Surface assembly

Abstract

A surface assembly and related method of constructing a surface assembly are used as part of a landing platform. The surface assembly includes a modular structure having an upper surface with a plurality of discrete elements. Each discrete element has a body of metal material defining at least one anchor aperture for receiving a hook or like anchor device for anchoring a helicopter or other powered light aircraft to the surface assembly. The surface assembly is configured to define an array of the plurality of discrete elements in which at least two of the anchor apertures are provided side-by-side. The body of each discrete element has a periphery, and each anchor aperture of the array is inboard of the periphery of a respective body of a discrete element in the array.

Claims

1. A helicopter anchoring grid, the anchoring grid having an upper surface defined by a modular structure formed from a plurality of discrete steel elements of the same shape and configuration, wherein each discrete steel element has a periphery which is tessellated with the periphery of one or more other discrete steel elements of said plurality of discrete steel elements, wherein no substantial gaps or overlapping regions are formed between the tessellated discrete steel elements in the modular structure, wherein each discrete steel element has at least one anchor aperture inboard of the periphery for receiving a hook or anchor device for anchoring a helicopter to the grid; wherein the anchoring grid comprises a plurality of steel link members and a plurality of steel stanchions; wherein each one of the plurality of steel link members is provided below the upper surface and collocates at least two adjacent discrete steel elements of said plurality of discrete steel elements in tessellation with one another; wherein each steel stanchion engages an underside of a respective one of the plurality of steel link members and spaces the respective one of the plurality of steel link members and at least two adjacent discrete steel elements above a ground surface, and wherein each steel stanchion locks the respective one of the plurality of steel link members and at least two adjacent discrete steel elements together.

2. The helicopter anchoring grid according to claim 1, wherein, a sum of the areas defined by the at least one anchor aperture of the plurality of discrete steel elements is in a range of 30% to 70% of a total area of the helicopter anchoring grid in plan view.

3. The helicopter anchoring grid according to claim 1, wherein the periphery of each discrete steel element is defined by a polygon in plan view, wherein said polygon is a regular 3, 4 or 6 sided polygon, or wherein said polygon is a regular hexagon.

4. The helicopter anchoring grid according to claim 1, wherein the periphery of each of the plurality of discrete steel elements comprises a plurality of facets, and wherein each facet is arranged against a complementary facet of at least one other discrete steel element of the plurality of discrete steel elements.

5. The helicopter anchoring grid according to claim 1, wherein each discrete steel element comprises an inner surface defined by the anchor aperture, wherein a significant proportion of the inner surface has a curved cross section, wherein the curved cross section extends from a first diameter at an upper surface of the discrete element to a second diameter at a depth within the discrete element, and wherein the first diameter is larger than the second diameter.

6. The helicopter anchoring grid according to claim 1, wherein the periphery of each of the plurality of discrete steel elements comprises a peripheral groove or recess extending around said periphery, wherein the peripheral groove or recess is configured for receiving a portion of one or more of said plurality of steel link members, wherein each of the plurality of steel link members and the peripheral groove or recess are configured to have complementary size and shape to accommodate one of the plurality of steel link members between two or more of the plurality of discrete steel elements during tessellation of said two or more discrete steel elements, without interfering with the capacity for said two or more discrete steel elements to be capable of tessellation.

7. The helicopter anchoring grid according to claim 6, wherein each of the plurality of discrete steel elements comprises a lower surface and a distributed plurality of access recesses below the peripheral groove or recess, each access recess configured for receiving an end of one of the plurality of steel stanchions, and wherein said access recesses extend from the lower surface to the peripheral groove or recess.

8. The helicopter anchoring grid according to claim 7, wherein each of the plurality of steel stanchions comprises a shoulder and each of the plurality of discrete steel elements comprises a plurality of locking grooves in the lower surface, wherein each locking groove is configured to receive a portion of the shoulder of a respective one of the plurality of steel stanchions, and wherein said locking grooves extend concentrically around the plurality of access recesses.

