Aircraft take-off and landing platform

Abstract

The utility model relates to the technical field of aircraft take-off and landing platforms, aims to solve the problem of how to improve the stability of an aircraft during landing, and provides an aircraft take-off and landing platform, the aircraft take-off and landing platform comprises a carrying platform, the carrying platform comprises a net-shaped structure, the net-shaped structure defines a plurality of through holes, the through holes penetrate through the carrying platform in the first direction, and the through holes are provided with hole walls; the hole wall comprises an inlet part, a middle part and an outlet part which are sequentially arranged in the first direction; in the first direction, the middle part protrudes towards the inner side of the through hole relative to the inlet part and the outlet part; the inlet part, the middle part and the outlet part are in smooth transition in the first direction. One end of the through hole close to the inlet part is provided with an air inlet, and one end of the through hole close to the outlet part is provided with an air outlet. The air outlet structure has the beneficial effects that the vortex region is formed at the outlet part, and high-pressure airflow generated by the rotor wing of the aircraft is guided to enter the vortex region, so that the impact strength and the impact frequency of the airflow on the ground and the surrounding environment are reduced, and the safety and the stability of the aircraft during landing are improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aircraft landing platform, in particular to a vertical take-off and landing aircraft landing platform. BACKGROUND

[0002] In order to provide support when the aircraft lands, a kind of aircraft landing platform is provided in the related art, for roof or other specific aircraft landing area.

[0003] However, due to the airflow generated when the aircraft lands, such as when a helicopter lands, the airflow generated by the rotor will reflect back when approaching the ground, forming a ground effect reaction force, causing instability when the aircraft lands. CONTENT OF THE INVENTION

[0004] The present application provides an aircraft landing platform to solve the problem of how to improve the stability of the aircraft landing.

[0005] The embodiment of the present application provides an aircraft landing platform, comprising a carrier, the carrier comprises a net structure, the net structure defines a plurality of through holes, the through holes pass through the carrier along a first direction, the through holes have a hole wall, the hole wall comprises an inlet portion, an intermediate portion and an outlet portion arranged in sequence along the first direction;And along the first direction, the intermediate portion is protruded to the inner side of the through hole relative to the inlet portion and the outlet portion;Along the first direction, the inlet portion, the intermediate portion and the outlet portion are smoothly transitioned;The end of the through hole close to the inlet portion has an air inlet, and the end of the through hole close to the outlet portion has an air outlet.

[0006] The aircraft landing platform described above, by setting the intermediate portion to protrude relative to the inlet portion and the outlet portion respectively, the airflow flowing from the air inlet to the air outlet is hindered when flowing through the intermediate portion, which is conducive to forming a vortex zone at the outlet portion, and the high-pressure airflow generated by the rotor of the aircraft is guided into the vortex zone, thereby reducing the impact intensity and impact frequency of the airflow on the ground and the surrounding environment, and further improving the safety and stability of the aircraft landing.

[0007] In one of the embodiments, along the first direction, the curvature of the hole wall is greater than or equal to 30 degrees and less than or equal to 60 degrees.

[0008] In one of the embodiments, the ratio of the hole diameter of the narrowest part of the intermediate portion to the radial dimension of the air inlet is greater than or equal to 1:3 and less than or equal to 1:2;And / or, the ratio of the hole diameter of the narrowest part of the intermediate portion to the radial dimension of the air outlet is greater than or equal to 1:3 and less than or equal to 1:2.

[0009] In one of the embodiments, the diameter of the narrowest part of the intermediate part is greater than or equal to 30 mm and less than or equal to 100 mm; and / or, the radial dimension of the air inlet is greater than or equal to 50 mm and less than or equal to 200 mm; and / or, the radial dimension of the air outlet is greater than or equal to 80 mm and less than or equal to 250 mm.

[0010] In one of the embodiments, the length of the through hole along the first direction is greater than or equal to 1 m and less than or equal to 3 m.

[0011] In one of the embodiments, the distance between adjacent air inlets is greater than or equal to 50 mm and less than or equal to 200 mm.

