diameter of about <NUM>; the platform <NUM> has a diameter of about <NUM>; each of the Y-shaped stabilisation beams <NUM> has a length of about <NUM>.

The aerodrome structure <NUM> is most suitable for vertical take-off and landing (VTOL) aircraft. That is, aircraft that can hover, take off, and land vertically. This includes various kinds of aircraft, including rotary-wing aircraft, i.e. helicopters, and other aircraft with powered rotors, such as cyclogyros, cyclocopters and tiltrotors. Also included are VTOL aircraft that may operate in other modes, e.g. STOL (short take-off and landing), or STOVL (short take-off and vertical landing), and lighter-than-air aircraft. The aircraft may be manned or unmanned ("drones" or UAVs). The aircraft may carry passengers or cargo, or both. In some applications, the aircraft may carry humanitarian aid supplies, or military equipment such as weaponry. The aircraft may be powered by electricity, fossil-fuels, or a combination of these.

The aerodrome structure <NUM> or installation may comprise its own supply of electrical power, for example by means of wind, solar or hydro, or alternatively may rely on an external supply, for example from the mains grid where the aerodrome structure <NUM> is located. Whatever the supply source, the aerodrome structure <NUM> or installation may be arranged to store electrical power, for example using batteries. Excess stored electricity may be fed into the mains grid, if desired. The electrical energy may be used to recharge electricallypowered aircraft which use the aerodrome structure <NUM>. Furthermore, the aerodrome structure <NUM> may include storage facilities for fossil fuels or hydrogen, in order to be able to refuel aircraft using those fuels.

The aerodrome structure <NUM> is constructed from its component parts which are originally packaged in containers, for example standard-size shipping containers, for convenient deployment to the site where the aerodrome structure <NUM> is to be erected. Some examples of the component parts of the lift structure <NUM> are shown in <FIG>, in particular the upper and base rings <NUM>, <NUM> (see <FIG>), the lift structure columns <NUM> (see <FIG>), and the Y-shaped stabilisation beams <NUM> (see <FIG>). As can be seen in the drawings, in this example each of these component parts, as well as some or all of the other component parts of the aerodrome structure <NUM>, comprises a plurality of discrete segments or elements which are configured to be connected or joined together in order to form the parts. In this example, the elements each have a length of about two metres.

The construction or assembly of the aerodrome structure <NUM> will now be described, with particular reference to <FIG>.

Referring to <FIG>, the elements of the component parts of the aerodrome structure <NUM> are taken from their containers and arranged on the ground at the construction site. The elements of some of the component parts are then connected together in order to form the individual component parts (not all of which are shown in <FIG>). Thus, in this example, the relevant elements are connected together to first form the base ring <NUM>, the lift structure columns <NUM>, the base cross-beams <NUM>, the Y-shaped stabilisation beams <NUM>, the hanger structure columns <NUM>, and the hanger structure roof members <NUM>. Furthermore, ends of the hanger structure columns <NUM> are hingedly or pivotably connected to respective ends of the hanger structure roof members <NUM> in order to pre-assemble the hanger structure <NUM>.

The base cross-beams <NUM> are placed on the ground inside the circumference of the base ring <NUM> and their ends are attached to respective portions of the base ring <NUM>. The rest plates <NUM> are mounted on or between the base cross-beams <NUM>. The lift apparatus <NUM> is mounted on the rest plates <NUM>.

Referring to <FIG> and <FIG>, each segment of the platform <NUM> (only the outer circumference of which is shown in the drawings) is positioned over the lift apparatus <NUM> (not shown) and is attached thereto. The segments of the platform <NUM> are connected together, either before or after attachment to the lift apparatus <NUM>. Thus, the platform <NUM> is positioned and supported slightly above the level of the base ring <NUM>.

The elements of the guide rails <NUM> are assembled and the guide rails <NUM> are raised into an upright position and their lower ends are fixedly attached to the base ring <NUM>. Alternatively, the elements of the guide rails <NUM> may be connected one on top of another such as to build the guide rails <NUM> up in the vertical direction from the base ring <NUM>. Preferably, temporary stabilisation struts <NUM> are attached to the outer surfaces of the guide rails <NUM> in order to provide additional lateral stabilisation during assembly. Thus, the guide rails <NUM> extend vertically from the base ring <NUM> and surround or encircle the platform <NUM>. Preferably, the outer edge of the platform <NUM> includes radially-extending projections which are received in channels provided in the inner surfaces of the guide rails <NUM>, thereby to engage the platform <NUM> with the guide rails <NUM> and prevent rotational movement of the platform <NUM> with respect to the guide rails <NUM>, which themselves provide improved lateral stability.

The segments of the upper ring <NUM> are positioned on the platform <NUM> and connected together to form the upper ring <NUM>. Since the diameter of the upper ring <NUM> is slightly greater than the diameter of the platform <NUM>, at least one temporary cross-member may be attached to the upper ring <NUM> such as to extend between opposing portions of the upper ring <NUM>, in order to support the upper ring <NUM> on the platform <NUM>. Alternatively, the same supporting effect may be achieved by attaching a temporary inner lip part to the upper ring <NUM>, such that the underside of the inner lip rests on the radially-outer part of the platform <NUM>.