9. The helicopter anchoring grid according to claim 7, wherein the plurality of steel stanchions comprises an end and a shoulder, wherein the lower surface of each of the plurality of discrete steel elements comprises a portion surrounding said access recesses, wherein the end of each of the plurality of steel stanchions extends through said access recesses in the discrete steel elements to engage a respective one of the plurality of steel link members, wherein the shoulder of each of the plurality of steel stanchions engages the portion of the lower surface surrounding said access recesses, and wherein the end of each of the plurality of steel stanchions comprises a thread and each of the plurality of steel link members comprises a complementary thread within the steel link member, wherein each of the plurality of steel stanchions engages the respective one of the steel link members via relative rotation of the threads.

10. The helicopter anchoring grid according to claim 1, wherein each discrete element defines a single anchor aperture.

11. A landing zone for a helicopter or other powered light aircraft, said landing zone incorporating the helicopter anchoring grid in accordance with claim 1.

12. The landing zone according to claim 11, wherein the helicopter anchoring grid defines a whole or a significant proportion of a surface area of said landing zone.

13. The landing zone according to claim 11, wherein the helicopter anchoring grid forms part of a periphery or one or more dedicated areas within an overall surface area of said landing zone.

14. A method of constructing a helicopter anchoring grid, comprising: providing a plurality of discrete steel elements of a same shape and configuration, each discrete steel element having a periphery and at least one anchor aperture inboard of the periphery; and tessellating the periphery of each discrete steel element with the periphery of one or more other discrete steel elements of said plurality of discrete elements to form a modular structure which defines an upper surface in which no substantial gaps or overlapping regions are formed between the tessellated discrete steel elements in the modular structure; the method including a step of providing a plurality of steel link members, wherein each one of the plurality of steel link members is provided below the upper surface and collocates at least two adjacent discrete steel elements of said plurality of discrete steel elements in tessellation with one another; the method including a step of providing a plurality of steel stanchions, wherein each steel stanchion engages an underside of a respective one of the plurality of steel link members and spaces the respective one of the plurality of steel link members and at least two adjacent discrete steel elements above a ground surface, and wherein each steel stanchion locks the respective one of the plurality of steel link members and at least two adjacent discrete steel elements together.

15. A helicopter anchoring grid, the anchoring grid having an upper surface defined by a modular structure formed from a plurality of discrete steel elements of the same shape and configuration, wherein each discrete steel element has a periphery which is tessellated with the periphery of one or more other discrete steel elements of said plurality of discrete steel elements, wherein no substantial gaps or overlapping regions are formed between the tessellated discrete steel elements in the modular structure, wherein each discrete steel element has at least one anchor aperture inboard of the periphery for receiving a hook or anchor device for anchoring a helicopter to the grid; wherein the anchoring grid comprises a plurality of steel link members and a plurality of steel stanchions; wherein each one of the plurality of steel link members is provided below the upper surface and collocates at least two adjacent discrete steel elements of said plurality of discrete steel elements in tessellation with one another; wherein each steel stanchion engages an underside of a respective one of the plurality of steel link members and spaces the respective one of the plurality of steel link members and at least two adjacent discrete steel elements above a ground surface, and wherein each steel stanchion locks the respective one of the plurality of steel link members and at least two adjacent discrete steel elements together; wherein each of the plurality of discrete steel elements comprises a body of stainless and/or maraging steel; wherein the at least one anchor aperture of each discrete steel element comprises a diameter in a range of 2 cm to 10 cm; wherein a sum of areas defined by the at least one anchor aperture of the plurality of discrete steel elements is in a range of 30% to 70% of a total area of the helicopter anchoring grid in plan view; and wherein each anchor aperture has a centre and wherein a distance from the centre to a centre of each adjacent anchor aperture of the anchoring grid is in a range of 2.6 cm to 13.0 cm.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) Embodiments are now briefly described, by way of example only, with reference to the accompanying drawings, in which:

(2) FIG. 1 is a plan view of a surface assembly according to an embodiment;

