A helicopter landing aid system

Abstract

The present application relates to the field of aircraft landing, in particular to a kind of helicopter landing aid system. Helicopter landing aid system includes lifting device, lifting device is provided with capture device, capture device includes frame body and movable member movable relative to frame body, frame body is equipped with the drive structure for driving movable member movement;Movable member is equipped with two, the end of two movable members is respectively matched with frame body, other end has the docking station of close docking, also has the far away station of mutual far away;Or, movable member is equipped with one, and the end of movable member has the docking station of close frame body, also has the far away station of far away frame body. By setting lifting device on ship, it is convenient to lift lifting device to find the position of helicopter, by the setting of capture device, it is convenient to capture the landing gear of helicopter;Further solve the problem that the performance of helicopter is deteriorated in the prior art, and helicopter needs to be additionally installed rope and hoisting winch to realize the capture of ship to helicopter.

Description

Technical Field

[0001] This invention relates to the field of aircraft landing, and more particularly to a helicopter landing assistance system. Background Technology

[0002] In existing technologies, ships are often equipped with drones to reconnoiter the surrounding sea area. Drones are a type of helicopter, capable of vertical takeoff and landing. During ascent, simply increasing horsepower is sufficient for the drone to overcome gravity and take off. After use, the drone needs to land on the ship. Due to the influence of waves and sea winds, it is difficult for drones to land smoothly, thus requiring an auxiliary landing system.

[0003] For example, Chinese utility model patent CN217100507U discloses a shipborne auxiliary recovery device for unmanned aerial vehicles (UAVs). It discloses a lifting assembly on the UAV, including a lifting winch mechanism and a lifting rope, with a first lifting hook at the end of the lifting rope. A recovery winch assembly is installed on the ship, with a recovery traction rope and a second lifting hook. When the UAV needs to land, it is first controlled to hover at a certain height. Then, the lifting rope on the lifting assembly is released, causing the first lifting hook to descend. The operator then engages the second lifting hook with the first lifting hook, connecting the UAV and the ship via the rope. Finally, the rope is wound up, allowing the UAV to dock on the ship under the rope's pull.

[0004] However, the above technical solutions require modifications to the helicopter, necessitating the installation of cables and hoisting winches to connect it to the ship. Helicopters have limited lift, and excessive additions to these structures would negatively impact their performance. Summary of the Invention

[0005] The purpose of this invention is to provide a helicopter landing assistance system to solve the problem in the prior art that helicopters need to be additionally equipped with ropes and hoisting winches to achieve ship capture of the helicopter, which leads to a decrease in helicopter performance.

[0006] To achieve the above objectives, the helicopter landing assistance system of this invention adopts the following technical solution:

[0007] A helicopter landing assistance system includes a lifting device, on which a capture device for capturing the landing gear of a helicopter is provided. The capture device includes a frame and movable parts that can move relative to the frame. The frame is provided with a drive structure for driving the movable parts. There are two movable parts, one end of each movable part is engaged with the frame, and the other end, under the action of the drive structure, has a docking position close to the frame and a moving position away from each other. When the other ends of the two movable parts are in the docking position, they form a limiting ring that encloses the landing gear. Alternatively, there is one movable part, the end of which, under the action of the drive structure, has a docking position close to the frame and a moving position away from the frame. When the end of the movable part is in the docking position, it, together with the frame, forms a limiting ring that encloses the landing gear.

