Heliport unit for takeoff and landing of helicopters or drones

Abstract

The present invention relates to a helipad unit for the take-off and landing of a helicopter or drone, comprising a plurality of module panels with protrusions formed on side walls, a support base spaced apart below the module panels, a T-shaped joint channel interposed between the module panels and having a resilient groove formed with an internal hollow portion and to which the protrusions are coupled, a clamping member inserted into the joint channel, and a plurality of support frames interposed between the support base and the module panels. In particular, the internal hollow portion of the joint channel, the open space provided at the bottom of each support frame, and the water receiving groove or downward sloping surface formed concavely below the space are aligned in the vertical direction to form a three-dimensional multi-stage drainage path that is mutually interconnected. According to the present invention, the structural reliability and environmental resistance of the helipad can be maximized, such as preventing corrosion of the structure and protecting internal electrical components, by stably supporting the impact of a heavy-load landing while actively guiding and collecting leakage entering through the gaps between the panels downward and safely discharging it.

Description

Technology Field

[0001] The present invention relates to a modular deck structure installed at a helicopter or drone landing pad, and more specifically to a helipad unit for the take-off and landing of a helicopter or drone in which panels are joined together at joints in modular units to form a landing surface. Background Technology

[0002] The utilization of helicopters and drones (hereinafter referred to as "aircraft") is expanding to areas such as emergency medical transport, disaster rescue, military operations, and Urban Air Mobility (UAM). Heliport units designed to facilitate the take-off and landing of these aircraft are installed in various environments, including urban rooftops, hospitals, offshore platforms, and mountainous regions. Consequently, there is a simultaneous demand for not only safe landing and take-off but also operational efficiency and ease of maintenance. Conventional heliport units are primarily composed of simple deck structures formed by combining multiple panels. While this offers the advantage of easy installation and construction, the following problems arise during actual operation.

[0003] First, there is a lack of fastening stability. In other words, the simple fastening between module panels is prone to loosening or deformation under repeated landing impacts or vibrations. This reduces the reliability of the entire helipad unit structure, causing difficulties in long-term operation.

[0004] Second, there is the absence of shock and vibration damping devices. Instantaneous shock loads generated during the landing of heavy helicopters are transmitted across the entire deck, concentrating excessive stress on the module panels and frame structure. Conventional structures lack buffering mechanisms to absorb or disperse this stress, leading to long-term fatigue damage and structural instability.

[0005] Third, there are limitations in environmental resistance and visibility. Heliport units installed outdoors are continuously exposed to various environmental conditions, such as rain, snow, salt, and dust. Since conventional lighting devices are installed by simply attaching them to the surface or in an exposed manner, they are vulnerable to external impact or contamination. Furthermore, if LEDs are positioned to protrude from the surface, there is a risk of interference with landing equipment.

[0006] Fourth, there is the inefficiency of wiring management. As the number of electrical equipment such as lighting, sensors, and drive units increases, wiring is becoming more complex. However, in conventional structures, cables are often simply placed under the panel or housed in separate conduits, resulting in poor maintainability and shielding performance. This increases maintenance costs and can cause electromagnetic interference (EMI) problems.

[0007] Fifth, there is a lack of safety equipment. In particular, the edges of heliport units pose a constant risk of aircraft or personnel falling during landing and takeoff. Conventionally, fixed handrails or simple boundary markers have often been installed, but these have limitations, such as restricting the aircraft landing space or failing to respond flexibly in emergency situations.

[0008] As such, while existing helipad units are faithful to ease of installation and basic functions, they have various technical limitations in terms of fastening stability, shock absorption, environmental resistance, wiring management, and safety equipment required during actual operation; therefore, a new helipad unit capable of resolving these issues is required. Prior art literature

[0009] Patent Document 1. Korean Published Patent Application No. 10-2017-0135603 (Publication Date Dec. 14, 2017) Patent Document 2. Korean Published Patent Application No. 10-2020-0042372 (Publication Date April 20, 2020) The problem to be solved

[0010] The present invention was devised to overcome these technical limitations of conventional heliport unit structures,

[0011] The objective of the present invention is to provide a structure that strengthens the fastening force between module panels and stably transmits the load to a lower support base by applying a T-shaped joint channel and a clamping member.

[0012] Another objective of the present invention is to prevent structural fatigue damage and improve safety by effectively absorbing landing shock and vibration by placing an elastic pad between the module panel and the lower support frame.

