GB2620559A

GB2620559A - Aerodrome structure

Info

Publication number: GB2620559A
Application number: GB2209894.1A
Authority: GB
Inventors: Singh Sandhu Harpreet; Fang-Ning Wu-Sandhu Andrea; Gough Chrispin Nicholas
Original assignee: Urban Air Port Ltd
Current assignee: Urban Air Port Ltd
Priority date: 2022-07-05
Filing date: 2022-07-05
Publication date: 2024-01-17
Also published as: WO2024008750A1; GB202209894D0

Abstract

An aerodrome structure 100 comprising a primary landing pad 120 for a vertical take-off and landing (VTOL) aircraft, the primary landing pad located in an upper plane and comprising a radially inner platform 130 and a radially outer platform 140. The inner diameter of the outer platform abuts the outer diameter of the inner platform such that the outer platform circumscribes and abuts the inner platform. There is a roof structure radially outside the outer platform, and a lift mechanism configured to lower the inner platform between the upper plane and a lower level. The outer diameter of the outer platform is at least 1.1 times that of the inner platform. There may be a secondary, static, landing pad 150 offset from the primary on the upper plane. The roof may extend to the upper level and may have a pitched portion. There may be zones around the landing pad that may be aircraft bays 160 on the lower level. There may be an aircraft transit area to facilitate movement of aircraft between the aircraft bay and the inner platform when it is lowered.

Description

Aerodrome structure

Background

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 (VTOL) aircraft. Such aircraft may be electrically-powered, or comprise hybrid power systems which combine different energy sources, and are therefore more sustainable than conventional fossil-fuelled aircraft. Furthermore, electrically-powered aircraft are more suitable for use in densely populated areas since they are quieter than conventionally powered aircraft and do not produce emissions that contribute to air pollution.

Furthermore, space may be at a particular premium in densely populated areas. There may be a need therefore for infrastructure which occupies a minimum footprint whilst at the same time accommodating aircraft capable of carrying more than a handful of passengers and/or freight.

The present disclosure aims to address this infrastructure need in an efficient, flexible, robust, and cost-effective manner. -2 -

Summary

Against this background, there is provided an aerodrome structure comprising: a primary landing pad for a vertical take off and landing aircraft, the primary landing pad being located in an upper plane and comprising a radially inner platform and a radially outer platform, wherein the radially outer platform has an inner diameter that abuts an outer diameter, D, of the radially inner platform such that the radially outer platform circumscribes and abuts the radially inner platform; a roof structure radially outside the radially outer platform; a lift mechanism configured to lower the inner platform between the upper plane and a lower level; wherein the radially outer platform has an outer diameter that is at least 1.1 times the outer diameter, D, of the radially inner platform.

In this way, the primary landing pad (comprising both the radially inner and the radially outer platform) has a larger diameter than the inner platform, which can serve as a stand for the aircraft. Regulations may require, for a particular dimension of vertical take off and landing aircraft, that the primary landing pad (or final take off and landing area -FATO) has a larger diameter than the diameter of a stand for an aircraft of the same dimension. By arranging only the stand, and not the entire primary landing pad, to move vertically, the lift mechanism does not need to be able to lower and raise the entire primary landing pad. This reduces the need for an over-engineered lift mechanism.

The radially outer platform may have an outer diameter that is at least 1.2 times, and preferably at least 1.25 times the outer diameter, D, of the radially inner platform.

The aerodrome structure may further comprise a secondary landing pad in the upper plane and being offset from the primary landing pad, wherein the secondary landing pad is static.

In this way, capacity is increased and also since the secondary landing pad is static it may be able to accommodate aircraft whose dynamic load during take off and landing would exceed the capacity of the lift mechanism, thus preventing them from taking off and landing on the primary landing pad. -3 -

An upper limit of the roof extends to the upper level. By not extending beyond the upper level, a further hazard free region is provided radially outside the primary landing pad, in the region above the roof. This may further assist with meeting regulatory requirements.

The roof may comprise a pitched roof portion that extends from the upper level towards the lower level The aerodrome structure may comprise a plurality of outer zones radially outside the landing pad.

These zones may provide space for airport facilities.

The plurality of radially outer zones may comprise an aircraft bay offset from the landing pad, wherein the aircraft bay is located at the lower level.

In this way, an aircraft may be located in the aircraft bay for boarding, deboarding and/or for maintenance.

The plurality of radially outer zones may comprise a plurality of aircraft bays offset from the landing pad, to provide increased capacity.

The plurality of radially outer zones may comprise a passenger reception area at the lower level.