[0008] The beneficial effects of the above technical solution are as follows: This invention innovatively proposes a helicopter landing assistance system. By installing a lifting device on the ship, it is easy to raise the lifting device to locate the helicopter's position. The capture device facilitates the capture of the helicopter's landing gear. The moving parts and drive structure on the capture device allow the moving parts to move relative to the frame. When two moving parts are provided, they can move away from each other or dock during movement. When moving away from each other, it is easy to capture the helicopter's landing gear by passing through it. When the two moving parts are in the docking position, a limiting ring is formed to control the landing gear. The system can surround the helicopter, thus capturing it; alternatively, a movable component can be provided, which, under the action of the drive structure, can work together with the frame to form a docking station that allows the landing gear to pass through and a limiting ring to limit the landing gear. By switching between the two stations, the helicopter's landing gear can be captured. In other words, no additional structure needs to be set on the helicopter. The capture of the helicopter can be completed through the cooperation of this system and the helicopter's landing gear. This solves the problem in the existing technology that helicopters need to be additionally equipped with ropes and hoisting winches to achieve ship capture of helicopters, which leads to a decrease in helicopter performance.

[0009] Furthermore, the other end of each of the two movable parts is a docking end, or the end of a single movable part that docks with the frame is also a docking end. Each of the two docking ends is equipped with a locking release device. The locking release device includes a housing, a locking element installed within the housing, and a drive mechanism for actuating the locking element. The capturing device also includes a locking pin and a rope connected to the locking pin. The locking release device with the locking pin pre-installed is a pre-installed device, and the locking release device with the locking pin finally installed is a final device. Each locking release device has a receiving groove on its housing for the end of the locking pin to be inserted into, and both ends of the locking pin have locking portions. The locking element, under the action of the drive mechanism, has a locking position that extends into the receiving groove to cooperate with the locking part to lock the locking pin, and a release position that disengages from the locking part to release the locking pin; when the locking pin is on the pre-installed device, one end of the locking pin is located in the receiving groove of the device and the locking element of the device is in the locking position; when the two mating ends are in the mating position, the other end of the locking pin is inserted into the receiving groove of the final device, and the locking element on the final device is in the locking position and the locking element on the pre-installed device is in the release position to realize the transfer of the locking pin; after the locking pin is transferred, the two mating ends move away from the position so that the rope attached to the locking pin is wrapped around the outside of the landing gear.

[0010] The beneficial effects of the above technical solution are as follows: by setting a locking release device and a locking pin that cooperates with the locking release device at the end of the docking end, it is convenient to transfer the rope. Since the rope is connected to the locking pin, the locking pin can dock with one of the two locking release devices respectively. Then, as the docking end of the moving part approaches and moves away, the locking pin can complete the transfer on the locking release device by cooperating with different locking release devices. Since the rope is connected to the locking pin, the transfer of the locking pin will also drive the transfer of the rope. The rope can be transferred from one docking end to the other docking end. At this time, the rope and the moving part can form a capture of the landing gear, completing the capture of the landing gear by the moving part and the capture of the landing gear by the rope.

[0011] Furthermore, the locking element is a latch, and the locking part is a snap-fit ​​groove for the latch to be inserted.

[0012] The advantages of the above technical solution are: the cooperation between the locking tongue and the locking groove makes the locking more reliable, the structure is simpler, and it is easier to process and manufacture.

[0013] Furthermore, the drive mechanism includes an electromagnetic coil and an elastic element. The electromagnetic coil is used to control the movement of the latch to the release position after being energized, and the elastic element is used to apply a force to the latch in the direction of the receiving groove.

[0014] The beneficial effects of the above technical solution are: it facilitates the movement of the locking tongue, and the locking pin can be locked and released respectively under the action of the electromagnetic coil and the elastic element.

[0015] Furthermore, the locking pin has a first guide surface at both ends; the locking tongue has a second guide surface that mates with the first guide surface.

[0016] The beneficial effect of the above technical solution is that the setting of two guide surfaces facilitates the locking pin to enter the locking position.

[0017] Furthermore, the pre-installed housing is provided with a limiting hole that communicates with the receiving groove and allows the rope to pass through.

[0018] The beneficial effect of the above technical solution is that the setting of the limiting hole provides a fulcrum for the rope, which facilitates the movement and threading of the rope.