[0013] Another objective of the present invention is to arrange the LED indicator module flush with the upper surface of the panel and apply a waterproof structure to ensure stable visibility even in harsh environments and to facilitate maintenance.

[0014] Another objective of the present invention is to form an integrated wiring duct inside one side of a panel module while simultaneously inserting and protecting a heating coil internally, thereby improving maintainability and electromagnetic shielding performance.

[0015] Another objective of the present invention is to ensure safety without interfering with the operation of the aircraft by installing a variable fence that is automatically retracted upon landing and restored after takeoff. means of solving the problem

[0016] A helipad unit for the take-off and landing of a helicopter or drone according to the present invention comprises: a plurality of module panels with protrusions formed on side walls; a support base spaced apart below the plurality of module panels; a T-shaped joint channel interposed between the joint portions of the plurality of module panels, wherein the T-shaped joint channel has a hollow portion formed inside that is open in the vertical direction and is provided with a resilient groove on a vertically extended wall surface into which the protrusions of the module panels are inserted and fastened; a clamping member inserted and fixed inside the joint channel; and a plurality of support frames interposed between the plurality of module panels and the support base; wherein the lower portion of each support frame is provided with a space open in the vertical direction, and a concavely recessed water receiving groove or downward inclined surface is formed below the space, and the internal hollow portion of the joint channel, the lower space of the support frame, and the water receiving groove or downward inclined surface are aligned in the vertical direction to form an interconnected drainage path.

[0017] In addition, according to an embodiment of the present invention, an elastic pad may be further included that is disposed between the contact surfaces of the plurality of module panels and the plurality of support frames to disperse vertical loads and absorb shocks and vibrations during aircraft landing.

[0018] In addition, according to an embodiment of the present invention, an LED indicator module may be embedded and installed on the upper surface of the plurality of module panels to form a plane with the surface of the plurality of module panels, and a gasket is disposed on the outer edge of the LED indicator module to seal the gap with the plurality of module panels, thereby performing the functions of blocking the inflow of external foreign substances and absorbing vibrations.

[0019] In addition, according to an embodiment of the present invention, a wiring and heating coil housing for accommodating wiring and heating coils may be integrally formed on one side of the interior of the plurality of module panels, and a shielding layer for blocking electromagnetic interference (EMI) may be formed on the outer wall of the housing.

[0020] Additionally, according to an embodiment of the present invention, the joint channel may be formed from a metal extrusion molded body, and the upper portion of the joint channel may further include an upper cap having a pair of contact surfaces that are seated parallel to the landing surfaces of the plurality of module panels, and an elastic liner may be inserted and installed in at least a portion of the clamping member.

[0021] In addition, according to an embodiment of the present invention, the plurality of support frames may include a support channel having a stepped groove that extends outward from the end of the skirt surface and comes into close contact with the surface of the support base, wherein the lower side is formed as an extended skirt surface with a wider width than the upper side. Furthermore, between the spaced intervals of the plurality of support frames, a planar clamp is further included to be installed parallel to the support base and to securely fix the support channel, and both ends of the planar clamp may be provided with a stopper that enters along the stepped groove when a fastener is fastened to increase the fastening strength.

[0022] In addition, according to an embodiment of the present invention, a variable fence may be further included that is disposed at the edge of the plurality of module panels and automatically stored or restored by a control signal according to the landing and takeoff situation of the aircraft.

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[0032] According to the present invention, the following effects can be obtained.

[0033] First, the bonding strength between module panels is reinforced, suppressing loosening or deformation even under repeated landing impacts and vibrations of the aircraft, thereby improving fastening stability; consequently, the long-term structural reliability of the helipad unit is ensured and the maintenance cycle is extended.

[0034] Second, instantaneous impact loads and vibrations occurring during landing are effectively mitigated, preventing fatigue damage to the helipad unit structure and enhancing occupant safety.

[0035] Third, it can maintain stable lighting performance even in environments with rain, snow, or salt, and can provide high visibility even at night or in adverse weather conditions.

[0036] Fourth, through the wiring and heating coil housing provided in the module panel itself, LED modules, sensors, various wiring, and heating coils can be easily installed and effectively protected.