With the upper ring <NUM> assembled and rested on the platform <NUM>, the lift structure columns <NUM> are arranged in spaced-relationship with each other around the circumference of the upper ring <NUM> so as to project radially therefrom. The inner ends of the lift structure columns <NUM> are hingedly or pivotably connected to the upper ring <NUM>, while the outer ends of the lift structure columns <NUM> are rested on the ground. Thus, the lift structure columns <NUM> slope downwardly from the upper ring <NUM> to the ground (as depicted by the dashed lines of the lift structure columns <NUM> in <FIG>).

In a similar manner, the Y-shaped stabilisation beams <NUM> (not shown in <FIG>) are arranged in spaced-relationship with each other around the circumference of the upper ring <NUM> so as to project radially therefrom. The inner ends of each Y-shaped stabilisation beam <NUM> are hingedly or pivotably connected to the upper ring <NUM>, at the same portions of the upper ring <NUM> to which a respective two of the lift structure columns are hingedly or pivotably connected, while the outer end of each Y-shaped stabilisation beam <NUM> is rested on the ground. Thus, the Y-shaped stabilisation beams <NUM> slope downwardly from the upper ring <NUM> to the ground.

Free ends of the hanger structure roof members <NUM> of the pre-assembled hanger structure <NUM> (not shown in <FIG>) are hingedly or pivotably connected to the upper ring <NUM>. Furthermore, the hanger structure columns <NUM> (which it will be recalled are hingedly or pivotably connected to the other ends of the respective hanger structure roof members <NUM>) are extended radially outward so as to lie in a generally straight line with the hanger structure roof members <NUM>). Thus, the hanger structure roof members <NUM> and the hanger structure columns <NUM> slope downwardly from the upper ring <NUM> to the ground.

The lift apparatus <NUM> is activated in order to raise the platform <NUM>, and thereby the upper ring <NUM> which rests on the platform <NUM>, vertically upward. The upstanding guide rails <NUM> serve to guide the platform <NUM> in its upward motion. As the upper ring <NUM> ascends with the platform <NUM>, the pivotably-connected lift structure columns <NUM> freely rotate in a plane which is perpendicular with the plane of the upper ring <NUM>. Thus, the lift structure columns <NUM> are drawn upward and inward, their inclination relative to the ground progressively increasing until they reach a substantially vertical condition. Preferably, the outer ends of the lift structure columns <NUM> are equipped with castor wheels to facilitate their inward travel over the ground.

In a similar manner, the Y-shaped stabilisation beams <NUM> (which are of greater length than the lift structure columns <NUM>) are also drawn upward and inward during the upward motion of the platform <NUM> and the upper ring <NUM>, their inclination relative to the ground also progressively increasing until they reach an inclination angle of around <NUM> degrees, in this example. Preferably, the outer ends of the Y-shaped stabilisation beams <NUM> are equipped with castor wheels to facilitate their inward travel over the ground.

Also in a similar manner, the hanger structure roof members <NUM> and the hanger structure columns <NUM> are drawn upward and inward during the upward motion of the platform <NUM> and the upper ring <NUM>, their inclination relative to the ground also progressively increasing. The inclination of the hanger structure columns <NUM> may be manually adjusted during (or after) the rise of the platform <NUM>, in order to set the desired final inclination of the hanger structure roof members <NUM> relative to the ground. For example, the hanger structure columns <NUM> may be set at an inclination of about <NUM> degrees, i.e. substantially vertical, and the hanger structure roof members <NUM> at an inclination of zero degrees, i.e. substantially horizontal. Preferably, the outer ends of the hanger structure columns <NUM> are equipped with castor wheels to facilitate their inward travel over the ground.

The lift apparatus <NUM> is deactivated in order to halt the upward movement of the platform <NUM>. Thus, the platform <NUM> is used to raise the upper ring <NUM>, the hanger structure columns <NUM>, the Y-shaped stabilisation beams <NUM>, and the hanger structure <NUM>, into position.

If fitted, the castor wheels are removed from the lift structure columns <NUM>, the Y-shaped stabilisation beams <NUM> and the hanger structure columns <NUM>. The lift structure columns <NUM>, the Y-shaped stabilisation beams <NUM>, and the hanger structure roof members <NUM>, are locked in place, such as to transition from the pivotable relationship with the upper ring <NUM> to a fixed relationship therewith. Locking may be achieved manually, for example by a bolted connection, or automatically, for example by a spring-loaded locking mechanism provided at the interface with the upper ring <NUM>. Self-locking mechanisms are commonly found in space-frame constructions, for example, with which the person skilled in the general art of construction will be familiar. Similarly, the hanger structure roof members <NUM> are locked in place relative to the hanger structure columns <NUM>.

The lower ends (i.e. the aforementioned outer ends) of the lift structure columns <NUM> are fixedly connected to the base ring <NUM>. In this way, the lift structure columns <NUM> provide a rigid connection between the upper and base rings <NUM>, <NUM>. In a similar manner, the upper ends of the guide rails <NUM> are rigidly connected to the upper ring <NUM> in order to provide additional structural rigidity to the upstanding tubular frame.

The outer ends of the Y-shaped stabilisation beams <NUM> are connected to their respective anchor members <NUM>, which are provided on the ground, thereby enhancing lateral stability. The anchor members <NUM> may be placed on the ground in pre-determined positions prior to the upward and inward movement of the Y-shaped stabilisation beams <NUM>, or alternatively put in place after said movement according to the final positions of the outer ends of the beams <NUM>.

