Aircraft take-off and landing platform

Abstract

The invention 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 which comprises a carrying platform, a plurality of through holes are formed in the carrying platform and penetrate through the carrying platform in the first direction, and each through hole is provided with a hole wall; 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. 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 aircraft has the beneficial effects that airflow is blocked when flowing through the middle part in the process of flowing from the air inlet to the air outlet, a vortex region is favorably formed at the outlet part, and high-pressure airflow generated by a rotor wing of the aircraft is guided into the vortex region, so that the impact strength and the impact frequency of the airflow to the ground and the surrounding environment are reduced, and the service life of the aircraft is prolonged. And the safety and the stability of the aircraft during landing are further improved.

Description

Technical Field

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

[0002] In order to provide support for an aircraft during takeoff and landing, an aircraft takeoff and landing platform is provided in the related art, which is used on a roof or other specific aircraft takeoff and landing areas.

[0003] However, since airflow is easily generated when an aircraft takes off and lands, such as when a helicopter lands, the airflow generated by the rotor will be reflected back when it approaches the ground, forming a ground effect reaction force, causing the aircraft to be unstable when landing. Summary of the invention

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

[0005] The embodiment of the present application provides an aircraft take-off and landing platform, including a platform, the platform is provided with a plurality of through holes, the through holes penetrate the platform along a first direction, the through holes have a hole wall, the hole wall includes an inlet portion, a middle portion and an outlet portion arranged in sequence along the first direction; and along the first direction, the middle portion protrudes toward the inner side of the through hole relative to the inlet portion and the outlet portion. The through hole has an air inlet at one end close to the inlet portion, and an air outlet at one end close to the outlet portion.

[0006] The above-mentioned aircraft take-off and landing platform is configured with a middle portion that protrudes relative to the inlet portion and the outlet portion respectively, so that the airflow is obstructed when flowing through the middle portion during the process of flowing from the air inlet to the air outlet, which is conducive to the formation of a vortex zone at the outlet portion. 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, thereby improving the safety and stability of the aircraft during landing.

[0007] In one of the embodiments, along the first direction, the inlet portion, the middle portion and the outlet portion transition smoothly.

[0008] In one embodiment, 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.

[0009] In one embodiment, the ratio of the aperture at the narrowest point of the middle 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 aperture at the narrowest point of the middle 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.

[0010] In one embodiment, the aperture at the narrowest point of the middle 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.

[0011] In one embodiment, the length of the through hole along the first direction is greater than or equal to 1 meter and less than or equal to 3 meters.

[0012] In one embodiment, the carrier includes a mesh structure defining a plurality of through holes.

[0013] In one embodiment, the distance between adjacent air inlets is greater than or equal to 50 mm and less than or equal to 200 mm.

[0014] In one embodiment, the aircraft landing platform further comprises a support structure. The support structure is supported on the platform along a first direction, the support structure is provided with a ventilation space, the ventilation space is respectively connected to a plurality of air outlets, and a ventilation port connected to the ventilation space is provided on the outer side of the support structure.

[0015] In one embodiment, the aircraft take-off and landing platform further includes a sound absorbing structure, which is arranged in the ventilation space and connected to the supporting structure. BRIEF DESCRIPTION OF THE 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 below. It should be understood that the following drawings only show certain embodiments of the present application and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other related drawings can be obtained based on these drawings without creative work.

[0017] Figure 1 It is a schematic diagram of the structure of an aircraft take-off and landing platform in one embodiment of the present application.

[0018] Figure 2 for Figure 1 A top view of the aircraft landing platform in the illustrated embodiment.

[0019] Figure 3 for Figure 1 A partial structural cross-sectional view of the carrier in the illustrated embodiment.