[0037] In summary, the present invention goes beyond merely listing elements such as fastening, lighting, drainage, and dustproofing of module panels individually proposed in conventional technology; by providing fastening stability, shock mitigation, environmental resistance, wiring management, and safety, it creates unpredictable synergistic effects and enables the safe and reliable operation of heliport units in various installation environments, such as hospitals, airports, offshore platforms, and urban rooftops. Furthermore, it possesses industrial applicability that allows for direct utilization in the future construction of Urban Air Mobility (UAM) infrastructure. Brief explanation of the drawing

[0038] FIG. 1 is a system schematic diagram showing the overall configuration of a modular deck system of a heliport unit for the take-off and landing of a helicopter or drone according to one embodiment of the present invention. FIG. 2 is a drawing illustrating the overall cross-sectional structure of a helipad configured by installing it on the upper end of a support base through a joint channel, a clamping member, and a support frame according to one embodiment of the present invention. FIG. 3 is a drawing illustrating the cross-sectional structure of a module panel according to one embodiment of the present invention. FIG. 4 is a drawing illustrating the cross-sectional structure of a T-shaped joint channel according to one embodiment of the present invention. FIG. 5 is a drawing illustrating the cross-sectional structure of a support frame according to one embodiment of the present invention. FIG. 6 is a drawing illustrating the cross-sectional structure of a planar clamp according to one embodiment of the present invention. Specific details for implementing the invention

[0039] Hereinafter, a 'heliport unit for the take-off and landing of a helicopter or drone' according to an embodiment of the present invention is described as follows.

[0040] FIG. 1 is a system schematic diagram showing the overall configuration of a modular deck system of a heliport unit for the take-off and landing of a helicopter or drone according to one embodiment of the present invention.

[0041] FIG. 2 is a drawing illustrating the overall cross-sectional structure of a helipad configured by installing it on the upper end of a support base through a joint channel, a clamping member, and a support frame according to one embodiment of the present invention.

[0042] A heliport unit (100) for the take-off and landing of a helicopter or drone according to the present invention may be configured to include a module panel (110) having a protrusion (112) formed on a wall surface (111), as shown in FIGS. 1 and 2.

[0043] In addition, it may be configured to include a T-shaped joint channel (210) installed between the module panels (110) to connect and fasten the module panels (110), and having a resilient groove (214) that is elastically seated on the protrusion (112) of the module panel (110) formed on the wall surface (111).

[0044] In addition, it may be configured to include a clamping member (220) that binds the module panel (110) within the joint channel (210) and reinforces the connection of the joint channel (210) to distribute the load acting from above and transmit it to a support base below.

[0045] Additionally, it may be configured to include a support frame (310) positioned at a predetermined distance between the module panel (110) and the support base (410) to distribute and support the vertical load during aircraft landing and to absorb shock and vibration. Here, the upper surface of the support frame (310) may be configured to include a support surface (301) that supports the lower surface of the module panel (110) by placing a plate pad (320) on it.

[0046] And, when a leak that has entered the internal hollow of the T-shaped joint channel (210) falls downward due to gravity, it can be configured to have a triple waterproof function in which it is collected in the space (314) formed at the bottom of the support frame (310) and discharged to the outside.

[0047] Here, the helipad unit (100) according to the present invention has a structure that strengthens the fastening stability between module panels (110), effectively disperses high loads and vibrations, and further blocks leakage occurring at the joint in three stages.

[0048] This is achieved through the organic combination of the T-shaped joint channel (210) and the support frame (310). The first stage of waterproofing is performed at the top of the helipad. By sealing the micro-gap between the module and the panel through a gasket (not shown) placed on the outer edge of the LED indicator module (120), rainwater, dust, salt, etc., entering the helipad surface are primarily blocked.

[0049] This protects the electrical components of the LED module and maintains stable lighting performance. In the second stage leakage path, any leakage that was not blocked in the first stage flows into the internal hollow of the T-shaped joint channel (210). The lower part of this internal hollow acts as a physical path to prevent water from spreading indiscriminately into the deck structure.

[0050] In the third stage of waterproofing, leakage falling from the lower part of the internal hollow of the joint channel (210) due to gravity passes through the lower space (314) of the lower support frame (310) and is collected in a water receiving groove (not shown) or slope (not shown) formed at the bottom and safely discharged to the outside of the structure.

[0051] This triple waterproof structure organically combines the original roles (bonding, shock absorption) of each component with independent waterproofing functions to fundamentally block leakage at multiple stages, thereby minimizing the possibility of corrosion of internal parts and electrical defects and improving the long-term reliability and durability of the helipad unit.