(3) FIG. 2 is a side view of the surface assembly of FIG. 1;

(4) FIGS. 3 and 4 are exploded and assembled isometric views respectively of two discrete elements, one link member and one stanchion of the surface assembly depicted in FIGS. 1 and 2;

(5) FIGS. 5a to 5d are plan, side and isometric views of a discrete element of the surface assembly depicted in FIGS. 1 and 2;

(6) FIGS. 6a to 6d are plan and side views of a link member of the surface assembly depicted in FIGS. 1 and 2;

(7) FIGS. 7a to 7c are plan and side views of a locking member of the surface assembly depicted in FIGS. 1 and 2.

DETAILED DESCRIPTION

(8) Embodiments are now described in detail, by way of example only, with reference to the accompanying drawings.

(9) With reference to FIGS. 1 and 2, a surface assembly for use as part of a landing platform is depicted at 1. The surface assembly 1 takes the form of a modular structure having an upper surface 2, including a plurality of discrete elements 3, each discrete element 3 defining at least one anchor aperture 4 for receiving a hook or like anchor device (not depicted). The surface assembly 1 is configured to define an array 5 of said discrete elements 3, in which at least two anchor apertures 4 are provided side-by-side. Each of the anchor apertures 4 of the surface assembly 1 is defined by the body of a single discrete element 3.

(10) Such a surface assembly 1 may be used for tethering a helicopter or other powered light aircraft, via engagement of a hook or like anchor device on said helicopter or other powered light aircraft with at least one anchor aperture 4 in the surface assembly 1. A surface assembly 1, having at least two anchor apertures 4 provides more than one option for receiving the hook or like anchor device, which reduces the required precision of the positional control of the helicopter or other powered light aircraft.

(11) In the illustrated embodiment, the sum of the areas defined by the anchor apertures 4 is approximately 50% of the total area of the surface assembly 1 in plan view. In alternative embodiments, the sum of the areas defined by the anchor apertures 4 could be anything in the range of 30% to 70% of the total area of the surface assembly 1.

(12) Having the sum of the areas defined by the anchor apertures 4 in this range provides a good trade-off between providing sufficient area for receiving a hook or like anchor and providing sufficient strength in the surface assembly 1.

(13) With reference to FIGS. 3, 4 and 5a to 5d, each discrete element 3 in the surface assembly 1 includes a periphery 6 configured for tessellation with the periphery 6 of at least one other discrete element 3 of the same shape and configuration, so that no spaces are formed between the bodies of adjacent discrete elements 3 in the array 5. This ensures that the discrete elements 3 fit together readily to form the surface assembly 1. The anchor aperture 4 of each discrete element 3 is located inboard of said periphery 6.

(14) The periphery 6 of each discrete element 3 is defined by a polygon in plan view. In some embodiments, said polygon is a regular 3, 4 or 6 sided polygon. In the embodiment of FIGS. 1 to 5d, said polygon is a regular hexagon. In this way, the discrete elements 3 can be manufactured as regular shapes.

(15) The periphery 6 of each discrete element 3 includes a plurality of facets 6a to 6f. Each facet is configured to be arranged against a complementary facet 6a to 6f of at least one other discrete element 3 of the same shape and configuration.

(16) With reference to FIGS. 5c to 5d, each discrete element includes an inner surface 7. Said anchor aperture 4 defines the inner surface 7. A significant proportion of the inner surface 7 has a curved cross section. The curved cross section extends from a first diameter D1 at an upper surface 8 of the discrete element 3 to a second diameter D2 at a depth within the discrete element 3. The first diameter D1 is larger than the second diameter D2. In this way, the curved portion of the inner surface 7 acts like a funnel to guide a hook or like anchor device through the anchor aperture 4.

(17) With reference to FIGS. 3, 4 and 6a to 6d, the surface assembly 1 includes a link member 9 provided to collocate two or more adjacent discrete elements 3 in close proximity.