The passenger reception area may comprise one or more of a lounge and a check in area.

The aerodrome structure may further comprise a circulation route at the lower level beneath the radially outer platform extending between the passenger reception area and the aircraft stand.

In this way, a space provided beneath the radially outer platform may be deployed for circulation between different parts of the aerodrome structure.

The passenger reception area may be located beneath the roof. -4 -

The aerodrome structure may further comprise an aircraft transit area to facilitate movement of aircraft between the aircraft bay and the radially inner platform, in an event that the radially inner platform is at the lower level.

In this way, an aircraft may efficiently transfer between the radially inner platform (when in the lower position) and the aircraft bay.

The radially inner platform may be circular.

In this way, an aircraft can land at any rotational position on the radially inner platform and does not need to be oriented in any particular direction.

The radially outer platform may have a circular outer perimeter and a circular inner perimeter.

The aerodrome structure may comprise one or more of: a cargo transit apparatus; an electric charger for an aircraft; a battery exchange facility; a hydrogen refuelling facility; a cargo transit apparatus.

The aerodrome structure may further comprise an electro-voltaic panel on an exterior façade of the aerodrome structure.

Brief description of the drawings

Embodiments of the disclosure are now described with reference to the accompanying drawings, in which: Figure 1 shows a schematic perspective view of a first aerodrome structure, provided for context; -5 -Figure 2 shows a schematic perspective view of the first aerodrome structure showing interior elements; Figure 3 shows a schematic plan view of a vertical take off and landing aircraft together with a circle of minimum diameter capable of accommodating the VTOL; Figure 4 shows four areas related to a landing area for an aircraft; Figure 5 shows a schematic plan view of a second aerodrome structure in accordance with

the disclosure;

Figure 6 shows a schematic perspective view of a third aerodrome structure in accordance with the disclosure; Figure 7 shows a schematic plan view of an interior of the second aerodrome structure; Figure 8 shows schematic plan view of the interior of the second aerodrome structure, showing circulation routes; Figure 9 shows a plan view of the second aerodrome structure showing additional stand markings; and Figure 10 shows a cross sectional view of the second aerodrome structure showing transition of an aircraft from aircraft bay, to radially inner platform, to secondary landing pad.

Detailed description

Figure 1 shows a first aerodrome structure developed by the applicant to show context for

the embodiments of the disclosure described below.

The aerodrome structure 10 of Figure 1 has the form of a shallow, truncated cone. The aerodrome structure 10 includes a platform 12 arranged to be raised and lowered, between a lower level (which may be coincident with the prevailing ground level or may not) within -6 -the interior of the aerodrome structure 10 and an upper region or top of the aerodrome structure 10 (per the position of the platform 12 shown in Figure 1). With regard to departing aircraft, the platform 12 functions to move the aircraft from ground level to the top of the aerodrome structure 10 and provides a take-off pad for the aircraft. With regard to arriving aircraft, the platform 12 provides a landing pad and serves to move the aircraft from the top of the aerodrome structure 10 to ground level.

Referring to Figure 2, the platform 12 is one element of a lift structure 14 which forms a central, core assembly of the aerodrome structure 10. As will be explained herein, the lift structure 14 and its platform 12 enables the construction of the aerodrome structure 10 itself, as well as handling the movements of aircraft when the aerodrome structure 10 is in-service.

The lift structure 14 comprises an upstanding tubular frame including an upper ring 16 located directly above a lower or base ring 18 which lies on the ground. The upper ring 16 is supported over the base ring 18 by a plurality of substantially vertical lift structure columns 20 which are spaced apart from each other around the circumference of the upper and base rings 16, 18.

The platform 12 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 12 has a diameter or span which is slightly smaller than that of the base ring 18 and the upper ring 16, such that it effectively abuts the base ring 18 and the upper ring 16 without conflicting with the base ring 18 and the upper ring 16. In this example, the platform 12 comprises aluminium alloy. The platform 12 is movably connected to guide rails 22 (not shown in Figure 2) which extend between the base ring 18 and the upper ring 16 and which are spaced apart around the circumference thereof. In this example, the lift structure 14 comprises four guide rails 22. In this example, the guide rails 22 comprise steel.

Lift apparatus 24 (not visible in Figure 2) is provided beneath the platform 12 (i.e. between the platform 12 and the underlying ground) and is arranged to raise and lower the platform 12 between the base ring 18 and the upper ring 16. In this example, the lift apparatus 24 is supported on rest plates 26 (not visible in Figure 2) which are arranged within the circumference of the base ring 18. Further in this example, the rest plates 26 are -7 -themselves supported on or between ground-based base cross-beams 28 (not visible in Figure 2) which extend across the diameter of the base ring 18 and are connected thereto. In this example, the base cross-beams 28 comprise steel.

