LANDING ZONE ARRANGEMENT WITH A PLURALITY OF REMOVABLE SEGMENTS, AND METHOD FOR OPERATING A LANDING ZONE ARRANGEMENT OF THIS KIND

Abstract

The invention relates to a landing zone arrangement (1) for aircraft (19), in particular aircraft capable of vertical take-off, said arrangement comprising: a plurality of segments (3) which together form a landing zone in an operating state; a storage space (2) in which the plurality of segments (3) are at least partially stowable in a stored state; and a base (5) with a rotatable rotor element (4) in order to rotate the plurality of segments (3) for transfer into the operating state and/or into the stored state. In order to create a landing zone arrangement which allows a lighter technical design, the invention provides that at least individual segments of the plurality of segments (3) are secured removably to the rotor element (4), and a securing unit (8) of the landing zone arrangement (1) is designed to fasten the removable segments (3) to the rotor element (4) for transfer into the operating state and to release this fastening for transfer into the stored state. A lifting unit (9) is provided, which has one or more lifting elements (10) arranged in or on the storage space (2) in order to move the removable segments (3) in the direction of the rotor element (4) when transferring into the operating state.

Claims

1. A landing zone arrangement for aircraft capable of vertical takeoff, comprising: multiple segments , which together form a landing zone in an operating state; a storage space, in which the multiple segments are at least partially stowable in a stored state; a base with a rotatable rotor element to rotate the multiple segments for transferring into the operating state and/or into the stored state, wherein at least individual ones of the multiple segments are removably attached to the rotor element and a securing unit of the landing zone arrangement is formed to attach the removable segments to the rotor element in transferring into the operating state and to detach this attachment in transferring into the stored state, and a lifting unit, which comprises one or more lifting elements arranged in or at the storage space, to move the removable segments towards the rotor element in transferring into the operating state.

2. The landing zone arrangement according to claim 1, wherein the rotor element is immovable in relation to the storage space parallel to its rotational axis and in a vertical direction.

3. The landing zone arrangement according to claim 1, wherein , wherein the securing unit comprises at least one pocket for receiving the removable segments at the rotor element.

4. The landing zone arrangement according to claim 1, wherein the segments comprise respective locking means to detachably connect the multiple segments to each other in the operating state.

5. The landing zone arrangement according to claim 1, wherein only one of the multiple segments is fixedly arranged at the rotor element.

6. The landing zone arrangement according to claim 5, wherein the segment fixedly arranged at the rotor element is designed larger than the removable segments and is formed to cover the storage space, in a water-proof manner.

7. The landing zone arrangement according to claim 1, wherein support arms are arranged at the base to support the landing zone.

8. The landing zone arrangement according to claim 7, wherein the support arms comprise a vertically extendable support element at their respective end facing away from the base.

9. The landing zone arrangement according to claim 7, wherein at least one of the support arms forms a lateral surface of the storage space and/or seals it, in a water-proof manner, in the stored state.

10. The landing zone arrangement according to claim 1, wherein the multiple segments are at least substantially shaped according to a circular sector or a triangle.

11. A method for operating a landing zone arrangement with the following steps for transferring the landing zone arrangement from a stored state into an operating state: moving multiple removable segments stored in a storage space of the landing zone arrangement towards a rotor element of the landing zone arrangement by means of a lifting unit, which comprises one or more lifting elements arranged in or at the storage space; attaching the multiple removable segments stored in the storage space of the landing zone arrangement to the rotor element of the landing zone arrangement; and expanding the multiple segments by rotating the rotor element; and/or with the following steps for transferring the landing zone arrangement from the operating state into the stored state: collapsing the multiple segments by rotating the rotor element and detaching the attachment of the removable segments and subsequent displacement of the segments by means of the lifting unit into the storage space of the landing zone arrangement.

12. The method according to claim 11, wherein the attachment of the multiple segments is each individually effected one after the other and the rotor element is rotated by a predetermined angle before attaching a segment to be subsequently attached.

Description

BRIEF DESCRIPTION OF DRAWINGS

[0040] FIG. 1 depicts a landing zone arrangement for aircraft, in particular capable of vertical takeoff, with multiple segments, which are stowed in a storage space in a stored state, in a schematic sectional view.