[0019] Furthermore, the lifting device has a capture station for controlling the capture device to rise above the deck to form a limit ring and capture the landing gear, and a descent station for controlling the capture device to descend below the deck after the locking pin is transferred and the two docking ends move away from the station.

[0020] The advantages of the above technical solution are: the lifting device facilitates the movement of the capture device, thereby enabling the capture of helicopters, and it saves space because it can descend below the deck.

[0021] Furthermore, the helicopter landing system also includes a winch positioned below the deck. The rope is connected to the drum of the winch. During the process of the lifting device controlling the capture device to descend from the capture position to the descent position, the rope is in a slack state. After the capture device descends to the descent position, the winch pulls the landing gear onto the deck by retracting the rope.

[0022] The beneficial effect of the above technical solution is that the setting of the winch makes it easy to tension the rope to pull the helicopter.

[0023] Furthermore, the moving parts are curved.

[0024] The beneficial effect of the above technical solution is that the arc-shaped moving parts are easy to form a closed loop after docking.

[0025] Furthermore, the frame has an arc-shaped cavity, and the movable part is an arc-shaped rod inserted into the arc-shaped cavity. A piston is also provided at the end of the arc-shaped rod. The piston divides the arc-shaped cavity into a rod-type cavity and a rodless cavity. The frame is provided with openings that connect the rod-type cavity and the rodless cavity and respectively supply pressure medium to the rod-type cavity and the rodless cavity or discharge pressure medium to allow the arc-shaped rod to extend and retract relative to the frame.

[0026] The advantages of the above technical solution are: it facilitates the extension and retraction of the arc-shaped rod, and the extension and retraction of the arc-shaped rod has little impact on the surrounding components during the movement; in addition, the arc-shaped cavity and the arc-shaped rod facilitate the rapid response of the arc-shaped rod, making it easier to capture the helicopter in a short time. Attached Figure Description

[0027] Figure 1 This is a schematic diagram of the structure of Embodiment 1 of the helicopter landing assistance system in this invention (located below the deck and not capturing the helicopter).

[0028] Figure 2 This is a schematic diagram of the structure of Embodiment 1 of the helicopter landing assistance system in this invention (located above the deck, capturing the helicopter);

[0029] Figure 3 This is a schematic diagram of the structure of Embodiment 1 of the helicopter landing assistance system in this invention (located below the deck and having completed the capture of the helicopter);

[0030] Figure 4 This is a schematic diagram of the structure of Embodiment 1 of the helicopter landing assistance system in this invention (with a helicopter attached, which is currently above the deck and being captured).

[0031] Figure 5 This is a schematic diagram of the locking release device and locking pin cooperation in Embodiment 1 of the helicopter landing assistance system of the present invention.

[0032] In the diagram: 1. Lifting device; 2. Winch; 31. Frame; 32. Arc rod; 4. Locking release device; 41. Housing; 42. Electromagnetic coil; 43. Locking tongue; 44. Spring; 45. Limiting hole; 46. Second guide surface; 5. Locking pin; 51. Snap-fit ​​groove; 52. Second guide surface; 6. Rope; 7. Helicopter; 71. Landing gear; 8. Deck. Detailed Implementation

[0033] The features and performance of the present invention will be further described in detail below with reference to embodiments.

[0034] In Embodiment 1 of the helicopter landing assistance system of this invention:

[0035] In this embodiment, a lifting device is installed below the deck of the ship. The lifting device can be raised and lowered relative to the deck. A capture device is installed above the lifting device to capture the landing gear of the helicopter. The capture device includes two relatively movable arc-shaped rods. During the docking process, a locking pin with a rope is used to transfer the ends of the two arc-shaped rods, thereby enabling the rope to capture the landing gear of the helicopter. Finally, the landing gear of the helicopter is pulled by the rope, thereby completing the landing assistance of the helicopter.