[0052] In addition, as illustrated in FIGS. 1 and 2, a variable fence (510) may be configured by placing it at the edge of the module panel (110). The variable fence (510) placed at the edge of the module panel (110) is configured to automatically retract or restore itself through a motor, hydraulic cylinder, or spring return type drive unit (520) by analyzing a signal detected by a sensor according to the takeoff and landing situation of the aircraft. Through this, the flight space of the aircraft can be secured, and at the same time, a crash prevention function can be provided after takeoff.

[0053] FIG. 3 is a drawing illustrating the cross-sectional structure of a module panel according to one embodiment of the present invention.

[0054] As shown in FIGS. 2 and 3, it may be preferable to configure the module panel (110) by placing an LED indicator module (120) on the upper surface at a predetermined position on the same plane as the surface of the module panel (110). Here, it is preferable to install the LED indicator module (120) so as to have the same plane as the surface of the module panel (110) to ensure there is no obstruction during the takeoff and landing of the aircraft.

[0055] In addition, it is preferable to provide a wiring and heating coil housing (113) capable of housing a heating coil (130) and various wirings on one end of the module panel (110).

[0056] FIG. 4 is a drawing illustrating the cross-sectional structure of a T-shaped joint channel according to one embodiment of the present invention.

[0057] The joint channel (210) may be configured to include an upper cap (212) formed of a metal extrusion molded body as shown in FIGS. 2 and 4, having a pair of contact surfaces (211) that are seated parallel to a landing surface (114) formed by stepping on the module panel (110), and a pair of vertical walls (213) that protrude downward from the contact surfaces (211) and are formed so that the interior is hollow.

[0058] Additionally, the vertical wall surface (213) of the joint channel (210) may be configured to include a resilient groove (214) that is elastically seated on a protrusion (112) formed on the wall surface (111) of the module panel (110) and inserted in close contact along the vertical wall surface (213).

[0059] The joint channel (210) is joined to the lower support frame (310) by a clamping member (220), wherein the clamping member (220) may be configured to include a bolt or a sliding key structure.

[0060] In addition, it may be configured to include an elastic pad (320) installed in the gap between the contact surface of the joint channel (210) and the support frame (310) to absorb shock and vibration transmitted from the top.

[0061] FIG. 5 is a drawing illustrating the cross-sectional structure of a support frame according to one embodiment of the present invention.

[0062] As shown in FIGS. 2 and 5, the support frame (310) is formed with an extended skirt surface (311) on the lower side that contacts the support base (410), which is wider than the upper side, in order to distribute the vertical load outward and strengthen the support strength when the aircraft lands, and includes a support channel (312) that extends outward from the end of the skirt surface (311) and is in close contact with the surface of the support base (410), and may be configured such that a stepped groove (313) is formed on the surface of the support channel (312).

[0063] FIG. 6 is a drawing illustrating the cross-sectional structure of a planar clamp according to one embodiment of the present invention.

[0064] As shown in FIGS. 2 and 6, the planar clamp (330) may be configured to be installed parallel to the support base (410) between the spaced-apart support frames (310) and arranged to connect the support channels (312) of the support frames (310) side by side to the support base (410) and secure them in close contact.

[0065] Here, it may be preferable that the surface clamp (330) be assembled to the support base (410) via a fastener (340) to suppress surface slip, shaking, flow, and deformation of the support frames (310).

[0066] Additionally, it may be preferable to form a plurality of grooves (332) on the lower surface of the above-mentioned surface clamp (330) to reduce weight, decrease the contact surface area with the support base (410), and suppress surface slip.

[0067] Additionally, the surface clamper (330) may be configured with a stopper (331) at both ends that enters along the step groove (313) formed in the support channel (312) when assembled to the support base (410) via the fastener (340), thereby increasing the fastening strength and maintaining the alignment of the support frame (310) and the overall assembly balance.

[0068] The configuration and operation of a heliport unit for the take-off and landing of a helicopter or drone according to an embodiment of the present invention are described in more detail as follows.

[0069] The heliport unit (100) of the present invention comprises a plurality of module panels (110) connected to each other to form a landing deck. Each module panel (110) is installed on a lower support frame (310).

[0070] When a water collection channel is formed at the joint of the module panels (110), rainwater or washing water can be managed so that it does not penetrate between the module panels (110) and drained smoothly.