[0041] FIG. 2 depicts the same landing zone arrangement in the stored state in a schematic top view.

[0042] FIG. 3 depicts multiple steps for transferring the landing zone arrangement into an operating state in a schematic perspective view.

[0043] FIG. 4 depicts again the landing zone arrangement in the stored state in a schematic top view.

[0044] FIG. 5 depicts the landing zone arrangement in a schematic perspective view on the bottom side thereof in a schematic perspective view.

[0045] FIG. 6 depicts a landing zone arrangement exemplarily installed on a ship in the stored state in a schematic perspective view.

[0046] FIG. 7 depicts the landing zone arrangement exemplarily installed on a ship in the operating state in a schematic perspective view.

DETAILED DESCRIPTION

[0047] FIGS. 1 and 2 show a landing zone arrangement 1 for providing a landing zone 11 for aircraft 19, in particular aircraft 19 capable of vertical takeoff. The landing zone 11 is in particular an at least substantially plane surface, which allows landing of the stored state. In particular, the landing zone arrangement 1 and the landing zone 11, respectively, are formed with respect to size and/or load-bearing capacity to be able to support a helicopter. In other words, the landing zone arrangement 1 and the landing zone 11, respectively, are formed to allow landing of a helicopter on the landing zone 11.

[0048] In order to allow a space-saving arrangement and installation, respectively, of the landing zone arrangement 1 at an installation site, for example a ship, a floating platform (for example an oil rig), a building or the like, it is provided that the landing zone arrangement 1 has an operating state and a stored state. Therein, a space requirement of the landing zone arrangement 1 in the stored state is considerably reduced compared to the operating state. Hereto, the landing zone arrangement 1 and the landing zone 11, respectively, are divided into multiple segments 3. In other words, the segments 3 form the landing zone 11 in the operating state of the landing zone arrangement 1. In still other words, the individual segments 3 are composed to an at least substantially plane surface in the operating state, wherein this surface forms the landing zone 11. The landing zone 11 is for example apparent based on FIGS. 5 and 7.

[0049] Now again with reference to FIGS. 1 and 2, the segments 3 are at least partially stowable in a storage space 2 of the landing zone arrangement 1 in the stored state. In particular, the multiple segments 3 are stowed or arranged in the storage space 2 as intended in the stored state. This is in particular apparent based on FIG. 1. The storage space 2 is laterally bounded by respective lateral surfaces 6.

[0050] These multiple segments 3 can be formed equally to each other or differently from each other. In other embodiments, it can for example be provided that all of the multiple segments 3 are identical. Presently, it is provided that one of the multiple segments 3 differs from the remaining, equal segments 3. This is further explained in the following.

[0051] A rotor element 4 is arranged at a base 5 of the landing zone arrangement 1. The rotor element 4 is rotatably arranged at the base 5. Hereto, the rotor element 4 can comprise an electric motor, hydraulic drive or any other drive. Therein, the rotor element 4 presently has a vertically oriented rotational axis. In other words, the rotor element 4 can rotate within a horizontal plane. In particular, the rotor element 4 can rotate within the plane, which is spanned by the landing zone 11 in the operating state of the landing zone arrangement 1. The rotor element 4 is formed to transfer the multiple segments 3 into the operating state and/or into the stored state. Hereto, the rotor element 4 moves the corresponding segments 3 with its rotational movement.

[0052] The landing zone arrangement 1 comprises a securing unit 8, which is formed to attach the segments 3 to the rotor element 4 and/or to detach the attachment. In particular, the securing unit 8 is formed to attach the segments 3 to the rotor element 4 in transferring into the operating state and to detach this attachment in transferring into the stored state. In other words, the at least individual ones of the multiple segments 3 are removably attached to the rotor element 4. In other words, the at least individual ones of the multiple segments 3 are reversibly attachable to the rotor element 4. These segments 3 are also referred to as removable segments 3. In other embodiments, it can be provided that all of the segments 3 are removable. In the present embodiment, it is provided that one of the multiple segments 3 is fixedly arranged at the rotor element 4 and the remaining segments 3 are removably designed. Therein, the removable segments 3 are presently preferably each designed identically to each other. In this manner, they are particularly easily exchangeable and/or replaceable. The single segment from the multiple segments 3, which differs from the remaining segments 3, is in particular the segment fixedly arranged at the rotor element 4 (see below the cover segment 16). This differing segment 3 can in particular be designed larger than the removable segments. Preferably, the segment 3 fixedly arranged at the rotor element 4 is formed to cover the storage space 2.