[0036] like Figure 1As shown, a lifting device 1 is installed on the ship. The bottom of the lifting device 1 is located below the deck 8 of the ship, and a lifting platform is provided at the upper end of the lifting device 1. A capture device for capturing the landing gear 71 of the helicopter 7 is provided on the platform. The capture device can be located below the deck 8 after the lifting device 1 is lowered. The lifting device 1 has a capture station for controlling the capture device to rise above the deck 8 and capture the landing gear 71 of the helicopter 7, and a descent station for lowering below the deck. The descent station can save space in its normal storage state, and at the same time, it can provide an installation point for the final fixation of the helicopter 7 during the capture process.

[0037] The capturing device includes a frame 31 fixedly mounted on a lifting platform and a movable component. The movable component passes through the frame 31, which has an arc-shaped structure and contains an arc-shaped cavity. The movable component is an arc-shaped rod 32 inserted into the arc-shaped cavity and movably engaged with the frame 31, slidingly engaging with the arc-shaped cavity. A piston is provided at the end of the arc-shaped rod 32, dividing the arc-shaped cavity into two chambers. One chamber contains the arc-shaped rod 32 and is designated as the rod-side chamber, while the other is designated as the rodless chamber. The frame 31 also has an opening connecting the rod-side chamber and the rodless chamber, supplying pressure medium to both chambers to cause the arc-shaped rod 32 to extend and retract relative to the frame 31. When pressure medium is supplied to the rod-side chamber and simultaneously discharged from the rodless chamber, the arc-shaped rod retracts; conversely, when pressure medium is supplied to the rodless chamber and simultaneously discharged from the rod-side chamber, the arc-shaped rod extends. The aforementioned movable parts and frame 31 are configured in the same way as the cylinder, except that the straight rod of the cylinder is replaced with an arc-shaped rod 32, and the cylindrical cavity of the cylinder body is configured as an arc-shaped cavity. The frame 31 then constitutes the drive structure for driving the arc-shaped rod 32.

[0038] Two frames 31 and two arc-shaped rods 32 are provided. The two frames 31 are arranged at intervals in front and behind on the lifting platform. The two arc-shaped rods 32 are arranged one-to-one with the two frames 31, and the two arc-shaped rods 32 are arranged symmetrically. After the two arc-shaped rods 32 extend at the same time, the ends of the two arc-shaped rods 32 approach each other. One end of the two arc-shaped rods 32 respectively cooperates with the frame 31, and the other end has a docking position that is close to the docking and a position that is far away from each other under the action of the driving structure. When the other end of the two moving parts is in the docking position, it is used to form a limiting ring that encloses the landing gear 71. The docking end of the two arc-shaped rods 32 is the docking end.

[0039] A locking release device 4 is also provided at the joint ends of the two arc-shaped rods 32. The locking release device 4 includes a housing 41, a locking element installed in the housing 41, and a drive mechanism for driving the locking element. The helicopter landing system also includes a locking pin 5, specifically, as shown in the figure. Figure 5As shown, the locking release device 4 has a housing 41 and a receiving groove on the housing 41 for receiving the locking pin 5. The locking release device 4 includes a locking tongue 43 passing through the housing 41, the axis of the locking tongue 43 being perpendicular to the axis of the receiving groove. An electromagnetic coil 42 is provided on the outer peripheral surface of the locking tongue 43 located inside the housing 41. A spring 44 is provided at the end of the locking tongue 43 away from the receiving groove, and the spring 44 abuts against the locking tongue 43 and the housing 41. In this embodiment, the electromagnetic coil 42 and the spring 44 also constitute a driving mechanism, and the locking tongue 43 constitutes a locking member. Under the action of the driving mechanism, the locking member has a locking position that extends into the receiving groove and cooperates with the locking part to lock the locking pin 5, and a releasing position that disengages from the locking part to release the locking pin 5. A snap-fit ​​groove 51 is provided on the locking pin 5, which constitutes the locking part of the locking member. The snap-fit ​​groove 51 cooperates with the locking tongue 43 to complete the fixing of the locking pin 5 by the locking release device 4. When it is necessary to fix the locking pin 5, under the action of the elastic element, the locking tongue 43 extends out of the receiving groove, thereby causing the locking pin 5 to be locked in the locking release device 4. When the locking pin 5 needs to be released, the electromagnetic coil 42 is energized, so that the locking tongue 43 has the electromagnetic force to overcome the elastic element, thereby causing the locking pin 5 to be released.