[0012] In one of the embodiments, the aircraft landing platform further comprises a support structure. The support structure is supported on the platform along the first direction, and the support structure is provided with a ventilation space, the ventilation space is communicated with the plurality of air outlets respectively, and the outer side of the support structure is provided with a ventilation opening communicated with the ventilation space.

[0013] In one of the embodiments, the aircraft landing platform further comprises a sound absorption structure. The sound absorption structure is arranged in the ventilation space and connected to the support structure.

[0014] In one of the embodiments, the sound absorption structure corresponds to at least part of the area of the platform and is arranged spaced apart from the platform along the first direction.

[0015] In one of the embodiments, the sound absorption structure is provided with a hole, the hole penetrates the sound absorption structure along the first direction; and / or, the sound absorption structure has multiple layers, the multiple layers of the sound absorption structure are arranged spaced apart from each other along the first direction. BRIEF DESCRIPTION OF DRAWINGS

[0016] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings in the embodiments will be briefly introduced as follows. It should be understood that the following drawings only show some of the embodiments of the present application, and therefore should not be considered as limiting the scope. For those skilled in the art, other related drawings can also be obtained without creative labor on the basis of these drawings.

[0017] Figure 1 The structure of the aircraft landing platform in an embodiment of the present application is shown.

[0018] Figure 2 The structure of the aircraft landing platform in an embodiment of the present application is shown. Figure 1 The top view of the aircraft landing platform in the embodiment shown is shown.

[0019] Figure 3 The structure of the aircraft landing platform in an embodiment of the present application is shown. Figure 1 The partial structure section view of the platform in the embodiment shown is shown.

[0020] Figure 4A partial structural sectional view of a hole wall in another embodiment of the present application.

[0021] Explanation of main element symbols:

[0022] Aircraft landing platform 100

[0023] Carrier 10

[0024] Through hole 10a

[0025] Air inlet 10b

[0026] Air outlet 10c

[0027] Mesh structure 11

[0028] Hole wall 111

[0029] Inlet portion 1112

[0030] Intermediate portion 1113

[0031] Outlet portion 1114

[0032] Parking identification 12

[0033] Support structure 21

[0034] Ventilation space 20a

[0035] Ventilation port 20b

[0036] Frame 211

[0037] Support column 212

[0038] Sound absorbing structure 22

[0039] First direction Z

[0040] Vortex area V

[0041] The following detailed description will further illustrate the present application in conjunction with the above-mentioned drawings. DETAILED DESCRIPTION

[0042] The technical solutions in the embodiments of the present application will be clearly and completely described in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only some of the embodiments of the present application, not all the embodiments.

[0043] It is to be understood that where the terms specific elements are preceded by the term "fixed" it will be taken to mean that the specific element can be directly on the other element or there can be intervening elements. Where a specific element is preceded by the term "connected" it will be taken to mean that the specific element can be directly connected to the other element or there can be intervening elements. Where a specific element is preceded by the term "disposed" it will be taken to mean that the specific element can be directly disposed on the other element or there can be intervening elements. The terms "vertical", "horizontal", "left", "right" and similar expressions used herein are for illustrative purposes only.

[0044] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. The terminology used in the description herein is for describing particular embodiments only and is not intended to be limiting of the application. As used herein, the term "and / or" includes any and all combinations of one or more of the associated listed items.

[0045] Some embodiments of the present application are described in detail. In the case of no conflict, the following embodiments and features in the embodiments can be combined with each other.

[0046] Embodiments

[0047] Figure 1 Structure diagram of the aircraft landing platform 100 in an embodiment of the present application; Figure 2 Structure diagram of the aircraft landing platform 100 in an embodiment of the present application; Figure 1 Top view of the aircraft landing platform 100 in the embodiment shown; Figure 3 Structure diagram of the aircraft landing platform 100 in the embodiment shown; Figure 1 Partial structure section view of the platform 10 in the embodiment shown; Figure 4 Partial structure section view of the hole wall 111 in another embodiment of the present application.