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

[0021] Description of main component symbols: Aircraft take-off and landing platform 100 Stage 10 Through hole 10a Air inlet 10b Air outlet 10c Mesh structure 11 Hole wall 111 Entrance Department 1112 Middle part 1113 Export 1114 Stop sign 12 Support structure 21 Ventilation space 20a Vent 20b Frame 211 Support column 212 Sound absorbing structure 22 First direction Z Eddy current area V The following specific implementation methods will further illustrate the present application in conjunction with the above-mentioned drawings. DETAILED DESCRIPTION

[0022] The technical solutions in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all of the embodiments.

[0023] It should be noted that when an element is referred to as being "fixed to" another element, it may be directly on the other element or there may also be a centered element. When an element is considered to be "connected to" another element, it may be directly connected to the other element or there may also be a centered element. When an element is considered to be "set on" another element, it may be directly set on the other element or there may also be a centered element. The terms "vertical", "horizontal", "left", "right" and similar expressions used herein are for illustrative purposes only.

[0024] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as those commonly understood by those skilled in the art to which this application belongs. The terms used herein in the specification of this application are only for the purpose of describing specific embodiments and are not intended to limit this application. The term "or / and" used herein includes any and all combinations of one or more related listed items.

[0025] Some embodiments of the present application are described in detail. In the absence of conflict, the following embodiments and features of the embodiments can be combined with each other.

[0026] Example Figure 1 It is a structural schematic diagram of an aircraft take-off and landing platform 100 in one embodiment of the present application; Figure 2 for Figure 1 A top view of the aircraft landing platform 100 in the illustrated embodiment; Figure 3 for Figure 1 A partial structural cross-sectional view of the stage 10 in the illustrated embodiment; Figure 4 It is a partial structural cross-sectional view of the hole wall 111 in another embodiment of the present application.

[0027] See also Figures 1 to 3 The present embodiment provides an aircraft take-off and landing platform 100, including a platform 10, the platform 10 is provided with a plurality of through holes 10a, the through holes 10a penetrate the platform 10 along a first direction Z, the through holes 10a have a hole wall 111, the hole wall 111 includes an inlet portion 1112, a middle portion 1113 and an outlet portion 1114 arranged in sequence along the first direction Z, and along the first direction Z, the middle portion 1113 protrudes toward the inner side of the through hole 10a relative to the inlet portion 1112 and the outlet portion 1114. The through hole 10a has an air inlet 10b at one end close to the inlet portion 1112, and an air outlet 10c at one end close to the outlet portion 1114.

[0028] The above-mentioned aircraft landing platform 100, the platform 10 is used to carry an aircraft (such as a vertical take-off and landing aircraft), and the aircraft can take off and land from the platform 10 or park on the platform 10. When the aircraft lands on the platform 10, the downwash airflow generated by the rotor of the aircraft will be reflected when it approaches the ground, forming a ground effect reaction force. By arranging multiple through holes 10a on the platform 10, it is possible to capture and block part of the dust and gravel, reduce the dust storm effect, and the multiple through holes 10a can guide and disperse the airflow, thereby reducing the impact of airflow reflection. And because the middle part 1113 of the hole wall 111 protrudes toward the inside of the through hole 10a relative to the inlet part 1112 and the outlet part 1114, combined with Figure 4 As shown, in the process of making the air flow flow from the air inlet 10b to the air outlet 10c, the air flow is hindered by the middle part 1113, thereby changing the straight path of the air flow, which is conducive to forming an approximately elliptical vortex area V at the outlet part 1114, and the high-pressure air flow is guided into the vortex area V. When the air flow enters the vortex area V, a vortex is formed in the vortex area V, so that the pressure of the air flow is redistributed in the vortex area V, and the energy of the air flow is dispersed to a larger area instead of directly impacting the ground, thereby reducing the concentration intensity of the air flow, that is, reducing the intensity of the air flow directly impacting the ground or the surrounding environment. And by forming the vortex area V, the continuous airflow pattern is interrupted and the impact frequency of the airflow is reduced. Therefore, the aircraft landing platform 100 reduces the impact of the airflow on the surrounding environment and personnel during the landing of the aircraft, and improves the safety and stability of the aircraft during landing.