[0053] FIG. 3 now shows the transfer of the landing zone arrangement 1 from the stored state into the operating state in sections based on multiple steps S1 to S4. In step S1, a segment 22 is removably attached to the rotor element 4. In the present example, this is in particular effected via a corresponding pocket or recess, which the rotor element 4 comprises for the removable segments 3. Thus, this pocket or recess is a part of the securing unit 8 in the present example. Corresponding to a hook-in movement 21, which is in particular effected within the plane spanned by the landing zone 11, the segment 22 is hooked or introduced into this pocket or recess. Subsequently, further fixing of the segment 22 can be effected by corresponding securing elements of the securing unit 8. These securing elements can be arranged at the rotor element 4 and/or the respective segment 3 and 22, respectively.

[0054] After attaching the segment 22 to the rotor element 4 in step S1, the rotor element 4 is rotated by a predetermined angle in the following step S2. This is indicated by an arrow 20 in FIG. 3. In addition, the segment 22 is locked to the adjacent segment 3 in step S2. Hereto, the segments 3 comprise respective locking means 12. Thus, a particularly stable attachment of each of the segments 3 or concretely of the segment 22 in the present example is ensured. The predetermined angle, by which the rotation 20 is effected, in particular corresponds to an angular range covered by the segment 22 and by the respective segments 3, respectively. Sense and purpose of the rotation 20 is in that a following segment 23 can subsequently be attached to the rotor element 4. This is effected in the following step S3. By a lifting unit 9, which includes four lifting elements 10 in the present example, the following segment 23 is lifted out of the storage space e.g. along a vertical direction of movement 18 (see also FIGS. 1 and 2). The lifting unit 9 and the lifting elements 10 thereof, respectively, can for example comprise an electric drive, in particular electric motor, a hydraulic drive or any other drive or actuator. The four lifting elements 10 are formed to commonly lift the segments 3 stored in the storage space in synchronized manner. Subsequently, the following segment 23 can also be inserted into the rotor element 4 with the hook-in movement 21 in horizontal or radial direction of movement 17 (see FIGS. 1 and 2). This movement too in horizontal direction of movement 17 can be effected by means of the lifting unit 9. The attachment can be effected analogously to the attachment of the segment 22. Alternatively, the segment 23 can be attached via the lifting elements 10 and be retained in the position.

[0055] In a subsequent step S4, the rotation 20 by the predetermined angle is again effected. Analogously to the step S2, the locking of the locking means 12 is effected in step S4. The following segment 23 is attached or locked to the segment 22 by means of the locking means 12.

[0056] By rotating 20 or expanding by means of the rotor element 4, the segments 3 stowed or arranged within the storage space 2 in stacked manner can be arranged next to each other at the rotor element 4 in transferring into the operating state. Therein, the rotation 20 in particular pursues the purpose to open an opening of the storage space 2 to the top for removing the respectively following segment 3. In this manner, lifting out and arranging a following segment 3 are allowed.

[0057] For controlling these method steps, a control unit 15 can be provided at the landing zone arrangement 1. For example, the control unit 15 can be formed to control the attachment and the expansion and/or collapse as well as detachment of the attachment. Accordingly, the control unit 15 can be formed to command the attachment of the multiple segments 3 each effected one after the other. Alternatively or additionally, the control unit can command that the rotor element is rotated by the predetermined angle before attaching the segment to be subsequently attached. In other words, the control unit 15 can be formed such that it controls the alternating rotation and expansion and attachment, respectively, of the segments 3, in particular in the sense mentioned above. In analogous manner, the control unit 15 can be formed to control the collapse as well as the detachment of the attachment in alternating or iterating manner.