[0071] The above module panel (110) is interconnected through the elastic connection of a protrusion (112) formed on a wall surface (111) and a resilient groove (214) formed on a vertical wall surface (213) of a T-shaped joint channel (210).

[0072] In addition, the clamping member (220), which is inserted and fastened inside the joint channel (210), supports the lower part of the protrusion (112), thereby effectively dispersing the vertical load and vibration load generated during the landing of the aircraft, and maximizing the fastening stability between the module panels (110). This fastening method prevents loosening even under repeated impact loads, thereby ensuring structural reliability in the long term.

[0073] Here, a plurality of module panels (110) are connected to each other through a T-shaped joint channel (210) at a joint where they meet, and a clamping member (220) is inserted inside the joint channel (210) to connect two adjacent module panels (110) simultaneously.

[0074] The above T-shaped joint channel (210) includes a contact surface (211) integrally processed as an extruded body on the lower surface and side of the module panels (110), an upper cap (212), a vertical wall surface (213) formed to be hollow inside, and a resilient groove (214) inserted in close contact along the vertical wall surface (213), and a clamping member (220) is inserted into the joint channel (210) and then fixed by bolt fastening or a sliding key method.

[0075] Unlike the conventional method of simply fixing module panels with screws, this structure greatly improves structural stability by distributing the load transfer path across the entire surface of the joint channel (210) and clamping member (220).

[0076] An elastic pad (320) is placed between the module panel (110) and the support frame (310). The elastic pad (320) placed in this manner effectively absorbs instantaneous shock and continuous vibration that occur during the landing of a helicopter or drone, thereby preventing fatigue damage to the structure and simultaneously improving the safety of the occupant.

[0077] Additionally, an LED marking module (120) is positioned on the upper surface of the module panel (110) in a flat plane with the surface of the module panel (110) so as not to interfere with the aircraft body during landing. During the installation process, a gasket (not shown) is installed to seal the LED marking module (120), thereby ensuring waterproof performance and providing high visibility in nighttime and adverse weather conditions.

[0078] In addition, a wiring and heating coil housing (113) is integrally formed on one side of the interior of the module panel (110) to protect the wiring of the LED indicator module (120), sensor, and driving part (not shown) of the variable fence (510) and to effectively block electromagnetic interference. Also, a variable fence (510) is provided at the edge of the helipad unit (100).

[0079] For example, when landing, the rotary electric variable fence (510) is controlled to rotate around a rotation axis (521) by outputting a control signal to a drive unit (520), such as a motor, according to a control signal from a control unit (not shown). Here, the control and drive system can be designed by simply applying various drive methods. For example, various drive methods, such as a rotary folding type or an up-down drive method using a hydraulic cylinder, can be selectively applied depending on the installation environment of the helipad site.

[0080] When a variable fence (510) is installed at the edge of the helipad unit (100) in this way, it is stowed to secure a landing space during normal operation, and restored after takeoff or while in a standby state to perform the functions of preventing crashes and ensuring safety. The variable fence (510) can provide clear visual guidance to pilots and operators by linking with LED markings.

[0081] The clamping member (220) is preferably made of metal or high-strength synthetic resin, and can be installed by inserting an elastic liner (not shown) in some areas as needed. This allows it to perform a cushioning function against minute shocks and vibrations that occur during landing.

[0082] Additionally, if the clamping member (220) is designed to facilitate the attachment and detachment of the module panel (110), simple separation and replacement are possible on a module panel (110) basis during maintenance. This provides the advantage of being able to quickly repair only some module panels (110) without dismantling the entire helipad unit (100).

[0083] Accordingly, as shown in FIG. 2, the fastening structure by the T-shaped joint channel (210) and clamping member (220) according to the present invention achieves the effects of strengthening the fastening stability between module panels (110), efficiently distributing shock and vibration loads, and providing convenience for maintenance.

[0084] Module panels (110) forming the deck structure of the heliport unit (100) are placed on a lower support frame (310), and a plurality of elastic pads (320) are interposed between them.

[0085] The elastic pad (320) functions as a major cushioning element that transmits the load and landing impact of the module panel (110) to the lower support frame (310) and then sequentially to the support base (410).

[0086] The elastic pad (320) is formed from a highly elastic material such as rubber, polyurethane, silicone, etc., and can be arranged in a double or multi-layer structure as needed. Although not specifically illustrated in the drawings, for example, the upper layer can be made relatively soft to absorb instantaneous shock, and the lower layer can be made hard to ensure long-term structural stability.