[0048] Referring to Figures 1 to 3 , the embodiment provides an aircraft landing platform 100, comprising a platform 10, the platform 10 comprising a mesh structure 11, the mesh structure 11 defining a plurality of through holes 10a, the through holes 10a penetrating through the platform 10 along a first direction Z, the through holes 10a having a hole wall 111, the hole wall 111 comprising an entry portion 1112, an intermediate portion 1113 and an exit portion 1114 arranged in sequence along the first direction Z, and along the first direction Z, the intermediate portion 1113 protrudes to the inside of the through hole 10a relative to the entry portion 1112 and the exit portion 1114. Along the first direction Z, the entry portion 1112, the intermediate portion 1113 and the exit portion 1114 smoothly transition. The through hole 10a has an air inlet 10b at one end close to the entry portion 1112, and has an air outlet 10c at one end close to the exit portion 1114.

[0049] The aircraft landing platform 100, the carrier 10 is used to carry an aircraft (such as a vertical take-off and landing aircraft), and the aircraft can take off from the carrier 10 or park on the carrier 10. When the aircraft lands on the carrier 10, the downwash generated by the rotor of the aircraft will be reflected when it approaches the ground, forming a ground effect reaction force. By providing the mesh structure 11 on the carrier 10, the mesh structure 11 defines a plurality of through holes 10a, which can capture and block part of the dust and sand, reduce the dust storm effect, and guide and disperse the airflow, thereby reducing the influence of airflow reflection, and the mesh structure 11 makes the plurality of through holes 10a more evenly distributed, so that the airflow generated by the rotor of the aircraft is more evenly dispersed, thereby further reducing the airflow reflection and the ground effect reaction force, and increasing the stability of the aircraft landing. In the first direction Z, the inlet portion 1112, the middle portion 1113 and the outlet portion 1114 are smoothly transitioned to facilitate the flow of the airflow from the air inlet 10b to the air outlet 10c. Moreover, due to the middle portion 1113 of the hole wall 111 protruding towards the inside of the through hole 10a relative to the inlet portion 1112 and the outlet portion 1114, in combination with the mesh structure 11 shown, in the process of the airflow flowing from the air inlet 10b to the air outlet 10c, the airflow is hindered by the middle portion 1113, thereby changing the straight path of the airflow, which is beneficial to forming an approximately elliptical vortex area V in the outlet portion 1114, and the high-pressure airflow is guided into the vortex area V. When the airflow enters the vortex area V, a vortex is formed in the vortex area V, the pressure of the airflow is redistributed in the vortex area V, and the energy of the airflow is dispersed to a larger area, rather than directly impacting the ground, thereby reducing the concentration of the airflow, i.e. reducing the intensity of the airflow directly impacting the ground or the surrounding environment. Moreover, by forming the vortex area V, the continuous airflow pattern is broken, and the impact frequency of the airflow is reduced. Therefore, the aircraft landing platform 100 reduces the influence of the airflow on the surrounding environment and personnel when the aircraft lands, and improves the safety and stability of the aircraft landing. Figure 4

[0050] It should be noted that the middle portion 1113 protrudes towards the inside of the through hole 10a, which means that the middle portion 1113 protrudes in the direction of the central axis of the through hole 10a. In use, the first direction Z can be the direction of gravity. The inlet portion 1112, the middle portion 1113 and the outlet portion 1114 are integrally formed.

[0051] In some embodiments, the shapes and sizes of the plurality of through holes 10a are the same. In other embodiments, the shapes or sizes of the plurality of through holes 10a can also be different.

[0052] Optionally, the material of the carrier 10 includes at least one of glass fiber composite material, carbon fiber or aluminum alloy. In other embodiments, the material of the carrier 10 can also include other high-strength lightweight materials.

[0053] ​In some embodiments, along the first direction Z, the curvature of the orifice wall 111 is greater than or equal to 30 degrees and less than or equal to 60 degrees to further optimize the airflow path and reduce airflow reflection and ground effect forces. It should be noted that since the curvature of the orifice wall 111 affects the path and velocity changes of airflow dispersion, the curvature range can be adjusted to suit different types of aircraft and different rotor downwash airflows. For example, when the curvature of the orifice wall 111 is small (close to 30 degrees), it can achieve smoother airflow guidance, which is suitable for low-impact scenarios. When the curvature of the orifice wall 111 is large (close to 60 degrees), it can disperse high-impact airflow more quickly, which is suitable for strong airflow scenarios.