The temporary stabilisation struts <NUM> attached to the outer surfaces of the guide rails <NUM> are no longer required and are therefore removed. With the upper ring <NUM> thus fixed firmly in place, the temporary cross-member (or the temporary inner lip part) (not shown in the drawings) is also no longer needed and is therefore removed from the upper ring <NUM>.

Referring to <FIG>, in this example the aerodrome structure <NUM> comprises additional outriggers or stabilisation beams <NUM> which are disposed between the Y-shaped stabilisation beams <NUM>. The additional stabilisation beams <NUM> comprise steel. An inner end of each additional stabilisation beam <NUM> is connected to the upper ring <NUM>, while the outer end is connected to a respective additional supporting anchor member <NUM>. Thus the additional stabilisation beams <NUM> slope downwardly and outwardly away from the lift structure <NUM>, in a similar manner to the Y-shaped stabilisation beams <NUM>. Furthermore, the side profile of the additional stabilisation beams <NUM> is similar to that of the Y-shaped stabilisation beams <NUM>, including the downwardly-cranked outer portion. The additional stabilisation beams <NUM> are erected in the same manner as the Y-shaped stabilisation beams <NUM>, i.e. the beams <NUM> are hingedly or pivotably attached to the upper ring <NUM>, raised into the elevated position by the platform <NUM>, and locked in place relative to the upper ring <NUM> once in the elevated position.

Also as shown in <FIG>, in this example the aerodrome structure <NUM> comprises horizontally-arranged bracing members <NUM> which connect adjacent pairs of the Y-shaped stabilisation beams <NUM> and the additional stabilisation beams <NUM>. The bracing members <NUM> may comprise steel. The bracing members <NUM> are connected to the beams <NUM>, <NUM> after the beams <NUM>, <NUM> have been placed into position as described herein above. In this example, the bracing members <NUM> form three rings which each extend circumferentially around the aerodrome structure <NUM>, the rings being located at an upper region, a lower region, and a mid-region of the aerodrome structure <NUM>. It will be understood that the bracing members <NUM> provide the aerodrome structure <NUM> with additional structural rigidity.

Referring next to <FIG>, the Y-shaped stabilisation beams <NUM> and the additional stabilisation beams <NUM> provide a means of support for the cladding segments <NUM> which generally cover the aerodrome structure <NUM>. More particularly, each of the Y-shaped stabilisation beams <NUM> and the additional stabilisation beams <NUM> is I-shaped in cross-section and twin luff tracks <NUM> or elongate channels are provided on the top of the flange parts of the beam <NUM>. Each of the luff tracks <NUM> is configured to receive an edge of one of the cladding sections <NUM>, the edge including a thickened keeper portion 42a for retaining the edge in the luff track <NUM>.

The installation of the cladding segments <NUM> is shown in <FIG>. During installation, the platform <NUM> is raised to the upper ring <NUM>. As mentioned herein above, each of the cladding segments <NUM> comprises a PVC-coated polyester material. Two personnel P1, P4 on the platform <NUM> feed the keeper portions 42a of opposing edges of a strip of the material, i.e. one cladding segment <NUM>, into the upper ends of the luff tracks <NUM> provided on adjacent additional stabilisation beams <NUM>. The end of the cladding segment <NUM> is pulled outward and downward by two further personnel P2, P3 on the ground, for example using a winch and a cable attached to the end of the strip. Thus the cladding segment <NUM> is drawn through the luff tracks <NUM> so as to extend from the upper ring <NUM> to the outer ends of the beams <NUM> at the ground, thereby spanning the gap between the two adjacent beams <NUM>.

Each cladding segment <NUM> is preferably held in tension in order to prevent sagging. The tension may be provided by a weighted portion of the outer/lower end of the cladding segment <NUM>. Sagging may also be prevented by positioning the cladding segments <NUM> so that they overlie the bracing members <NUM>, such that the bracing members <NUM> resist downward movement of the cladding segments <NUM>.

All of the cladding segments <NUM> are installed in this way (some between adjacent pairs of the additional stabilisation beams <NUM> (as shown in <FIG>) and others between adjacent additional stabilisation beams <NUM> and Y-shaped stabilisation beams <NUM>), so that the cladding generally covers the aerodrome structure <NUM> from its top to its base. Thus, the Y-shaped stabilisation beams <NUM> and the additional stabilisation beams <NUM> function as structural roof members for supporting the cladding segments <NUM>, as well as providing enhanced lateral stability for the lift structure <NUM>.

In this example, the cladding segments <NUM> are opaque such as to prevent sunlight from passing through the cladding segments <NUM> into the interior of the aerodrome structure <NUM>. Referring to <FIG>, transparent PVC window panels <NUM> are provided, in the triangular openings formed by the inner ends of the Y-shaped stabilisation beams <NUM> and the upper ring <NUM>, in order to allow sunlight into the aerodrome structure <NUM>.

Referring to <FIG>, transparent PVC window panels <NUM> are also provided around the lift structure <NUM>, the panels <NUM> being attached to the lift structure columns <NUM> and extending between the base ring <NUM> and the upper ring <NUM>. These PVC window panels <NUM> allow views of the platform <NUM> and any aircraft thereon from positions within the interior of the aerodrome structure <NUM>. A curtain portion 54a of the panels <NUM> allows for access through the above-mentioned side opening <NUM> of the lift structure <NUM>, for loading and unloading aircraft on and off the platform <NUM>.