[0087] According to the present invention, the impact load generated at the moment a helicopter or drone lands is first transmitted to the module panel (110) and then absorbed through a compression deformation process while passing through the elastic pad (320). In this process, the impact energy is dispersed and dampened and transmitted to the support frame (310), thereby minimizing fatigue damage acting on the entire structure of the helipad unit.

[0088] In addition, the arrangement of the elastic pad (320) can be designed to absorb not only vertical loads but also horizontal vibrations and displacements, such as rotational or torsional loads. Accordingly, stability can be maintained under various landing conditions.

[0089] Preferably, the elastic pad (320) can be configured as a module to facilitate maintenance and can be replaced on an individual pad basis. This allows for efficient management even during long-term operation.

[0090] Accordingly, the elastic pad (320) placement structure of the present invention can effectively mitigate landing shock, absorb vibrations, prevent structural fatigue damage, and provide maintenance efficiency.

[0091] An LED marker module (120) is embedded and installed on the upper surface of the module panel (110). The LED marker module (120) is positioned flush with the surface of the module panel (110) to ensure stable landing without interfering with the ground surface of the landing device. Additionally, the flat positioning reduces the risk of damage caused by protrusions of the LED marker module (120) and provides ease of surface cleaning and maintenance.

[0092] It is preferable to place a gasket (not shown) on the outer edge of the LED indicator module (120). The gasket may be composed of a silicone O-ring, a plurality of rubber layers, or a foam sealing material, and completely seals the gap between the LED indicator module (120) and the module panel (110). This prevents the penetration of water, dust, salt, etc., thereby ensuring stable waterproof performance.

[0093] In addition, the gasket not only serves a waterproofing function but also performs the function of absorbing vibrations and assisting in the fastening stability of the LED indicator module (120). Heat generated when the LED indicator module (120) is lit is released to the outside through the module panel (110) and the thermally conductive filler, thereby improving durability.

[0094] If the LED indicator module (120) is designed to be easily detached and replaced from the top, it can be quickly replaced without dismantling the module panel (110) during maintenance.

[0095] Accordingly, the LED marking module (120) and gasket waterproof structure of the present invention can achieve the effects of securing landing stability, ensuring environmental resistance in adverse weather and outdoor environments, providing convenience for maintenance during long-term operation, and ensuring visibility suitable for aviation lighting standards.

[0096] Meanwhile, a wiring and heating coil housing (113) is integrally formed inside the module panel (110). The wiring and heating coil housing (113) can perform the function of accommodating and protecting various cables connected to the LED indicator module (120), the driving part of the variable fence (510), various sensors, and the control part.

[0097] In addition to the space for accommodating the heating coil (130) inside the duct of the wiring and heating coil housing (113), a separate cable tray (not shown) may be provided so that the wiring can be arranged in an organized manner, and in this case, interference or twisting between cables can be prevented.

[0098] In addition, if a separate shielding layer (not shown) is placed on the outer wall of the wiring and heating coil housing (113), electromagnetic interference (EMI) generated from the aircraft's communication equipment or surrounding electronic equipment can be effectively blocked. This ensures the stability of signal transmission and allows for management to prevent electrical abnormalities from occurring in the power supply for night lighting or fence drive units.

[0099] In addition, if a separate drain (not shown) is formed in the wiring and heating coil housing (113), rainwater or condensate can be automatically discharged if it flows into the interior. This prevents cable insulation failure or short circuits.

[0100] Accordingly, the wiring and heating coil housing (113) can provide maintenance convenience through the removal of snow and ice and freezing prevention by the heating of the heating coil (130), systematic accommodation and protection of wiring, stable signal transmission by EMI shielding, and improved environmental resistance by securing drainage.

[0101] Meanwhile, the driving mechanism of the variable fence (510) according to one embodiment of the present invention is described as follows.

[0102] The variable fence (510) installed at the edge of the helipad unit (100) has a structure that automatically retracts or restores depending on the landing and takeoff conditions of the aircraft. Unlike fixed railings or simple boundary markers, this ensures the safety of workers and equipment without hindering the landing and takeoff of the aircraft.

[0103] The variable fence (510) can be operated by a drive unit (520). The drive unit (520) can be implemented in various ways.

[0104] For example, the motor drive method can control the variable fence (510) to move vertically or horizontally by means of an electric motor and a gear train. Precise opening and closing control is possible according to a control signal from the control unit.