[0058] The control unit 15 can be mechanically or preferably electronically designed. For example, the control unit 15 can be designed as a microprocessor, programmable logic gate (FPGA) or as a digital signal processor. Accordingly, the landing zone arrangement 1 can include an analog or digital control unit 15, which is formed to perform or control the method according to the invention. In case of a digital control unit 15, it can comprise a memory, on which an executable program code is stored, which entails performing the corresponding method steps upon execution of the program code in the control unit 15.

[0059] FIG. 4 additionally shows multiple support arms 7 in the stored state. These support arms 7 are arranged at the base 5 or the rotor element 4 with a first end. The support arms 7 comprise a respective vertically extendable support element 14 at the opposing end. In particular, the support arms 7 are pivotably arranged at the base 5. In the stored state, the support arms 7 (just as the segments 3) can be stowed within the storage space 2.

[0060] FIG. 5 shows the landing zone arrangement 1 in the operating state. On the top side of the landing zone arrangement 1, there is the landing zone 11. In FIG. 5, it is apparent by the upwards directed perspective how the landing zone 11 and the segments 3, respectively, are supported from below by the support arms 7. In other words, the support arms 7 are formed to support the landing zone 11 and individual segments 3, respectively, from below. Hereto, the support arms 7 can be pivoted such that they are transferred into a respective operating position. For example, the support arms 7 take their respective operating position in the operating state, in which the respective support arms 7 are spread from the base 5 and the rotor element 4, respectively. Therein, the support arms 7 can extend in their main extension direction in radial direction related to the rotor element 4 and the base 5, respectively. In addition to pivoting the support arms 7, it can be provided that they vary their respective length. For example, the support arms 7 can be designed as telescopic arms. In this case, the support arms 7 can increase their length in the operating state with respect to the stored state. In this manner, an even more efficient support of the landing zone 11 in a position located radially farther outwards is possible. For example, the respective extendable support element 14 is extended at the respective end facing away from the base 5 in the operating state such that a predetermined pressure is generated on the bottom side of the landing zone 11 and on the bottom side of one or more segments 3, respectively. This pressure is directed upwards and generates the supporting force.

[0061] Finally, FIGS. 6 and 7 show an exemplary arrangement of the landing zone arrangement 1 with a ship as an exemplary installation site. Therein, FIG. 6 shows the landing zone arrangement 1 in the stored state and FIG. 7 shows the landing zone arrangement 1 in the operating state. As FIG. 7 further shows, a surface of the rotor element 4 is also part of the landing zone. In other words, the surface of the rotor element 4 can also contribute to the landing zone 11 in addition to the segments 3.

[0062] Based on FIG. 6, it is well apparent that one of the segments 3 is larger than the remaining ones of the segments 3. It is the segment differing from the remaining segments 3, which was already described above. In the present example, it is designed as a cover segment 16. The cover segment 16 is formed to seal the storage space 2 towards the top, in particular in water-proof manner, in the stored state. Hereto, the cover segment 16 rests on the lateral surfaces 6 in the present example, which laterally bound the storage space 2. Hereby, a particularly secure storage of the segments 3 arranged within the storage space 2 is ensured. By the larger dimensions of the cover segment 16, it can be that it protrudes beyond one or more of the segments 3 adjoining in the operating state. In this case, a step can arise here, but which is negligible in practice.

List of Reference Characters

[0063] 1 landing zone arrangement

[0064] 2 storage space

[0065] 3 segment

[0066] 4 rotor element

[0067] 5 base

[0068] 6 lateral surface

[0069] 7 support arm

[0070] 8 securing unit

[0071] 9 lifting unit

[0072] 10 lifting element

[0073] 11 landing zone

[0074] 12 locking means

[0075] 14 support element

[0076] 15 control unit

[0077] 16 cover segment

[0078] 17 horizontal direction of movement

[0079] 18 vertical direction of movement

[0080] 19 aircraft

[0081] 20 rotation

[0082] 21 hook-in movement

[0083] 22 segment

[0084] 23 segment

[0085] S1-S4 method steps