It will be understood that some of the above-described assembly steps may be performed in a different order. For example, as described herein above, the inner ends of each of the lift structure columns <NUM>, the Y-shaped stabilisation beams <NUM>, the additional stabilisation beams <NUM>, and the hanger structure roof members <NUM> of the pre-assembled hanger structure <NUM>, are hingedly or pivotably connected to the upper ring <NUM>. The lift apparatus <NUM> is then activated in order to raise the platform <NUM>, and thereby the upper ring <NUM> which rests on the platform <NUM>, vertically upward, thereby raising the lift structure columns <NUM>, the Y-shaped stabilisation beams <NUM>, the additional stabilisation beams <NUM>, and the hanger structure roof members <NUM> and the hanger structure columns <NUM>, which are all then locked into position relative to the upper ring <NUM> in order to provide a rigid structure.

In an alternative assembly procedure, only the lift structure columns <NUM> are hingedly or pivotably connected to the upper ring <NUM>, raised into position, and subsequently locked into fixed connection with the upper ring <NUM>. The lower ends of the lift structure columns <NUM> are then also fixedly connected to the base ring <NUM>, as has been described herein above. In this way, the lift structure <NUM> is erected to form a rigid, free-standing structure with the upper ring <NUM> fixed in space at the top. The platform <NUM> is then lowered and the inner ends of one or more of the Y-shaped stabilisation beams <NUM>, the additional stabilisation beams <NUM>, and the hanger structure roof members <NUM> of the pre-assembled hanger structure <NUM>, are rested on the platform <NUM> and temporarily attached thereto, for example using chains or ropes or the like. The platform <NUM> is then raised to the upper ring <NUM> and the inner ends of the Y-shaped stabilisation beams <NUM>, the additional stabilisation beams <NUM>, and the hanger structure roof members <NUM> are released from the platform <NUM> and fixedly connected (locked) to the upper ring <NUM>. It will be understood that the platform <NUM> may be used to move all of these structural elements from the ground to the upper ring <NUM> either simultaneously or sequentially.

Certain features of the aerodrome structure <NUM> will now be discussed in greater detail.

Referring to <FIG>, the base ring <NUM> may be firmly supported on the ground by a plurality of base ring support plates <NUM> (only one of which is shown in the drawing along with a portion of the base ring <NUM>). Each of the base ring support plates <NUM> comprises upstanding buttress members 56a which form a channel for receiving and supporting a portion of the base ring <NUM>. This portion of the base ring <NUM> includes an upstanding projection 18a for connection with a respective one of the upstanding lift structure columns <NUM>, as has been described herein above. The base ring support plates <NUM> effectively increase the area of the "footprint" of the base ring <NUM>, thereby spreading the load (weight) of the lift structure <NUM> over the ground. As has been mentioned herein above, the lift apparatus <NUM> supports the overlying platform (not shown in <FIG>) and is itself supported by the underlying rest plates <NUM> which are located on or between the base cross-beams <NUM>. This underlying structure provides a firm supportive base for the lift apparatus <NUM> and the platform <NUM>.

Referring also to <FIG>, the lift apparatus <NUM> itself comprises at least one lift mechanism and associated ancillary equipment including a power supply. The lift mechanism may be operated electrically or hydraulically, or a combination of these. The lift mechanism is preferably compact in order to minimise the space required beneath the platform <NUM>. Suitable lift mechanisms include scissor lifts, telescopic lifts, and chain link lifts. Preferably, a plurality of lift mechanisms are provided at strategic locations beneath the platform <NUM> in order to spread the lifting force over the lower surface of the platform <NUM>. The multiple lift mechanisms may be arranged to be synchronised using gearboxes and drive shafts. This example includes a plurality of chain link lifts <NUM>, as shown in <FIG>. A chain link lift is a type of lift wherein a plurality of connected chain links are deployed outwardly and upwardly from a horizontal storage housing such as to form a rigid, vertical column. An example of a suitable chain link lift is that produced by Serapid (France), which is described as being an electromechanical telescopic actuator specifically designed for the vertical movement of heavy loads using rigid chain technology.

<FIG> shows two of the anchor members <NUM> which support the Y-shaped stabilisation beams <NUM> at the outer periphery of the aerodrome structure <NUM>. In this example, the anchor members <NUM> are configured to rest on the ground, rather than be sunk into the ground, thereby avoiding a need for digging conventional foundations. Each anchor member <NUM> comprises ballast units, for example comprising concrete blocks or water-filled containers, in order to provide sufficient weight to resist movement relative to the ground.

The anchor members <NUM> are configured to be height adjustable in order to accommodate non-level ground at the site where the aerodrome structure <NUM> is erected. In this way the need to first level the ground may be avoided. In this example, each anchor member <NUM> comprises an upper plate structure <NUM> which connects with the Y-shaped stabilisation beam <NUM>, and a lower plate structure <NUM> which lies on the ground. The upper plate structure <NUM> comprises laterally-extending tubular members <NUM>, each configured to receive an end of a telescopic rod (not shown in <FIG>) for connecting together the upper plate structures <NUM> of an adjacent two of the anchor members <NUM>.

The upper and lower plate structures <NUM>, <NUM> are connected to each other by upstanding struts, in this example T-shaped members <NUM>, the height of which determines the vertical distance between the upper and lower plate structures <NUM>, <NUM> and thereby the height from a ground datum of the Y-shaped stabilisation beams <NUM>. The required heights of the T-shaped members <NUM> are predetermined by taking a survey of the ground at the site.