[0105] Another hydraulic drive method can be applied by using a hydraulic cylinder to raise and lower the variable fence (510), and stable operation can be ensured even in strong wind environments.

[0106] Another spring return mechanism maintains an upright position using the elastic force of springs under normal conditions, is lowered by a motor or hydraulics upon a landing signal, and can be controlled to stand upright again using the spring's restoring force upon release. This design is simple in structure, making maintenance easy.

[0107] The variable fence (510) can be linked with a sensor (not shown). For example, the sensor may receive an approach signal or a landing detection signal of an aircraft and transmit it to a control unit. In this case, the control unit may operate a drive unit according to the signal to retract or restore the variable fence (510).

[0108] Accordingly, the variable fence driving mechanism according to the present invention prevents spatial interference during the takeoff and landing of an aircraft, immediately restores the crash prevention function when necessary, and enables optimization according to the operating environment through the selective application of the driving method.

[0109] Meanwhile, the safety interlock sequence of the variable fence (510) according to one embodiment of the present invention is described as follows.

[0110] The variable fence (510) installed at the edge of the helipad unit (100) can be opened and closed automatically via a control unit, except for manual opening and closing. For example, it can be operated automatically through a safety interlock sequence that sequentially proceeds from sensor signal input → control → driving → status check. This ensures the safety of the pilot and the operator during the landing and takeoff process.

[0111] In addition, detection signal information detected by the sensor can be transmitted to the control unit as a control signal using various sensors. For example, signals of an aircraft's approach or takeoff / landing can be detected through sensors including radar sensors, infrared sensors, or wireless signal receivers. For instance, if an aircraft landing signal is detected, the sensor can transmit the imminent landing status to the control unit.

[0112] During the operation phase, the control unit analyzes the signal input from the sensor to determine whether to retract or restore the fence. That is, during the landing process, it instructs the variable fence (510) to retract, and after takeoff, it outputs a signal to restore the variable fence (510).

[0113] In the operation phase of the drive unit (520), the drive unit (520) operates according to the output signal of the control unit. The drive unit stores or restores the variable fence (510) in one of the following ways: a motor, a hydraulic cylinder, or a spring return.

[0114] When an LED indicator (not shown) is attached to the top of the variable fence (510) during the status check and visual guidance phase, the position (stored state / restored state) of the variable fence (510) can be visually displayed. Additionally, the control unit checks whether the variable fence (510) has operated correctly through sensor feedback.

[0115] Through this interlock sequence, the variable fence (510) is automatically retracted upon landing so as not to obstruct the approach of the aircraft, and is immediately restored after takeoff to perform a crash prevention function, and in emergency situations, the LED indicator can be flashed to indicate a dangerous condition.

[0116] In addition, the heliport unit (100) according to the present invention is based on a modular design, allowing for rapid installation and maintenance at the site.

[0117] In the installation phase, first, a support frame (310) is placed on a support base (410) corresponding to the foundation structure of the installation site. Subsequently, each module panel (110) is seated on the support frame (310), and adjacent module panels (110) are firmly connected through a T-shaped joint channel (210) and a clamping member (220).

[0118] Preferably, a water collection channel is formed at the joint between the module panels (110) so that the drainage function operates naturally even immediately after installation.

[0119] In the connection step between module panels (110), the wiring and heating coil housing (113) formed integrally inside each module panel (110) are connected, and the wiring required for the LED indicator module (120), sensor, variable fence (510), etc. is organized collectively.

[0120] The connection between the module panels (110) is made through a connector interface, allowing for quick construction without the need for separate soldering or wiring processing.

[0121] In the operation phase, after the module panel (110) is installed, the helipad unit (100) absorbs shock and vibration by means of an elastic pad (320), and can guide landing and ensure nighttime visibility through an LED marking module (120).

[0122] The variable fence (510) at the edge is automatically retracted upon landing and restored after takeoff, thereby ensuring the operation of the aircraft and the safety of the surroundings at the same time.

[0123] During the maintenance phase, the helipad unit (100) according to the present invention can be separated and replaced in module units. Therefore, only parts, including the damaged module panel (110), LED indicator module (120), elastic pad (320), etc., can be selectively replaced.