[0040] like Figure 5 As shown, there are two locking release devices 4 and only one locking pin 5. A rope 6 is also provided at the end of the locking pin 5. The locking pin 5 is pre-installed on one of the locking release devices 4, which is the pre-installation device. The other of the two locking release devices is the final device. Locking and releasing of the locking pin 5 can be accomplished through the cooperation of the locking tongue 43 and the drive mechanism. When the locking pin 5 is on the pre-installation device, one end of the locking pin 5 is located in the receiving groove of the device, and the locking element of the device is in the locking position. When the two mating ends are in the mating position, the other end of the locking pin 5 is inserted into the receiving groove of the final device, and the locking element on the final device is in the locking position, while the locking element on the pre-installation device is in the release position, thus realizing the transfer of the locking pin 5. During the transfer, the rope 6 also moves and transfers along with the locking pin 5. In other words, the locking pin 5 and the rope 6 can be transferred from the pre-installation device to the final device, thereby changing the capture of the helicopter 7 by the arc rod 32 to the capture of the helicopter 7 by the rope 6. In order to facilitate the guidance of the rope 6 during the transfer process, a limiting hole 45 is provided on the housing 41 of the pre-installation device to facilitate the passage of the rope 6. The limiting hole 45 is connected to the receiving groove. During the movement of the locking pin 5 from the pre-installation device to the final device, the rope 6 still moves in the limiting hole 45, which facilitates the guidance of the rope 6.

[0041] The locking pin 5 has two symmetrically arranged locking grooves 51, spaced apart along the axis of the locking pin. The end of the locking pin 5 has a tapered surface, which gradually increases in size towards the center, facilitating the movement of the locking tongue 43 on the end face of the locking pin 5. These two tapered surfaces constitute the first guide surface. The two locking grooves 51 facilitate the locking pin 5's engagement within the two locking release devices 4, meaning that the locking pin 5 can be switched on the arc-shaped rod 32 through its interaction with the locking release device 4, allowing it to move from one arc-shaped rod 32 to another. Furthermore, the locking tongue 43 also has a second guide surface 52 that engages with the first guide surface, facilitating the locking tongue 43's entry into the receiving groove. Simultaneously, a winch 2 is located at the end of the rope 6 furthest from the locking pin 5, allowing the winch 2 to tighten the rope 6, effectively pulling it taut.

[0042] During use, the helicopter 7 lifting system, such as Figure 1 As shown, at this time, the lifting device 1 is below the deck 8. First, it controls the helicopter 7 to hover. During the hovering process, the position of the helicopter 7 is detected by sensors on the ship, and signals are exchanged with the helicopter 7 to control it to hover to the preset position. After the helicopter 7 hovers in place, the lifting device 1 rises and controls the two arc-shaped rods 32 to move. The two arc-shaped rods 32 move towards each other, causing their mating ends to engage, as shown. Figure 2 and Figure 4 As shown. At this time, the locking pin 5 is simultaneously accommodated in the receiving slots of the pre-device and the final device, and the locking pin 5 is transferred synchronously on the two arc-shaped rods 32. Specifically, at this time, the locking tongue 43 in the pre-device rises to release the locking pin 5, and the locking tongue 43 in the final device descends to lock the locking pin 5. That is to say, after this step, the locking pin 5 is fixed to the final device. Then, the two arc-shaped rods 32 are controlled to retract, and the two arc-shaped rods 32 are respectively in a position away from the work position. The rope 6 is also pulled out. At this time, the rope 6 is attached to the landing gear 71 of the helicopter 7, and the rope 6 captures the landing gear 71 of the helicopter 7. Then, the lifting platform is controlled to descend, so that the lifting device 1 descends below the deck 8. Then, under the action of the winch 2, the rope 6 is continuously tightened. During the tightening process, the helicopter 7 is continuously pulled down until the landing gear 71 of the helicopter 7 is in contact with the deck 8 of the ship, and the landing of the helicopter 7 is completed. Figure 3 As shown.