[0054] In some embodiments, such as Figure 3 As shown, the ratio of the aperture L1 at the narrowest point of the middle section 1113 to the radial dimension L2 of the air inlet 10b is greater than or equal to 1:3 and less than or equal to 1:2, to balance the effects of airflow dispersion and dust capture. It should be noted that the range of the ratio of the aperture L1 at the narrowest point of the middle section 1113 to the radial dimension L2 of the air inlet 10b affects the airflow dispersion efficiency. For example, a larger ratio (such as 1:2) is suitable for enhancing airflow compression and particle capture capabilities, while a smaller ratio (such as 1:3) is suitable for more efficient airflow release and dispersion. Specific values ​​can be adjusted according to site requirements and aircraft model.

[0055] In some embodiments, the ratio of the aperture L1 at the narrowest point of the middle portion 1113 to the radial dimension L3 of the outlet 10c is greater than or equal to 1:3 and less than or equal to 1:2, in order to facilitate airflow dispersion.

[0056] In some embodiments, the radial dimension L3 of the air outlet 10c is greater than or equal to the radial dimension L2 of the air inlet 10b, and the dimension of the outlet portion 1114 along the first direction Z is greater than or equal to the dimension of the inlet portion 1112 along the first direction Z, so that the space in the outlet portion 1114 is greater than or equal to the space in the inlet portion 1112, thereby facilitating the formation of a vortex region V in the outlet portion 1114.

[0057] In some embodiments, the aperture L1 at the narrowest point of the intermediate portion 1113 is greater than or equal to 30 mm and less than or equal to 100 mm, so that the airflow has better compression and release efficiency, respectively. When the aperture L1 at the narrowest point of the intermediate portion 1113 is smaller (close to 30 mm), it is beneficial to increase the compression effect of the airflow, which is suitable for weakening the impact of high-energy airflow. When the aperture L1 at the narrowest point of the intermediate portion 1113 is larger (close to 100 mm), it is suitable for the smooth release of airflow, which improves the stability during landing. By optimizing the aperture L1 at the narrowest point of the intermediate portion 1113, the ground effect reaction force can be further reduced.

[0058] In some embodiments, the radial dimension L2 of the air inlet 10b is greater than or equal to 50 mm and less than or equal to 200 mm to balance the air flow dispersion and particle capturing efficiency. It is to be noted that the radial dimension L2 of the air inlet 10b directly affects the preliminary dispersion effect of the air flow. For example, the radial dimension L2 of the air inlet 10b is greater (close to 200 mm) for high air flow intensity scenarios to reduce the concentrated reflection of the air flow, and the radial dimension L2 of the air inlet 10b is smaller (close to 50 mm) for low air flow intensity scenarios to help enhance the particle capturing capability.

[0059] In some embodiments, the radial dimension L3 of the air outlet 10c is greater than or equal to 80 mm and less than or equal to 250 mm. It is to be noted that the radial dimension L3 of the air outlet 10c determines the way the air flow is finally dispersed to the external environment. The radial dimension L3 of the air outlet 10c is smaller (close to 80 mm) for controlling the air flow speed to reduce the impact on the ground and surrounding facilities, and the radial dimension L3 of the air outlet 10c is greater (close to 250 mm) for quickly releasing the air flow to adapt to high air flow intensity air flow take-off and landing scenarios.

[0060] In some embodiments, as shown in FIG. 1B, the air inlet 10b is configured in a circular arc shape, for example, the air inlet 10b can be configured in a circular shape, an elliptical shape, or other irregular shapes. Figure 2

[0061] In some embodiments, the length H of the through hole 10a along the first direction Z is greater than or equal to 1 m and less than or equal to 3 m to balance the buffering effect of the platform 10 and the complexity of the structure. When the length H of the through hole 10a along the first direction Z is longer, a larger buffering space can be provided to reduce the air flow speed, thereby reducing the pressure of the air flow on the platform 10 and the ground impact, and when the length H of the through hole 10a along the first direction Z is shorter, it is beneficial to reduce the complexity and cost of the structure.