Thus, still referring to <FIG>, the anchor member <NUM> on the right side rests on a part of the ground that is higher than the piece of ground which supports the anchor member <NUM> on the left side. Accordingly, the heights of the T-shaped members <NUM> are selected so that the vertical distance, between the upper and lower plate structures <NUM>, <NUM> of the left side anchor member <NUM>, is greater than the vertical distance between the upper and lower plate structures <NUM>, <NUM> of the right side anchor member <NUM>. In addition, the lower plate structure <NUM> of each anchor member <NUM> is configured to be adjustable in tilt angle, in order to accommodate sloping ground underneath the lower plate structure <NUM>.

In this way, the lower ends of the Y-shaped stabilisation beams <NUM> are positioned so as to lie in the same horizontal plane and therefore to be level with each other. It will be understood that the position of each anchor member <NUM> can be adjusted as required prior to locking the Y-shaped stabilisation beams <NUM> relative to the upper ring <NUM>, as has been described herein above. With the lower ends of the Y-shaped stabilisation beams <NUM> in the desired position, adjacent pairs of the laterally-extending tubular members <NUM> may be connected together using the insertable telescopic rods, thereby providing additional bracing to the structure of the aerodrome structure <NUM> at ground level.

As has been mentioned herein above, the component parts of the aerodrome structure <NUM> are originally packaged in containers, for example standard-size shipping containers, for convenient deployment to the site where the aerodrome structure <NUM> is to be erected. In order to minimise the number and volume of the containers, the component parts are preferably broken down into discrete segments or elements, as has been described, this being a highly space-efficient means of packaging the aerodrome structure <NUM>.

The contents of the containers are preferably arranged to suit the order of assembly of the aerodrome structure <NUM>, as discussed herein above. For example, the base ring <NUM> and the base cross-beams <NUM> are preferably provided in the same container, since the base cross-beams <NUM> are to be connected to the base ring <NUM> once the base ring <NUM> has been set out on the ground.

In one example, the aerodrome structure <NUM> is packaged in a total of eight containers, or container groups each comprising a plurality of individual containers, as follows:.

Preferably, the containers include hoisting equipment to ease removal of the parts of the aerodrome structure <NUM> from the containers. The containers also preferably include wheels, so that they can be more easily moved by personnel to the exact location on-site where the parts are required for assembly.

The aerodrome structure <NUM> may be disassembled or dismantled and removed from site, if it is no longer required. The disassembly sequence is essentially the reverse of the assembly sequence, as follows.

The platform <NUM> is raised to its upper position. The cladding segments <NUM> are each drawn upwardly and inwardly through their supporting luff tracks <NUM>, for example by personnel using a winch located on the platform <NUM>. Thus the cladding segments <NUM> are removed from the aerodrome structure <NUM>. The transparent PVC window panels <NUM> are removed from the triangular openings at the inner ends of the Y-shaped stabilisation beams <NUM>. The transparent PVC window panels <NUM> are removed from the lift structure <NUM>.

The insertable telescopic rods are removed from the laterally-extending tubular members <NUM> of the anchor members <NUM>. The bracing members <NUM> are disconnected and removed from the adjacent pairs of the Y-shaped stabilisation beams <NUM> and the additional stabilisation beams <NUM>. The lower ends of the Y-shaped stabilisation beams <NUM> are disconnected from the anchor members <NUM>.

The temporary stabilisation struts <NUM> are re-attached to the outer surfaces of the guide rails <NUM>. The upper ends of the guide rails <NUM> are disconnected from the upper ring <NUM>. The lower ends of the lift structure columns <NUM> are disconnected from the base ring <NUM>.

The inner ends of the lift structure columns <NUM>, the Y-shaped stabilisation beams <NUM>, the additional stabilisation beams <NUM>, and the hanger structure roof members <NUM>, are unlocked so as to restore their pivotable relationship with the upper ring <NUM>. Castor wheels are attached to the lower/outer ends of the lift structure columns <NUM>, the Y-shaped stabilisation beams <NUM>, and the additional stabilisation beams <NUM>.

The lower ends of the pivotably-connected lift structure columns <NUM> are displaced outwardly (manually by personnel, or automatically, e.g. by a spring-loaded mechanism) in order to place them into a non-vertical condition. The lift apparatus <NUM> is activated in order to lower the platform <NUM>. As the upper ring <NUM> descends vertically with the platform <NUM>, the lift structure columns <NUM> freely rotate in a plane which is perpendicular with the plane of the upper ring <NUM>. Thus, the lift structure columns <NUM> are pushed downward and outward, their inclination relative to the ground progressively decreasing. The pivotably-connected additional stabilisation beams <NUM> and hanger structure roof members <NUM> are similarly pushed downward and outward.

The lift apparatus <NUM> is deactivated in order to halt the downward movement of the platform <NUM> at the region of the base ring <NUM>. In this lowered position of the platform <NUM>, the lift structure columns <NUM>, the Y-shaped stabilisation beams <NUM>, the additional stabilisation beams <NUM>, and the hanger structure roof members <NUM>, slope downwardly from the upper ring <NUM> to the ground.