The spacing of the lift structure columns 20 and the guide rails 22 is configured such as to provide a side opening 30 of the lift structure 14, for loading an aircraft onto the platform 12 and unloading an aircraft from the platform 12 when the platform 12 is in a lowered position, i.e. such as to be located in the region of the base ring 18. When the platform 12 is in a raised position, i.e. such so as to be located in the region of the upper ring 16, the platform 12 provides a take-off and landing pad for an aircraft. Thus the platform 12 may also be referred to as a Final Approach and Take-Off or "FATO" platform. As such, the platform 12 is configured to meet relevant aviation regulations. In this regard, the platform 12 comprises appropriate markings, navigation lighting and equipment, and a surface material which is non-slip, durable, and corrosion resistant.

Still referring to Figure 2, the aerodrome structure 10 further comprises Y-shaped outriggers or stabilisation beams 32, which provide enhanced lateral stabilisation to the lift structure 14 and also form an additional structure of the aerodrome structure 10. In this example, the aerodrome structure 10 comprises six of the beams 32. In this example, the beams 32 comprise steel. As can be seen in the drawing, the Y-shaped stabilisation beams 32 slope downwardly and outwardly away from the lift structure 14. The two inner ends of each Y-shaped stabilisation beam 32 are fixedly connected to the upper ring 16, in particular at the same portions of the upper ring 16 to which a respective two of the lift structure columns are fixedly connected. The outer end of each Y-shaped stabilisation beam 32 is fixedly connected to a respective anchor member 34 which is in contact with the ground. An outer portion of the beam 32 which includes said outer end is cranked downwardly, i.e. the beam 32 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 32.

The aerodrome structure 10 further comprises a hanger structure 36 for accommodating aircraft entering and leaving the platform 12. The hanger structure 36 comprises a plurality of upstanding hanger structure columns 38 which are fixedly connected to a plurality of hanger structure roof members 40, ends of some of the hanger structure roof members 40 being fixedly connected to the upper ring 16 of the lift structure 14. An outer region of the -8 -hanger structure (i.e. to the right-hand side in the sense of Figure 2) includes an entrance/exit for aircraft to enter/leave the aerodrome structure 10.

Referring again to Figure 1, the aerodrome structure 10 further comprises an outer covering or cladding which is attached to the Y-shaped stabilisation beams 32 and defines a covered inner volume of the aerodrome structure 10. The cladding comprises a plurality of cladding segments 42, each of the segments spanning a space between an adjacent pair of the Y-shaped stabilisation beams. In this example, the cladding segments 42 comprise a fabric material, more particularly a PVC-coated polyester.

In the example aerodrome structure 10 of Figures 1 and 2, the lift structure is configured to raise and lower the entirety of the horizontal platform 12.

Regulations may require that various elements of VTOL aerodrome infrastructure have minimum dimensions relative to the maximum dimension of a VTOL aircraft with which they are to be used.

The smallest circular area capable of accommodating VTOL may have a diameter, Di. This diameter may be termed "the dimension" or "the critical dimension" of the aircraft. In Figure 3, a schematic plan view of a VTOL is shown together with a circle having the critical dimension Di of the VTOL.

A so-called "stand" for a VTOL, on which the VTOL may stand, for example for boarding, may be required to have a minimum diameter that is larger than the critical dimension of the aircraft. In Figure 4, the diameter of the stand D2 shown in the context of the critical dimension D. In addition, a flat safety area may be required to have a minimum diameter that is larger than the diameter of the stand. In Figure 4, the diameter of the safety area is D3.

Furthermore, there may a further safety area required outside the flat safety area which, though not necessarily flat, is required to be free of obstacles. In Figure 4, the diameter of the safety area is at. In the embodiments of the present disclosure, the wider (non-flat) safety area may extend at least in part above the conical outer portion of the truncated cone that forms the exterior of the aerodrome structure. -9 -

Some regulations may require as follows: that D2 is at least Di + 4 meters; that D3 is at least at least 1.5 x Di; and that D4 is the outer obstacle-free safety area is at least 2 x Di.

In the context of the aerodrome structure having a primary landing platform that is movable between an upper (landing and take off) level and a lower (boarding) level, it may be feasible with small aircraft to have the entire area having diameter D3 form part of the platform mounted to the lift structure. This is as shown in the example of Figures 1 and 2.