[0124] This modular maintenance structure allows only specific parts to be replaced without complete dismantling, minimizing downtime and reducing management costs. Explanation of the symbols

[0125] 100: Heliport unit 110: Module panel 111: Wall surface 112: Protrusion 113: Wiring and heating coil housing 114: Landing surface 120: LED indicator module 130: Heating coil 210: Joint channel (T-shaped) 211: Contact surface 212: Upper cap 213: Vertical wall surface 214: Resilient groove 220: Clamping member 310: Support frame 311: Skirt surface 312: Support channel 313: Step groove 320: Elastic pad 330: Face clamp 331: Stopper 340: Fastener 410: Support base 510: Variable Fence 520: Drive Unit 521: Rotation axis

Claims

Claim 1 A helipad unit for the take-off and landing of a helicopter or drone comprises: a plurality of module panels having protrusions formed on side walls; a support base spaced apart from the lower portion of the plurality of module panels; a T-shaped joint channel interposed between the joint portions of the plurality of module panels, wherein the T-shaped joint channel has a hollow portion formed inside that is open in the vertical direction and is provided with a resilient groove on a vertically extended wall surface into which the protrusions of the module panels are inserted and fastened; a clamping member inserted and fixed inside the joint channel; and a plurality of support frames interposed between the plurality of module panels and the support base; wherein the lower portion of each support frame is provided with a space open in the vertical direction, and a concavely recessed water receiving groove or downward sloping surface is formed below the space, and the internal hollow portion of the joint channel, the lower space of the support frame, and the water receiving groove or downward sloping surface are aligned in the vertical direction to form an interconnected drainage path. Claim 2 A heliport unit for the take-off and landing of a helicopter or drone, characterized in that, in claim 1, it further comprises an elastic pad disposed between the contact surfaces of the plurality of module panels and the plurality of support frames to disperse vertical loads and absorb shocks and vibrations during the landing of an aircraft. Claim 3 A heliport unit for the take-off and landing of a helicopter or drone, characterized in that, in claim 1, an LED marking module is embedded and installed on the upper surface of the plurality of module panels so as to be flush with the surface of the plurality of module panels. Claim 4 A heliport unit for the take-off and landing of a helicopter or drone, characterized in that, in claim 3, a gasket is disposed on the outer surface of the LED indicator module to seal the gap with the plurality of module panels, thereby blocking the inflow of external foreign matter and absorbing vibrations of the LED indicator module. Claim 5 A heliport unit for the take-off and landing of a helicopter or drone, characterized in that, in claim 1, a wiring and heating coil housing for accommodating wiring and heating coils is integrally formed on one side of the interior of the plurality of module panels. Claim 6 A heliport unit for the take-off and landing of a helicopter or drone, characterized in that, in claim 5, a shielding layer for blocking electromagnetic interference (EMI) is formed on the outer wall of the wiring and heating coil housing. Claim 7 A heliport unit for the take-off and landing of a helicopter or drone, characterized in that, in claim 1, the plurality of module panels include a landing surface formed by creating a step at the edge, the joint channel is formed of a metal extrusion molded body, and the upper cap further includes a pair of contact surfaces that are seated parallel to the landing surface of the plurality of module panels. Claim 8 A heliport unit for the take-off and landing of a helicopter or drone, characterized in that, in claim 1, the clamping member is formed of a metal material or a high-strength synthetic resin, and an elastic liner is inserted and installed in at least a portion of the clamping member to cushion the shock and vibration generated during the landing of an aircraft. Claim 9 A helipad unit for the take-off and landing of a helicopter or drone according to claim 1, wherein the plurality of support frames are formed with an expanded skirt surface having a wider width than the upper side on the lower side in contact with the support base to distribute and support the vertical load outwardly during landing of the aircraft and to reinforce the support strength, and include a support channel extending outward from the end of the skirt surface and in close contact with the surface of the support base, wherein a stepped groove is formed on the surface of the support channel. Claim 10 A helipad unit for the take-off and landing of a helicopter or drone according to claim 9, further comprising a planar clamp installed parallel along the support base between the spaced intervals of the plurality of support frames to connect the support channels of the plurality of support frames side by side to the support base and securely fix them, wherein both ends of the planar clamp are provided with a stopper that enters along a stepped groove formed in the support channel when assembled to the support base via a fastener to increase fastening strength and maintain the alignment of the plurality of support frames and overall assembly balance. Claim 11 A heliport unit for the take-off and landing of a helicopter or drone, characterized in that, in claim 1, it further includes a variable fence disposed at the edge of the plurality of module panels and automatically stored or restored by a control signal according to the landing and take-off situation of the aircraft.

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