[0029] It should be noted that the middle portion 1113 protrudes toward the inner side of the through hole 10a, which means that the middle portion 1113 protrudes toward the center axis of the through hole 10a. When in use, the first direction Z may be the direction of gravity. The inlet portion 1112, the middle portion 1113 and the outlet portion 1114 are integrally formed.

[0030] 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 may also include other high-strength and lightweight materials.

[0031] In some embodiments, Figure 3 and Figure 4 As shown, along the first direction Z, the inlet portion 1112, the middle portion 1113 and the outlet portion 1114 transition smoothly to facilitate the flow of air from the air inlet 10b to the air outlet 10c.

[0032] In some embodiments, along the first direction Z, the curvature of the hole wall 111 is greater than or equal to 30 degrees and less than or equal to 60 degrees, so as to further optimize the flow path of the airflow and reduce airflow reflection and ground effect force. It should be noted that, since the curvature of the hole wall 111 affects the path and speed change of airflow dispersion, the curvature range is adjusted to be suitable for different types of aircraft and different rotor downwash airflows. For example, when the curvature of the hole wall 111 is small (close to 30 degrees), a smoother airflow guidance can be achieved, which is suitable for low-impact scenarios. When the curvature of the hole wall 111 is large (close to 60 degrees), high-impact airflow can be dispersed more quickly, which is suitable for strong airflow scenarios.

[0033] In some embodiments, Figure 3 As shown, the ratio of the aperture L1 at the narrowest part of the middle part 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, so as to balance the effects of airflow dispersion and dust capture. It should be noted that the ratio range of the aperture L1 at the narrowest part of the middle part 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 the airflow compression and particle capture capabilities, and a smaller ratio (such as 1:3) is suitable for more efficient airflow release and dispersion. The specific value can be adjusted according to site requirements and aircraft models.

[0034] 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 air outlet 10c is greater than or equal to 1:3 and less than or equal to 1:2, so as to facilitate airflow dispersion.

[0035] 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 within the outlet portion 1114 is greater than or equal to the space within the inlet portion 1112, so as to facilitate the formation of a vortex zone V in the outlet portion 1114.

[0036] In some embodiments, the aperture L1 at the narrowest part of the middle part 1113 is greater than or equal to 30 mm and less than or equal to 100 mm, so that the airflow has good compression and release efficiency. When the aperture L1 at the narrowest part of the middle part 1113 is small (close to 30 mm), it is conducive to increasing the compression effect of the airflow and is suitable for reducing the impact of high-energy airflow. When the aperture L1 at the narrowest part of the middle part 1113 is large (close to 100 mm), it is suitable for smoothly releasing the airflow and improving the stability during landing. By optimizing the aperture L1 at the narrowest part of the middle part 1113, the ground effect reaction force can be further reduced.

[0037] 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 capture efficiency. It should be noted that the radial dimension L2 of the air inlet 10b directly affects the initial dispersion effect of the air flow. For example, when the radial dimension L2 of the air inlet 10b is large (close to 200 mm), it is suitable for scenes with high air flow intensity and can reduce the concentrated reflection of the air flow. When the radial dimension L2 of the air inlet 10b is small (close to 50 mm), it is suitable for scenes with low air flow intensity and helps to enhance the particle capture capability.

[0038] 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 should be noted that the radial dimension L3 of the air outlet 10c determines the way in which the airflow is finally dispersed to the external environment. When the radial dimension L3 of the air outlet 10c is small (close to 80 mm), it is suitable for controlling the airflow speed to reduce the impact on the ground and surrounding facilities. When the radial dimension L3 of the air outlet 10c is large (close to 250 mm), it is suitable for quickly releasing the airflow and adapting to the high airflow intensity airflow take-off and landing scene.