(18) Each discrete element 3 includes a periphery 6 and a peripheral groove 10 extending around said periphery 6. The peripheral groove 10 is configured for receiving a portion of the link member 9. The link member 9 and the peripheral groove 10 are configured to have complementary size and shape, such that the link member 9 can be disposed between two or more discrete elements 3 of the same size and shape without preventing tessellation of the peripheries 6 above the peripheral grooves 10.

(19) In this way, the link member 9 can be disposed between two adjacent discrete members 3, whilst ensuring no substantial gaps in the upper surface 2 of the surface assembly 1.

(20) With reference to FIGS. 3, 4 and 7a to 7c, the surface assembly 1 includes a locking member 11 provided for locking together the link member 9 and adjacent collocated elements 3 in the array 5.

(21) In this way, the modular components are secured together to create a rigid and fixed surface assembly 1.

(22) Each discrete element 3 includes a lower surface 13 and a distributed plurality of access recesses 12 below the peripheral groove 10. Each access recess 12 is configured for receiving an end of the locking member 11. The access recesses 12 extend from the lower surface 13 to the peripheral groove 10.

(23) In this way, the upper surface 8 of the discrete elements 3 can be tessellated, whilst providing a gap in the lower surface 13 for receiving the locking member 11. This allows the locking member 11 to secure the discrete elements 3 and link member 9 together to form a sturdy and fixed assembly.

(24) The locking member 11 includes an end 16 and a shoulder 15. The lower surface 13 of the discrete elements 3 includes a portion surrounding said access recesses 12. The end 16 of the locking member 11 extends through said access recesses 12 in the discrete elements 3 to engage the link member 9.

(25) In this way, both the link member 9 and adjacent discrete elements 3 are locked together with a single locking member 11.

(26) The end 16 of the locking member 11 includes a thread 17 and the link member 9 includes a complementary thread within the link member 9. The locking member 11 engages the link member 9 via relative rotation of the threads.

(27) With reference to FIG. 2, the array 5 is spaced from a floor surface 19 in use, via a plurality of stanchions 20.

(28) This provides a void 21 into which a hook or like anchor can extend.

(29) With reference to FIGS. 3, 4 and 7a to 7c, the locking member 11 includes a stanchion 20, for spacing the array 5 from a floor surface 19 in use.

(30) In this way, the stanchion/locking member 11 provides the dual-function of securing the discrete elements 3 and link member 9 together, whilst separating the array 5 from the floor surface 19 to create a void 21 into which a hook or like anchor can extend.

(31) With reference to FIG. 1, the surface assembly 1 defines a landing grid in plan view. The array 5 includes a tessellation of said discrete elements 3.

(32) With reference to FIGS. 5a to 5d, the diameter D2 of each anchor aperture 4 is in the range of 1 cm and 25 cm. In exemplary embodiments, the diameter D2 of each anchor aperture 4 is around 5.1 cm. Each anchor aperture 4 has a centre C. The distance X from the centre C to a centre C of each adjacent anchor aperture 4 is in the range of 1.3 cm and 32.5 cm. In exemplary embodiments, the distance X from the centre C to a centre C of each adjacent anchor aperture 4 is around 6.6 cm.

(33) In this way, the anchor apertures 4 are suitably sized for receiving a hook or like anchor device of known construction and of conforming to landing grid standards.

(34) Each discrete element 3, link member 9 and locking member 11 is of stainless steel. Further, each discrete element 3, link member 9 and locking member 11 is of precipitation hardened stainless steel. Further, each discrete element 3, link member 9 and locking member 11 is of precipitation hardened stainless steel with high tensile strength.

(35) In some embodiments, each discrete element 3, link member 9 and locking member 11 may be of maraging steels.

(36) In alternative embodiments, each discrete element 3, link member 9 and locking member 11 may be of a different metal material.

(37) Such materials ensure that the surface assembly 1 is strong enough for use in securing a helicopter or other powered light aircraft, and for satisfying any relevant standards or safety certification requirements.

(38) Each discrete element 3, link member 9 and locking member 11 is a machined, forged or cast component. This allows an appropriate manufacturing technique to be chosen depending on the type of raw materials used. For example, machining from offcut blocks of metal, casting from molten scrap metal etc.