The temporary cross-member (or temporary inner lip part) is re-attached to the upper ring <NUM> in order to support the upper ring <NUM> on the platform <NUM>. The inner ends of the lift structure columns <NUM>, the Y-shaped stabilisation beams <NUM>, the additional stabilisation beams <NUM>, and the hanger structure roof members <NUM>, are disconnected and removed from the upper ring <NUM>. The temporary cross-member (or temporary inner lip part) is removed from the upper ring <NUM> and the segments of the upper ring <NUM> are separated from each other. The upper ring <NUM> is thus dismantled.

The temporary stabilisation struts <NUM> are removed from the guide rails <NUM>. The guide rails <NUM> are disconnected from the platform <NUM> and the elements of the guide rails <NUM> are separated from each other. The guide rails <NUM> are thus dismantled.

The segments of the platform <NUM> are disconnected from each other, either before or after detachment from the lift apparatus <NUM>. The lift apparatus <NUM> is removed from the rest plates <NUM>. The rest plates <NUM> are removed from the base cross-beams <NUM>. The ends of the base cross-beams <NUM> are detached from their respective portions of the base ring <NUM>. The segments of the base ring <NUM> are separated from each other. The base ring <NUM> is thus dismantled.

The ends of the hanger structure columns <NUM> are disconnected from the respective ends of the hanger structure roof members <NUM>. The relevant elements are disconnected from each other to dismantle the lift structure columns <NUM>, the Y-shaped stabilisation beams <NUM>, the additional stabilisation beams <NUM>, the hanger structure columns <NUM>, and the hanger structure roof members <NUM>.

The component parts of the aerodrome structure <NUM> are put back into their containers. The containers are loaded onto vehicles and taken away from the site. If desired, the aerodrome structure <NUM> may be assembled once more at a different site.

Some variants of the aerodrome structure and its structural parts will now be described.

In the above-described example, the pre-assembled platform <NUM> comprises a plurality of segments or elements, for ease of packaging, transportation and handling. Once assembled and integrated into the lift structure <NUM>, the platform <NUM> is a single piece. In another example, however, the assembled and integrated platform <NUM> comprises two or more discrete pieces or parts. That is, the platform <NUM> is split, segmented, or partitioned. In such an example, the lift apparatus <NUM> is configured to operate the different parts of the platform <NUM> independently of each other. Thus, a first part of the platform <NUM> may be activated to be raised while at the same time a second part of the platform <NUM> may be activated to be lowered. Or, first and second parts of the platform <NUM> may be activated to be raised, or lowered, at the same time but at different velocities. Also in such an example, first and second parts of the platform <NUM> may be activated to as to be raised or lowered together at the same velocity, such that the two parts behave as though they were a single platform <NUM>. Splitting the platform <NUM> into discrete parts in this manner advantageously increases flexibility with regard to aircraft handling.

In the above-described example, guide rails <NUM> are connected to the base ring <NUM> to enhance the lateral stability of the lift structure <NUM> and the platform <NUM> thereof. The guide rails <NUM> are particularly effective when used in combination with the plurality of chain link lifts <NUM>, which also form part of the above-described example, since each of the chain link lifts <NUM> exerts a point load on a small portion of the platform <NUM>. However, the guide rails <NUM> may be omitted in examples which comprise different lift mechanisms, for example a scissor lift, where the lifting force may be applied over a larger area of the platform <NUM>. Furthermore, the guide rails <NUM> may even be omitted from examples which utilise chain link lifts <NUM>, since the size and weight of the platform <NUM>, and/or the number and positioning of the chain link lifts <NUM>, may be such that the chain link lifts <NUM> themselves provide sufficient lateral stability to the platform <NUM>. Thus it will be understood that the guide rails <NUM> (and of course the temporary struts <NUM> that may be used in conjunction with the guide rails <NUM>) are an optional feature of the aerodrome structure of the disclosure.

While in the above-described example some of the structural elements of the aerodrome structure <NUM> comprise steel, in other examples different materials may be employed. These include, but are not limited to, metals and metal alloys, for example aluminium alloy or titanium alloy, plastics materials, composite materials such as carbon fibre, and wood, or any combination of these. Preferably the structural elements are lightweight, fire resistant, and corrosion resistant.

While in the above-described example the cladding segments <NUM> of the aerodrome structure <NUM> comprise PVC-coated polyester, in other examples different materials may be employed. These include, but are not limited to, metals and metal alloys, for example aluminium, plastics materials, composite materials such as carbon fibre, and wood, or any combination of these. Preferably the cladding segments <NUM> are flexible, lightweight, water resistant, fire resistant, and corrosion resistant.

While in the above-described example the anchor members <NUM> are rested on the ground, in other examples the anchor members <NUM> are partially or fully buried in the ground in order to support the Y-shaped stabilisation beams <NUM>.

While in the above-described example the upper and base rings <NUM>, <NUM> of the lift structure are circular in shape, in other examples the upper and base rings are non-circular, for example oval, elliptical, or rectangular, for example square.

While in the above-described example the cladding comprises a fabric material, in particular PVC-coated polyester, other examples may include different kinds of cladding. In one example, mounting tracks are attached to the upper surfaces or the undersides of the Y-shaped stabilisation beams <NUM> and/or the additional stabilisation beams <NUM>. Click-on panels or screens are then pressed into the tracks so as to cover the aerodrome structure <NUM>. The click-on methodology is less labour intensive and more time-efficient than other means of attachment such as screw fixings. It also requires no specialist skills or tools.