[0062] In some embodiments, the spacing between adjacent air inlets 10b is greater than or equal to 50 mm and less than or equal to 200 mm. The spacing between adjacent air inlets 10b determines the dispersion density of the air flow. When the spacing between adjacent air inlets 10b is smaller (close to 50 mm), a finer air flow dispersion can be achieved to reduce the ground effect reaction force, and when the spacing between adjacent air inlets 10b is greater (200 mm), it is suitable for quickly releasing the air flow to reduce the superposition effect of the vortex flow.

[0063] It is to be noted that the size and density of the through hole 10a can be adjusted according to the application scenario.

[0064] In some embodiments, as shown in FIG. 1B, the air inlet 10b is configured in a circular arc shape, for example, the air inlet 10b can be configured in a circular shape, an elliptical shape, or other irregular shapes. Figure 2 ​As shown, the platform 10 is also equipped with a parking mark 12 to facilitate identification of the aircraft take-off and landing platform 100. Optionally, the parking mark 12 includes a ring mark and an H-shaped mark.

[0065] In some embodiments, such as Figure 1 As shown, the aircraft takeoff and landing platform 100 also includes a support structure 21, which is supported on the platform 10 along the first direction Z. The support structure 21 is provided with a ventilation space 20a, which is connected to a plurality of air outlets 10c (see...). Figure 3 Furthermore, the outer side of the support structure 21 is provided with a vent 20b that communicates with the ventilation space 20a. In this way, the support structure 21 is provided to improve the stability of the aircraft take-off and landing platform 100. After the airflow flows into the ventilation space 20a through the through hole 10a, it flows out of the aircraft take-off and landing platform 100 through the vent 20b, so as to further reduce the impact of airflow on the surrounding environment.

[0066] In some embodiments, such as Figure 1 As shown, the aircraft takeoff and landing platform 100 also includes a sound-absorbing structure 22. The sound-absorbing structure 22 is disposed in the ventilation space 20a and connected to the support structure 21. Thus, by providing the sound-absorbing structure 22, noise pollution during aircraft takeoff and landing is reduced, further minimizing the impact on the surrounding environment and personnel. Optionally, the material of the sound-absorbing structure 22 includes sound-absorbing materials. In some embodiments, such as... Figure 1 As shown, the sound-absorbing structure 22 corresponds to at least a portion of the platform 10 and is spaced apart from the platform 10 along the first direction Z, so that airflow can flow out of the vent 20b between the sound-absorbing structure 22 and the platform 10.

[0067] In some embodiments, the sound-absorbing structure 22 is provided with holes (not shown) that extend through the sound-absorbing structure 22 along a first direction Z to allow airflow exiting the stage 10 to pass through. Optionally, each hole corresponds to a plurality of through holes 10a in the stage 10 (see...). Figure 3 This further facilitates the airflow through the sound-absorbing structure 22 along the first direction Z.

[0068] In some embodiments, such as Figure 1 As shown, the support structure 21 includes a frame 211 and a plurality of support columns 212. The frame 211 surrounds the outside of the platform 10, and the plurality of support columns 212 support the frame 211 along the first direction Z on the side near the air outlet 10c. The outer side of the sound-absorbing structure 22 is connected to the plurality of support columns 212 respectively. Optionally, the sound-absorbing structure 22 is constructed in the form of a plate.

[0069] In some embodiments, such as Figure 1As shown, the sound-absorbing structure 22 has multiple layers, and the multiple layers of the sound-absorbing structure 22 are arranged at intervals along the first direction Z to enable airflow to flow out of the air vent 20b between adjacent sound-absorbing structures 22. In this way, by arranging the sound-absorbing structure 22 in multiple layers, the sound-absorbing and reflecting effects of the sound-absorbing structure 22 on noise are improved, further reducing noise pollution during take-off and landing of the aircraft. Optionally, the thickness of each layer of the sound-absorbing structure 22 along the first direction Z is 20-50 mm, to more effectively reduce noise pollution during take-off and landing, especially in densely populated urban environments. It should be noted that the thickness of the sound-absorbing structure 22 has a direct impact on the noise attenuation effect, and a smaller thickness of the sound-absorbing structure 22 (close to 20 mm) is suitable for low-noise scenarios, and a larger thickness of the sound-absorbing structure 22 (close to 50 mm) is suitable for high-noise scenarios.