[0039] In some embodiments, Figure 2 As shown, the air inlet 10b is configured in an arc shape. For example, the air inlet 10b can be configured in a circular, elliptical or other irregular shapes.

[0040] In some embodiments, the length H of the through hole 10a along the first direction Z is greater than or equal to 1 meter and less than or equal to 3 meters to balance the buffering effect and structural complexity of the carrier 10. When the length H of the through hole 10a along the first direction Z is longer, a larger buffer space can be provided to reduce the airflow speed, thereby reducing the pressure of the airflow on the carrier 10 and the impact on the ground, 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.

[0041] In some embodiments, Figure 2 As shown, the platform 10 includes a mesh structure 11, and the mesh structure 11 defines a plurality of through holes 10a. In this way, the mesh structure 11 is provided to make the plurality of through holes 10a more evenly distributed, so that the airflow generated by the rotor of the aircraft is more evenly dispersed, so as to further reduce the airflow reflection and the ground effect reaction force, and increase the landing stability of the aircraft. Optionally, 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 may also be different.

[0042] 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 airflow. When the spacing between adjacent air inlets 10b is small (close to 50 mm), a finer airflow dispersion can be achieved to reduce the ground effect reaction force. When the spacing between adjacent air inlets 10b is large (200 mm), it is suitable for rapid release of airflow to reduce the superposition effect of vortices.

[0043] It should be noted that the size and density of the through holes 10a can be adjusted according to the application scenario.

[0044] In some embodiments, Figure 2 As shown, a parking mark 12 is also provided on the carrier 10 to facilitate identification of the aircraft landing platform 100. Optionally, the parking mark 12 includes a ring mark and an H-shaped mark.

[0045] In some embodiments, Figure 1 As shown, the aircraft take-off and landing platform 100 further includes a support structure 21, the support structure 21 is supported on the platform 10 along the first direction Z, and the support structure 21 is provided with a ventilation space 20a, and the ventilation space 20a is respectively connected to a plurality of air outlets 10c (see Figure 3 ), and a vent 20b communicating with the ventilation space 20a is provided on the outer side of the support structure 21. In this way, the support structure 21 is provided to improve the stability of the aircraft landing platform 100, and the airflow flows into the ventilation space 20a through the through hole 10a, and then flows out of the aircraft landing platform 100 through the vent 20b, so as to further reduce the impact of the airflow on the surrounding environment.

[0046] In some embodiments, Figure 1 As shown, the aircraft take-off and landing platform 100 also includes a sound absorbing structure 22. The sound absorbing structure 22 is arranged in the ventilation space 20a and connected to the support structure 21. In this way, by setting the sound absorbing structure 22, the noise pollution during the take-off and landing of the aircraft is reduced, and the impact of the take-off and landing of the aircraft on the surrounding environment and personnel is further reduced. Optionally, the material of the sound absorbing structure 22 includes sound absorbing material. 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 air can flow out of the vent 20 b between the sound absorbing structure 22 and the platform 10 .

[0047] In some embodiments, the sound absorbing structure 22 is provided with a hole (not shown), which penetrates the sound absorbing structure 22 along the first direction Z to allow the airflow out of the carrier 10 to pass through. Optionally, each hole corresponds to a plurality of through holes 10a of the carrier 10 (see Figure 3 ), so as to further facilitate the airflow to pass through the sound absorbing structure 22 along the first direction Z.

[0048] In some embodiments, Figure 1 As shown, the support structure 21 includes a frame 211 and a plurality of support columns 212, the frame 211 is arranged around the outside of the carrier 10, and the plurality of support columns 212 are supported on one side of the frame 211 close to the air outlet 10c along the first direction Z. The outer sides of the sound absorbing structure 22 are respectively connected to the plurality of support columns 212. Optionally, the sound absorbing structure 22 is constructed in a plate shape.