While in the above-described example the stabilisation beams <NUM> are Y-shaped, in other examples the beams have other shapes. For example, the stabilisation beams may be elongate and generally straight in plan view. Also, while in the above-described example the aerodrome structure <NUM> includes additional stabilisation beams <NUM>, in other examples these are omitted. It will be understood that the aerodrome structure <NUM> may comprise any number and form of stabilisation beams, provided that the beams extend from the lift structure (preferably the upper ring thereof) to the ground, both in order to enhance lateral stability of the lift structure and also to provide a structure for supporting the external cladding which defines the interior volume of the aerodrome structure <NUM>. The stabilisation beams may be of any suitable shape in cross-section, for example the classic I-beam cross-section as shown in <FIG>.

It will be understood that, in examples which comprise stabilisation beams having shapes other than Y-shapes, the transparent PVC window panels will take a different shape than that shown in <FIG>, due to an absence of the triangular apertures formed by the Y-shaped beams in the above-described example. In such examples, the transparent PVC window panels may take any other suitable shape. One example is shown in <FIG>, wherein the transparent PVC window panels <NUM>' are generally elongate ovals which extend radially from the upper ring <NUM>.

While the above-described example comprises cladding segments <NUM> which are opaque, such as to prevent sunlight from passing through the cladding segments <NUM> into the interior of the aerodrome structure <NUM>, in other example the cladding segments <NUM> may be transparent or translucent, so as to allow sunlight to pass through the cladding segments <NUM> into the interior of the aerodrome structure <NUM>. In such examples the cladding segments <NUM> may comprise one or more of the materials mentioned herein above. In some such examples, the transparent or translucent cladding segments <NUM> are used in conjunction with windows of the aerodrome structure <NUM>, as have been described herein above. In other such examples, the windows are omitted.

While the above-described example comprises a hanger structure <NUM> including an entrance/exit for aircraft, in other examples the hanger structure <NUM> is omitted. In some such examples, one or more of the cladding segments <NUM> is configured to permit aircraft to enter and leave the interior of the aerodrome structure <NUM>. For example, referring to <FIG>, a cladding segment 42a may be configured to be rotated about a hinge point at the upper ring <NUM>, using powered hydraulic struts or the like, in order to lift the cladding segment 42a upward so as to form an opening in the side of the aerodrome structure <NUM>.

It will be understood that the aerodrome structure has been described in relation to its preferred embodiments and may be modified in many different ways without departing from the scope defined by the accompanying claims.

<FIG> shows a foot <NUM> for supporting a piece of infrastructure, such as an aerodrome structure <NUM> in accordance with the disclosure. The foot may be used in place of the anchor <NUM> described above. The foot <NUM> may be applicable to any piece of infrastructure and is not limited to use in an aerodrome structure <NUM>.

The foot <NUM> comprises a platform <NUM> having a first portion <NUM>, a second portion <NUM> and a central portion <NUM> between the first portion <NUM> and the second portion <NUM>. The first portion <NUM> comprises a first surface <NUM> and the second portion <NUM> comprises a second surface <NUM>.

The foot <NUM> also comprises a first base <NUM> configured to support the first portion <NUM> and a second base <NUM> configured to support the second portion <NUM> of the platform.

The foot <NUM> comprises at least a first four rods <NUM>, <NUM>, <NUM>, <NUM> that each extend between the first base <NUM> and the first portion <NUM>. The first four rods <NUM>, <NUM>, <NUM>, <NUM> each comprise a threaded rod configured for use with a corresponding nut in order to facilitate independent adjustment of each of the first four rods <NUM>, <NUM>, <NUM>, <NUM>. Independent adjustment means that it is possible that the length of a portion of each of the first rods that extends between the first base <NUM> and the first portion <NUM> may be different from that equivalent length for each of the other rods. In this way, the first base <NUM> may be non-parallel with the platform <NUM>. Therefore, it is possible for the first base <NUM> to be resting on an incline but for the first portion <NUM> to be adjusted so as to be horizontal.

Similarly, the foot <NUM> comprises at least a second four rods <NUM>, <NUM>, <NUM>, <NUM> that each extend between the second base <NUM> and the second portion <NUM>. The second four rods <NUM>, <NUM>, <NUM>, <NUM> each comprise a threaded rod for use with a corresponding nut in order to facilitate independent adjustment of each of the second four rods <NUM>, <NUM>, <NUM>, <NUM>. Independent adjustment means that it is possible that the length of a portion of each of the second rods that extends between the second base <NUM> and the first portion <NUM> may be different from that equivalent length for each of the other second rods. In this way, the second base <NUM> may be non-parallel with the platform <NUM> and non-parallel with the first base <NUM>. Therefore, it is possible for the first base <NUM> to be resting on an incline but for the second portion <NUM> to be adjusted so as to be horizontal.

By adjusting the first base <NUM> and the second base <NUM> appropriately, using, respectively, the first four rods <NUM>, <NUM>, <NUM>, <NUM> and the second four rods <NUM>, <NUM>, <NUM>, <NUM>, it is possible to adjust the platform <NUM> so as to be horizontal even when the first base <NUM> and the second base <NUM> are resting on inclines.

The foot <NUM> also comprises a first pair of legs <NUM>, <NUM> projecting upwards from the first portion <NUM> of the platform <NUM> and a second pair of legs <NUM>, <NUM> projecting upwards from the second portion <NUM> of the platform <NUM>.