[0070] In other embodiments, the sound-absorbing structure 22 can also have one layer.

[0071] In use, the aircraft landing platform 100 can be fixed to the roof or a dedicated platform by the support column 212, forming a landing area for the aircraft.

[0072] The aircraft landing platform 100 provided by the embodiments of the present application has a simple structure and low cost, and is easy to install or modify on existing aircraft landing platforms 100. By arranging the mesh structure 11, the airflow generated by the rotor can be effectively dispersed and guided to reduce airflow reflection and ground effect reaction force, thereby improving landing stability, and the dust storm effect is reduced by the plurality of through holes 10a. The vortex area V is formed by the structure of the hole wall 111, which optimizes the airflow path and provides a buffering effect, thereby reducing the impact strength and impact frequency of the airflow, reducing the impact of the airflow on the surrounding environment and personnel, and reducing safety hazards. The sound-absorbing structure 22 is arranged to reduce noise. Therefore, the aircraft landing platform 100 described above improves the safety of the take-off and landing process, reduces environmental pollution, improves the acceptability of the rotorcraft in urban environments, and is particularly suitable for densely populated urban environments.

[0073] The above embodiments are only used to illustrate the technical solutions of the present application and not to limit it, although the present application has been described in detail with reference to the above preferred embodiments, those skilled in the art should understand that the technical solutions of the present application can be modified or replaced by equivalents without departing from the spirit and scope of the present application.

Claims

1. An aircraft landing platform, characterized in that, The platform comprises a net structure defining a plurality of through holes penetrating the platform along a first direction, the through holes having a hole wall comprising an inlet portion, an intermediate portion and an outlet portion arranged in sequence along the first direction, and along the first direction, the intermediate portion is convex to the inner side of the through hole relative to the inlet portion and the outlet portion, and the inlet portion, the intermediate portion and the outlet portion are smoothly transitioned along the first direction. The through hole has an air inlet end near the inlet portion and an air outlet end near the outlet portion. Along the first direction, the curvature of the hole wall is greater than or equal to 30 degrees and less than or equal to 60 degrees.

2. The aircraft docking platform of claim 1, wherein: The ratio of the hole diameter at the narrowest part of the intermediate portion to the radial dimension of the air inlet is greater than or equal to 1:3 and less than or equal to 1:2; and / or, 3. The aircraft docking platform of claim 1, wherein: The ratio of the hole diameter at the narrowest part of the intermediate portion to the radial dimension of the air outlet is greater than or equal to 1:3 and less than or equal to 1:

2.

4. The aircraft landing platform according to claim 1, wherein: The hole diameter at the narrowest part of the intermediate portion is greater than or equal to 30 mm and less than or equal to 100 mm; and / or, The radial dimension of the air inlet is greater than or equal to 50 mm and less than or equal to 200 mm; and / or, The radial dimension of the air outlet is greater than or equal to 80 mm and less than or equal to 250 mm. The length of the through hole along the first direction is greater than or equal to 1 m and less than or equal to 3 m.

5. The aircraft docking platform of claim 1, wherein: The distance between adjacent air inlets is greater than or equal to 50 mm and less than or equal to 200 mm.

6. The aircraft docking platform of claim 1, wherein: The aircraft landing platform further comprises a support structure; 7. The aircraft docking platform of claim 1, wherein: The support structure is supported on the platform along the first direction, the support structure is provided with a ventilation space, the ventilation space is in communication with a plurality of air outlets respectively, and the outer side of the support structure is provided with a ventilation port in communication with the ventilation space. The aircraft landing platform further comprises an acoustic absorption structure; 8. The aircraft docking platform of claim 7, wherein: The acoustic absorption structure is arranged in the ventilation space and connected to the support structure. The acoustic absorption structure corresponds to at least part of the area of the platform and is arranged spaced apart from the platform along the first direction.

9. The aircraft docking platform of claim 8, wherein:

10. The aircraft landing platform according to claim 9, wherein: The acoustic absorption structure is provided with a hole penetrating the acoustic absorption structure along the first direction; And / or, The acoustic absorption structure has multiple layers, and the multiple layers of the acoustic absorption structure are arranged spaced apart from each other along the first direction. ​

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