However, for larger aircraft, it may be preferable to avoid providing the infrastructure necessary to lift the entire area of the safety area.

Figure 5 shows a highly schematic view of a second aerodrome structure 100 in

accordance with the disclosure.

The aerodrome structure 100 comprises the primary landing pad 120 comprising the radially inner platform 130 and the radially outer platform 140. In addition, the aerodrome structure 100 comprises a secondary landing pad 150 which is static and at the same (upper) level as the primary landing pad 120. The aerodrome structure 100 further comprises a pair of aircraft bays 250 at the lower level. The aircraft bays 250 may have no roof.

Thus, in the aerodrome structure of Figure 5, for the primary landing pad only the stand (D2) and not the entirety of the flat safety area (D3) is movable up and down. The annular portion of the flat safety area that falls between D2 and D3 remains in situ at the upper level regardless of the vertical position of the inner platform. Furthermore, the portion of the obstacle free safety area that falls outside the flat safety area (that is, the annular portion between D3 and D4) extends beyond the flat area at the top of the aerodrome and over the conical outer portion of the truncated cone that forms part of the exterior of the aerodrome structure.

The stand is shown with diameter D2 and the lift structure assembly (not visible in Figure 5) is configured to lower and raise only the stand (diameter D2) whereas the annular safety area (outer diameter D3) is configured to remain in place at the upper level. In this way, -10 -when an aircraft lands or takes off, the stand is at the upper level and the entire platform (diameter D3) acts to provide a single planar area. However, once the aircraft has landed, only the stand (diameter 02) lowers to provide access by the aircraft to the lower level.

Beneath the secondary landing pad 150 there may be provided an aircraft hangar 160 (not shown in Figure 5). The hangar may provide facilities for maintenance and/or charging of the aircraft.

Figure 6 shows another embodiment of an aerodrome structure in which the lift mechanism moves only the inner portion of the primary landing platform representing the stand (D2) while an outer annular portion of the platform remains in situ (D3).

The Figure 6 embodiment comprises a secondary landing platform adjacent the primary landing platform at the upper level, and which does not have lift functionality. In this way, a VTOL may land on the second FATO and then move laterally to the central FATO to be moved via the lift mechanism to the lower level. Furthermore, since the secondary landing platform does not have lift functionality, it may be able to accommodate greater dynamic loads that may be associated with some VTOLs on take off and landing.

The Figure 6 embodiment further comprises a plurality of landing areas 160, 170, 180 at ground level outside a perimeter of the aerodrome structure 100.

Figure 7 shows a ground floor plan of an embodiment similar to that of Figure 6.

As shown, the aerodrome structure 100 may further comprise, at the lower level (ground floor), a passenger lounge 210, a security area 220, a command and control centre 230, a logistics space 240, the one or more open aircraft bays 250, and an aircraft hangar 260. One or more further FATOs 270 may be provided. A passenger pick up and drop off point 290 may also be provided.

Part of an annular area beneath the static platform portion (between 02 and 03, as shown in Figure 5) may be devoted to circulation space 280 between various parts of the aerodrome structure, including aircraft bays 250 and the passenger lounge 210.

Figure 8 shows various options for passenger flows between the various areas of the interior of the aerodrome structure, making use of the circulation space 280 accommodated in the annular area beneath the static portion of the platform.

Figure 9 shows how stands can be arranged as compound or hybrid stands. In particular, a large stand (such as that provided as part of the secondary landing pad 150) capable of accommodating a large VTOL may also provide a plurality of smaller stands 151, 152, 153, 154 capable of accommodating more than one smaller VTOL rather than only one large VTOL. This principle may be applied to any of the stands.

Figure 10 shows two cross sectional view of an aerodrome structure in accordance with the disclosure. In the top view, the radially inner platform is shown at the lower level illustrating how the VTOL can be moved laterally from the hanger or stand to the platform. In the right view, the radially inner platform is shown at the upper level from which either the VTOL may take off from the primary landing platform, or from which the VTOL may be moved laterally in order to take off from the secondary landing platform.

The lift mechanism may comprise any appropriate lifting apparatus such as but not limited to a scissor lift mechanism, a link lift mechanism, a column lift mechanism or an integrated lift mechanism.

The aerodrome structure 10 may comprise one or more electric chargers configured to charge a VTOL aircraft. Instead of or in addition to an electric charger, the aerodrome structure 100 may comprise a battery exchange facility and/or a hydrogen refuelling facility.