[0043] In Embodiment 2 of the helicopter landing system of this invention: Regarding the arrangement of the frame and the movable component, this embodiment proposes a new arrangement. Unlike Embodiment 1, in this embodiment, the movable component is arc-shaped and hinged to the frame. The drive structure controls the rotation of the movable component on the frame, thereby allowing the two frames to be joined together. Of course, in other embodiments, the movable component can also be set as an arc-shaped rack, which passes through the frame and is driven by gears to move, so that the ends of the movable component are connected.

[0044] In Embodiment 3 of the helicopter landing system of the present invention: Regarding the arrangement of the frame and moving parts, this embodiment proposes a new arrangement. Unlike Embodiment 1, in this embodiment, the moving part is a telescopic rod of a cylinder, the frame is a vertically arranged support frame, the telescopic rod is arranged perpendicularly to the support frame, and the telescopic rod and the frame can form a limiting ring for capturing the helicopter landing gear.

[0045] In Embodiment 4 of the helicopter landing assistance system of the present invention: Regarding the setup of the helicopter landing assistance system, this embodiment proposes a new arrangement. Unlike Embodiment 1, this embodiment does not include a winch. The rope has a certain length and one end of the rope is fixed in the limiting hole. The other end of the rope moves with the locking pin. When the rope catches the helicopter, the lowering of the lifting device applies tension to the rope, thereby pulling the helicopter to land.

[0046] In Embodiment 5 of the helicopter landing system of the present invention: Regarding the setting of the lifting device, this embodiment proposes a new arrangement. Unlike Embodiment 1, in this embodiment, the lifting device is set above the deck, and a separate parking platform is set above the deck, where the helicopter is finally parked.

[0047] In Embodiment 6 of the helicopter landing system of the present invention: Regarding the setting of the locking release device, this embodiment proposes a new arrangement. Unlike Embodiment 1, the locking release device in this embodiment no longer has a limiting hole for limiting the rope. Since the rope can pass through the landing gear, the landing gear can also be captured.

[0048] In Embodiment 7 of the helicopter landing system of this invention: Regarding the arrangement of the capture device, this embodiment proposes a new arrangement. Unlike Embodiment 1, this embodiment only provides a first guide surface on the locking pin and does not provide a second guide surface. Of course, in other embodiments, only a second guide surface may be provided and the first guide surface may not be provided.

[0049] In Embodiment 8 of the helicopter landing system of the present invention: Regarding the arrangement of the drive mechanism, this embodiment proposes a new arrangement. Unlike Embodiment 1, the drive mechanism in this embodiment no longer uses an electromagnetic coil, but is instead set as a cylinder, hydraulic cylinder or electric push rod.

[0050] In Embodiment 9 of the helicopter landing system of the present invention: Regarding the setting of the locking pin, this embodiment proposes a new arrangement. Unlike Embodiment 1, the locking pin is no longer provided with a snap-fit ​​groove. At least three clamping pieces are provided in the receiving groove of the locking release device. Each clamping piece is close to each other to snap and fix the locking pin. At this time, the locking part of the locking pin is the outer peripheral surface of the locking pin. The entire snap-fit ​​form is similar to a three-jaw chuck.