Each leg of the first and second pairs of legs <NUM>, <NUM>, <NUM>, <NUM> may comprise a stem <NUM>, a base <NUM>, and a brace <NUM>, extending between the stem <NUM> and the base <NUM>. Each base <NUM> is parallel to the platform <NUM>. In the illustrated embodiment, the base <NUM> of each leg is fastened to the platform using fixings <NUM>.

The foot <NUM> further comprises a beam <NUM> having a first end and a second end. The first end is supported by the first pair of legs <NUM>, <NUM> and the second end is supported by the second pair of legs <NUM>, <NUM>.

The first pair of legs <NUM> ,<NUM> comprises a first range of attachment positions <NUM> for supporting the beam <NUM> at a first variety of vertical positions. The second pair of legs <NUM>, <NUM> comprises a second range of attachment positions <NUM> for supporting the beam <NUM> at a second variety of vertical positions that correspond with the first variety of vertical positions. In this way, a height of the beam <NUM> is selectable by selecting one of the first variety of vertical positions and a corresponding one of the second variety of vertical positions in such a way that the beam <NUM> is parallel to the platform <NUM>.

In the illustrated configuration the first range of attachment positions <NUM> and the second range of attachment positions <NUM> comprises a series of equally spaced apertures. The beam <NUM> comprises pairs of apertures that correspond with a pair of apertures of the attachment positions <NUM> of the legs <NUM>, <NUM>, <NUM>, <NUM>. In this way, the beam <NUM> may be positioned and fastened to a pair of apertures of the equally spaced apertures in accordance with a required height. To the extent that further, more precise, vertical adjustment is required, the first four rods <NUM>, <NUM>, <NUM>, <NUM> and the second four rods <NUM>, <NUM>, <NUM>, <NUM> may be adjusted in parallel so as to maintain horizontality of the platform <NUM> whilst enabling modest vertical adjustment of the platform <NUM>.

The apertures of the attachment positions <NUM> and the apertures in the beam <NUM> may be connected by means of bolts or threaded bar with corresponding nuts.

The foot may be of steel, of composite material, or of any other suitable material. An underside of the first base <NUM> and an underside of the second base <NUM> may be of a material having a coefficient of friction that exceeds a friction threshold in order to avoid lateral movement of the feet <NUM>. The material of the underside of the first base <NUM> and the underside of the second base <NUM> may further accommodate minor deformations so as to compensate for minor undulations in the surface on which the first base <NUM> and the second base <NUM> is supported.

<FIG> shows the foot <NUM> of <FIG> deployed with first and second ballast elements <NUM>, <NUM>. The first ballast element <NUM> is supported by the first surface <NUM> and the second ballast element <NUM> is supported by the second surface <NUM>. In this way, both the first pair of legs <NUM>, <NUM> and the second pair of legs <NUM>, <NUM> are disposed between the first and second ballast elements <NUM>, <NUM>.

The first surface <NUM> may cantilever from the first base <NUM> in a direction away from the central portion <NUM>. The second surface <NUM> may cantilever from the second base <NUM> in a direction away from the central portion <NUM>.

The ballast elements <NUM>, <NUM> may be of concrete, of steel, or of any other material of sufficient density to reduce the risk of movement of the foot <NUM>.

<FIG> shows the foot of <FIG> from a different perspective.

<FIG> shows a side view of the foot of <FIG> in situ on uneven ground. It can be seen that the first base <NUM> is on a first incline and the second base <NUM> is on a second incline different from the first incline. In this way, neither the first base <NUM> nor the second base <NUM> is horizontal yet the platform <NUM> is horizontal.

<FIG> shows exactly the same components as <FIG>, but the first base <NUM> is on a third incline and the second base <NUM> is on a fourth incline different from the third incline. In this way, neither the first base <NUM> nor the second base <NUM> is horizontal yet the platform <NUM> is horizontal. Furthermore, it can be seen that the while the ground level shown in the <FIG> embodiment is higher than the ground level shown in the <FIG> embodiment, in each case the platform <NUM> is at a height consistent with the platform <NUM> of the other foot in the other Figure. This means that when the feet shown in <FIG> and <FIG> are deployed in a single building, the floor level (consistent with the height of the beam <NUM>) is horizontal between one foot and the other.

<FIG> and <FIG> show a building <NUM>, in a side view and in a plan view, respectively, that deploys the feet <NUM> of the present disclosure. The building <NUM> in question is an airport for vertical take of and landing vehicles, also known as a vertiport. The vertiport <NUM> comprises a FATO <NUM> (Final Approach and Takeoff area) having a circular perimeter that is surrounded by an annular enclosed space bounded by an outer ring defined by the feet <NUM> of the present disclosure and an inner ring at a perimeter of the FATO <NUM>. The annular space may be covered with a roof structure <NUM>.

Claim 1:
A lift structure (<NUM>) for an aerodrome structure (<NUM>), comprising:
an upstanding tubular frame comprising an upper ring (<NUM>) located over a base ring (<NUM>) and supported thereon by columns (<NUM>);
a platform (<NUM>) located within the tubular frame; and
a lift mechanism (<NUM>) arranged to raise and lower the platform (<NUM>) between the base ring (<NUM>) and the upper ring (<NUM>),
wherein:
the columns (<NUM>) are spaced apart from each other to provide a side opening (<NUM>) for loading an aircraft onto the platform (<NUM>) and unloading an aircraft therefrom when the platform (<NUM>) is in a lowered position; and
the platform (<NUM>) provides a take-off and landing pad for an aircraft when the platform (<NUM>) is in a raised position.