(39) Each discrete element 3 defines a single anchor aperture 4. This is a simple configuration which is easier to manufacture via a machining, forging or casting process than a multi-aperture component. Moreover, this provides greater flexibility over the size and shape of landing grids that can be assembled.

(40) In the exemplary embodiment depicted in the figures, the locking member 11 includes a shoulder 15 and each discrete element includes a plurality of locking grooves 14 in the lower surface 13. Each locking groove 14 is configured to receive a portion of the shoulder 15 of the locking member 11. The locking grooves 14 extend concentrically around the plurality of access recesses 12.

(41) In this way, the locking grooves 14 provide a better surface for engagement with the complementary shoulder 15 of the locking member 11. In other words, the shoulder 15 of the locking member 11 acts as a key to be located within said locking grooves 14 to fix the locking member 11 to the lower surface 13 of the discrete elements 3.

(42) In other embodiments, the lower surface 13 may comprise a flat face, with no locking grooves 14 around the plurality of access recesses 12.

(43) In the exemplary embodiment depicted in the figures, a shoulder 15 of the locking member 11 is disposed in the locking grooves 14 on the lower surface 13 of the discrete elements 3 surrounding said access recesses 12. In other embodiments, the shoulder 15 of the locking member 11 is configured to abut against a flat lower surface 13 of the discrete elements 3.

(44) With reference to FIGS. 5a to 5d, a discrete element 3 for use in a surface assembly 1 is depicted. The discrete element 3, includes at least one anchor aperture 4 for receiving a hook or like anchor device.

(45) The discrete element 3 also includes a periphery 6, which is configured for tessellation with a periphery 6 of at least one other discrete element 3 of the same shape and configuration.

(46) A peripheral groove 10 extends around the periphery 6. The peripheral groove 10 is configured for receiving a portion of a link member 9.

(47) The discrete element 3 includes a plurality of access recesses 12 below the peripheral groove, for receiving an end 16 of a locking member 11. The access recesses 12 extend from a lower surface 13 of the discrete element 3 to the peripheral groove 10.

(48) Multiple discrete elements 3 of this type can be tessellated to form an array 5. In other words, the discrete elements 3 fit together with no substantial gaps or overlapping between them. Moreover, peripheral grooves 10 and access recesses 12 in the periphery 6 allow link members 9 and locking members 11 of complementary configuration to be used to secure the surface array 5.

(49) A method of constructing a surface assembly 1 includes: providing a plurality of discrete elements 3 as described above; providing a link member 9 of complementary shape and configuration to the peripheral groove 10 in the periphery 6 of each discrete element 3; disposing the link member 9 between adjacent discrete elements 3 to collocate the discrete elements 3; tessellating said plurality of discrete elements 3 to form an array 5; providing a locking member 11, of complementary shape and configuration to the access recesses 12 in the peripheries 6; engaging the locking member 11 with said discrete elements 3 and link member 9 to lock them together. Advantageously, the array may be separated from a floor surface 19 via a plurality of stanchions 20 (which may also function as a locking member 11).

(50) This method provides flexibility to construct landing grids of any size or shape via changing the number or distribution of discrete elements 3, link members 9 and locking members 11. This method of modular construction also allows for simple reconfiguration of the surface assembly 1, replacement of damaged elements and management of obsolescence via upgrading elements. In addition, small modular components can be more easily manufactured, stored and distributed than large surface assemblies.

(51) In exemplary embodiments, the surface assembly defines the whole or a significant proportion of the surface area of a landing zone for a helicopter or other powered light aircraft. In other embodiments, the surface assembly forms part of the periphery or dedicated area within the overall surface area of a landing zone for a helicopter or other powered light aircraft, e.g. so as to define discrete anchor regions within the overall surface area of the landing zone. In such embodiments, the remainder of the landing zone may be constructed from alternative means or materials, e.g. from conventional metal or pavement materials or the like.