[0051] In Embodiment 10 of the helicopter landing system of the present invention: Regarding the arrangement of the moving parts, this embodiment proposes a new arrangement. Unlike Embodiment 1, the moving part in this embodiment is an arc-shaped rod and there is only one. There are two locking and releasing devices, one of which is set on the arc-shaped rod and the other is set on the frame. The locking pin is initially set on the locking and releasing device of the arc-shaped rod. By transferring during docking, the rope is pulled so that the rope captures the landing gear of the helicopter.

[0052] In Embodiment 11 of the helicopter landing assistance system of the present invention: Regarding the setup of the helicopter landing assistance system, this embodiment proposes a new arrangement. Unlike Embodiment 1, the helicopter landing assistance system in this embodiment no longer includes locking pins, locking release devices, and ropes. The landing gear of the helicopter is captured by the docking of two arc-shaped rods. Then, the movement of the two arc-shaped rods is driven by the lifting device, and the landing gear of the helicopter is driven by the arc-shaped rods to complete the landing of the helicopter.

[0053] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. The scope of patent protection of the present invention shall be determined by the claims. Similarly, any equivalent structural changes made based on the description and drawings of the present invention shall also be included within the scope of protection of the present invention.

Claims

1. A helicopter landing assistance system, characterized in that: The system includes a lifting device, on which a capture device for capturing the landing gear of a helicopter is installed. The capture device includes a frame and an arc-shaped rod that can move relative to the frame. The frame has an arc-shaped structure and a drive structure for driving the arc-shaped rod. There are two arc-shaped rods, one end of which engages with the frame, and the other end is a docking end. Under the action of the drive structure, the rods have a docking position that is close to the frame and a moving position that is far away from each other. The docking position is used to form a limiting ring with the frame to enclose the landing gear. The capture device also includes a locking pin and a rope connected to the locking pin. The locking pin has locking parts at both ends, and a locking release device is installed at both docking ends. The locking release device includes a housing with a receiving groove, a locking element installed in the housing, and a drive mechanism that drives the locking element to extend into the receiving groove to engage with the locking part to lock or disengage the locking part to release the locking pin. One end of the locking pin is located in the receiving slot of one of the locking release devices and is locked by the locking element. When docking, the other end of the locking pin is inserted into the receiving slot of another locking release device and locked by the locking element of that device, while being released by the locking element of the first device, thus realizing the transfer of the locking pin. After the locking pin is transferred, the two docking ends are moved apart so that the rope attached to the locking pin is wrapped around the outside of the landing gear so that the helicopter can be pulled down by the rope.

2. The helicopter landing assistance system according to claim 1, characterized in that: The locking element is a latch, and the locking part is a snap-fit ​​groove for the latch to be inserted.

3. The helicopter landing assistance system according to claim 2, characterized in that: The drive mechanism includes an electromagnetic coil and an elastic element. The electromagnetic coil is used to control the movement of the latch to the release position after being energized, and the elastic element is used to apply a force to the latch in the direction of the receiving groove.

4. The helicopter landing assistance system according to claim 2, characterized in that: The locking pin has a first guide surface at both ends; the locking tongue has a second guide surface that mates with the first guide surface.

5. The helicopter landing assistance system according to any one of claims 1-4, characterized in that: The locking release device housing where the pre-locking pin is located has a limiting hole that communicates with the receiving groove and allows the rope to pass through.

6. The helicopter landing assistance system according to any one of claims 1-4, characterized in that: The lifting device has a capture station for controlling the capture device to rise above the deck to form a limit ring and capture the landing gear, and a descent station for controlling the capture device to descend below the deck after the locking pin is transferred and the two docking ends move away from the station.

7. The helicopter landing assistance system according to claim 6, characterized in that: The helicopter landing system also includes a winch positioned below the deck. The rope is connected to the drum of the winch. During the process of the lifting device controlling the capture device to descend from the capture position to the descent position, the rope is in a slack state. After the capture device descends to the descent position, the winch pulls the landing gear down to the deck by retracting the rope.