The aerodrome structure 100 may comprise one or more photovoltaic panels on an exterior face of the aerodrome structure. The aerodrome structure 100 may comprise cargo handling apparatus.

The aerodrome structure 100 may comprise one or more intermediate levels, between the upper level and the lower level. For example, an intermediate level may be for cargo. The lift apparatus may be configured to move the platform between the upper level, the lower level and the one or more intermediate levels.

While, in the illustrated embodiments, the landing pads are substantially circular, other shapes would also fall within the scope of the disclosure. For example, the landing platforms may have a substantially polygonal shape (e.g. a hexagon). Use of the words "diameter" and "radially" in this specification should not be interpreted as inferring that the shape of the platform is circular.

-12 -Similarly, while the illustrated embodiments have the radially inner platform concentric with the radially outer platform, this is not a requirement.

While, in the illustrated embodiments, two of the aircraft bays are shown without a roof, this is not a requirement and a roof may be provided as appropriate. If a roof is provided, it may be also that a perimeter wall with an opening or doorway is also provided.

While the term "landing pad" has been used throughout this specification, this should not be taken to mean that the landing pad is for landing only and not for take off. The term "landing and take off pad" would be equally appropriate.

The disclosure also envisages a further embodiment (not illustrated) in which the radially inner platform a plurality of segments or sectors (which could also be described as a split/segmented platform) wherein each can be raised or lowered independently of each other platform. In this way, more than one VTOL aircraft may be accommodated and raised/lowered independently.

Claims

-13 -CLAIMS: 1. An aerodrome structure comprising: a primary landing pad for a vertical take off and landing aircraft, the primary landing pad being located in an upper plane and comprising a radially inner platform and a radially outer platform, wherein the radially outer platform has an inner diameter that abuts an outer diameter, D, of the radially inner platform such that the radially outer platform circumscribes and abuts the radially inner platform; a roof structure radially outside the radially outer platform; a lift mechanism configured to lower the inner platform between the upper plane and a lower level; wherein the radially outer platform has an outer diameter that is at least 1.1 times the outer diameter of the radially inner platform.
2. The aerodrome structure of claim 1 wherein the radially outer platform has an outer diameter that is at least 1.2 times, and preferably at least 1.25 times the outer diameter of the radially inner platform.
3. The aerodrome structure of claim 1 or claim 2 further comprising a secondary landing pad in the upper plane and being offset from the primary landing pad, wherein the secondary landing pad is static.
4. The aerodrome structure of any preceding claim wherein an upper limit of the roof structure extends to the upper level.
5. The aerodrome structure of claim 4 wherein the roof comprises a pitched roof portion that extends from the upper level towards the lower level.
6. The aerodrome structure of any preceding claim further comprising a plurality of outer zones radially outside the landing pad.
7. The aerodrome structure of claim 6 wherein the plurality of radially outer zones comprises an aircraft bay offset from the landing pad, wherein the aircraft bay is located at the lower level.
-14 - 8. The aerodrome structure of claim 6 or claim 7 wherein the plurality of radially outer zones comprises a passenger reception area at the lower level.
9. The aerodrome structure of claim 8 when dependent upon claim 6 further comprising a circulation route at the lower level beneath the radially outer platform extending between the passenger reception area and the aircraft stand.
10. The aerodrome structure of claim 8 or claim 9 wherein the passenger reception area is located beneath the roof.
11. The aerodrome structure of claim 7 or any claim dependent upon claim further comprising an aircraft transit area to facilitate movement of aircraft between the aircraft bay and the radially inner platform, in an event that the radially inner platform is at the lower level.
12. The aerodrome structure of any preceding claim wherein the radially inner platform is circular.
13. The aerodrome structure of any preceding claim wherein the radially outer platform has a circular outer perimeter and a circular inner perimeter.
14. The aerodrome structure of claim 7 or any claim dependent upon claim 7, wherein any preceding claim wherein the aircraft bay has an arcuate perimeter such that, in use with an aircraft, both sides of the aircraft are directly accessible from the perimeter of the aircraft bay.
15. The aerodrome structure may further comprise a first lower level in which the platform cooperates with one or more of: a first level of the cargo transit apparatus; an electric charger for an aircraft; a battery exchange facility; a hydrogen refuelling facility; a cargo transit apparatus.
-15 - 16. The aerodrome structure of any preceding claim further comprising an electrovoltaic panel on an exterior façade of the aerodrome structure.
17. The aerodrome structure of any preceding claim wherein the primary landing pad and/or, where present, the secondary landing pad comprises stand markings for one larger VTOL and also stand markings for a plurality of smaller VTOLs.