[0049] In some embodiments, Figure 1 As 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 so that the airflow can flow out of the vent 20b between adjacent sound absorbing structures 22. In this way, by arranging multiple layers of the sound absorbing structure 22, the absorption and reflection effect of the sound absorbing structure 22 on noise is improved, and the noise pollution during take-off and landing of the aircraft is further reduced. Optionally, the thickness of each layer of the sound absorbing structure 22 along the first direction Z is 20 mm to 50 mm, so as to more effectively reduce the 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. When the thickness of the sound absorbing structure 22 is small (close to 20 mm), it is suitable for low-noise scenes. When the thickness of the sound absorbing structure 22 is large (close to 50 mm), it is suitable for high-noise scenes.

[0050] In other embodiments, the sound absorbing structure 22 may also have a layer.

[0051] When in use, the aircraft take-off and landing platform 100 can be fixed on a roof or a dedicated platform or the like through the support columns 212 to form a landing area for the aircraft.

[0052] The aircraft landing platform 100 provided in the embodiment of the present application has a simple structure, low cost, and is easy to install or modify on the existing aircraft landing platform 100. By providing a 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 reducing the dust storm effect through multiple through holes 10a. The vortex zone 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 intensity and impact frequency of the airflow, reducing the impact of the airflow on the surrounding environment and personnel, and reducing safety hazards. A sound-absorbing structure 22 is provided to reduce noise. Therefore, the above-mentioned aircraft landing platform 100 improves the safety of the take-off and landing process, reduces environmental pollution, and improves the acceptability of the rotorcraft in the urban environment, and is particularly suitable for densely populated urban environments.

[0053] The above implementation modes are only used to illustrate the technical solutions of the present application and are not intended to limit the present application. Although the present application has been described in detail with reference to the above preferred implementation modes, a person skilled in the art should understand that the technical solutions of the present application may be modified or replaced by equivalents without departing from the spirit and scope of the technical solutions of the present application.

Claims

1. An aircraft take-off and landing platform, characterized in that: include: A carrier, wherein the carrier is provided with a plurality of through holes, the through holes penetrate the carrier along a first direction, the through holes have a hole wall, the hole wall comprises an entrance portion, a middle portion and an exit portion sequentially arranged along the first direction; and along the first direction, the middle portion protrudes toward the inner side of the through hole relative to the entrance portion and the exit portion; One end of the through hole close to the inlet portion has an air inlet, and one end of the through hole close to the outlet portion has an air outlet.

2. The aircraft take-off and landing platform according to claim 1, characterized in that: Along the first direction, the inlet portion, the middle portion and the outlet portion transition smoothly.

3. The aircraft take-off and landing platform according to claim 2, characterized in that: 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.

4. The aircraft take-off and landing platform according to claim 1, characterized in that: The ratio of the aperture at the narrowest point of the middle 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 aperture at the narrowest point of the middle 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.

5. The aircraft take-off and landing platform according to claim 1, characterized in that: The aperture of the narrowest part of the middle 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.

6. The aircraft take-off and landing platform according to claim 1, characterized in that: The length of the through hole along the first direction is greater than or equal to 1 meter and less than or equal to 3 meters.

7. The aircraft take-off and landing platform according to claim 1, characterized in that: The carrier includes a mesh structure, and the mesh structure defines a plurality of the through holes.

8. The aircraft take-off and landing platform according to claim 1, characterized in that: The distance between adjacent air inlets is greater than or equal to 50 mm and less than or equal to 200 mm.

9. The aircraft take-off and landing platform according to claim 1, characterized in that: The aircraft take-off and landing platform also includes a support structure; The support structure is supported on the carrier along the first direction, and a ventilation space is provided on the support structure. The ventilation space is connected to the plurality of air outlets respectively, and a ventilation port connected to the ventilation space is provided on the outer side of the support structure.

10. The aircraft take-off and landing platform according to claim 9, characterized in that: The aircraft take-off and landing platform also includes a sound absorbing structure; The sound absorbing structure is arranged in the ventilation space and connected to the supporting structure.

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