8. The helicopter landing assistance system according to any one of claims 1-4, characterized in that: The frame has an arc-shaped cavity, and an arc-shaped rod is inserted into the arc-shaped cavity. A piston is also provided at the end of the arc-shaped rod. The piston divides the arc-shaped cavity into a rod-type cavity and a rodless cavity. The frame is provided with openings that connect the rod-type cavity and the rodless cavity and respectively supply pressure medium to the rod-type cavity and the rodless cavity or discharge pressure medium to enable the arc-shaped rod to move telescopically relative to the frame.

9. A helicopter landing assistance system, characterized in that: The system includes a lifting device, on which a capture device for capturing the landing gear of a helicopter is installed. The capture device includes a frame and an arc-shaped rod that can move relative to the frame. The frame has an arc-shaped structure and a drive structure for driving the arc-shaped rod. The arc-shaped rod has one end, which, under the action of the drive structure, has a docking position close to the frame and a moving position away from the frame. When docking, it is used to form a limiting ring with the frame to enclose the landing gear. The capture device also includes a locking pin and a rope connected to the locking pin. The locking pin has locking parts at both ends. The end of the arc-shaped rod that docks with the frame is the docking end. Both docking ends are equipped with a locking release device. The locking release device includes a housing with a receiving groove, a locking element installed in the housing, and a drive mechanism that drives the locking element to extend into the receiving groove and cooperate with the locking part to lock or disengage the locking part to release the locking pin. One end of the locking pin is located in the receiving slot of one of the locking release devices and is locked by the locking element. When docking, the other end of the locking pin is inserted into the receiving slot of another locking release device and locked by the locking element of that device, while being released by the locking element of the first device, thus realizing the transfer of the locking pin. After the locking pin is transferred, the two docking ends are moved apart so that the rope attached to the locking pin is wrapped around the outside of the landing gear so that the helicopter can be pulled down by the rope.

10. The helicopter landing assistance system according to claim 9, characterized in that: The locking element is a latch, and the locking part is a snap-fit ​​groove for the latch to be inserted.

11. The helicopter landing assistance system according to claim 10, characterized in that: The drive mechanism includes an electromagnetic coil and an elastic element. The electromagnetic coil is used to control the movement of the latch to the release position after being energized, and the elastic element is used to apply a force to the latch in the direction of the receiving groove.

12. The helicopter landing assistance system according to claim 10, characterized in that: The locking pin has a first guide surface at both ends; the locking tongue has a second guide surface that mates with the first guide surface.

13. The helicopter landing assistance system according to any one of claims 9-12, characterized in that: The locking release device housing where the pre-locking pin is located has a limiting hole that communicates with the receiving groove and allows the rope to pass through.

14. The helicopter landing assistance system according to any one of claims 9-12, characterized in that: The lifting device has a capture station for controlling the capture device to rise above the deck to form a limit ring and capture the landing gear, and a descent station for controlling the capture device to descend below the deck after the locking pin is transferred and the two docking ends move away from the station.

15. The helicopter landing assistance system according to claim 14, characterized in that: The helicopter landing system also includes a winch positioned below the deck. The rope is connected to the drum of the winch. During the process of the lifting device controlling the capture device to descend from the capture position to the descent position, the rope is in a slack state. After the capture device descends to the descent position, the winch pulls the landing gear down to the deck by retracting the rope.

16. The helicopter landing assistance system according to any one of claims 9-12, characterized in that: The frame has an arc-shaped cavity, and an arc-shaped rod is inserted into the arc-shaped cavity. A piston is also provided at the end of the arc-shaped rod. The piston divides the arc-shaped cavity into a rod-type cavity and a rodless cavity. The frame is provided with openings that connect the rod-type cavity and the rodless cavity and respectively supply pressure medium to the rod-type cavity and the rodless cavity or discharge pressure medium to enable the arc-shaped rod to move telescopically relative to the frame.

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