An unmanned helicopter transport shelter and transport vehicle

Abstract

The unmanned helicopter transport shelter provided by the application comprises a shelter body, paddle boxes, lifting units and horizontal moving units. The shelter body comprises a fixed shelter body, two wing doors and driving members for driving the wing doors to open and close. The two paddle boxes are arranged close to the tails of the two main body structures respectively. The two lifting units are arranged to place the two main body structures respectively to drive the main body structures to move vertically. The horizontal moving unit is arranged in the shelter body and detachably connected to the two lifting units to drive the lifting units and the main body structures to simultaneously horizontally enter and exit the shelter body. The two main body structures enter and exit the shelter body from the two wing doors in a 180° symmetrical state. The application also provides a transport vehicle. The application has the effect of improving the problem that the space utilization rate is low and the transportation cost is high in the prior art mode of transporting the unmanned aerial vehicle by one machine, one shelter and one vehicle. Meanwhile, the application has the effect of solving the problems that the cost requirement is high and time-consuming when the unmanned aerial vehicle is loaded and unloaded.

Description

Technical Field

[0001] This invention relates to the field of transportation equipment technology, and in particular to an unmanned helicopter transport container and transport vehicle. Background Technology

[0002] Compared to manned helicopters, unmanned helicopters possess unique flight performance and application value, suitable for both civilian and military use, such as rescue and monitoring in sudden natural disasters and public security incidents, as well as lethal and non-lethal military and police missions. Typically, an unmanned helicopter consists of an unmanned helicopter fuselage and detachable tail, main rotor blades, stabilizer wings, and tail rotor blades. The bottom of the unmanned helicopter is fixedly connected to landing gear for takeoff and landing, and the cross-sectional dimensions of its tail and rotor blades are much smaller than those of the fuselage. In terms of transportation, conventional methods involve one helicopter, one cabin, and one vehicle, resulting in limited space utilization and high transportation costs. Furthermore, loading and unloading unmanned helicopters requires auxiliary mechanical equipment (such as cranes and trolleys) or manual assistance, and the drone's position needs to be adjusted within the cabin. The loading and unloading tools are costly and time-consuming. Summary of the Invention

[0003] In view of the shortcomings of the existing technology, the present invention provides an unmanned helicopter transport container and transport vehicle, which can improve the existing technology of transporting drones by one helicopter, one container and one vehicle, which has low space utilization and high transportation costs. At the same time, the loading and unloading of drones is costly and time-consuming.

[0004] On one hand, according to an embodiment of the present invention, an unmanned helicopter transport container is provided for placing an unmanned aerial vehicle (UAV), the UAV including rotor blades and a main structure having a fuselage, a tail, and landing gear disposed on the belly of the fuselage, the unmanned helicopter transport container comprising:

[0005] The cabin includes a fixed cabin, two opposing wing doors rotatably connected to the fixed cabin at their top ends, and a drive unit for driving the wing doors to open and close.

[0006] There are two propeller boxes, which are located inside the cabin, to hold the propellers of the two drones respectively, and the two propeller boxes are located close to the tail of the two main structures.

[0007] The lifting unit has two units, which are used to hold the two main structures respectively, so as to drive the main structures to move vertically;

[0008] And a horizontal moving unit, which is set inside the cabin, has two units and is detachably connected to the two lifting units to drive the lifting units and the main structure to enter and exit the cabin horizontally at the same time. The two main structures enter and exit the cabin from the two wing doors in a 180° symmetrical state.

[0009] Preferably, the lifting unit includes:

[0010] Two-stage scissor lift platform;

[0011] The landing gear support frame is located on top of the secondary scissor lift platform to support the main structure;

[0012] And a forklift mounting tube, which is installed on the top of the secondary scissor lift platform and is detachably connected to the horizontal moving unit.

[0013] Preferably, the secondary scissor lift platform is provided with multiple pins, and the bottom of the fixed compartment is provided with insertion holes for the pins to be inserted.

[0014] Preferably, the horizontal movement unit includes:

[0015] The sliding rail is located at the bottom of the fixed cabin and extends along the opening direction of the wing door;

[0016] The forklift body is slidably connected to the slide rail;

[0017] The lifting boom is vertically slidably connected to the forklift body;

[0018] The front fork is fixed at one end to the lifting rod and extends towards the opening of the wing door;

[0019] And a moving drive unit, which is set on the forklift body and the drive end is connected to the lifting rod to drive the lifting rod and the front fork to move vertically.

[0020] Preferably, the driving element includes:

[0021] Fixed base, fixed to the fixed cabin body;

[0022] The electric actuator is rotatably connected to the fixed base;

[0023] And a rotating base, which is rotatably connected to the piston end of the electric push rod and fixed to the wing door.

[0024] Preferably, the wing door includes:

[0025] The inclined top plate is rotatably connected to the fixed cabin at one end.

[0026] And the side panels, fixed to the other end of the sloping top plate, to seal the sides of the cabin.

[0027] Preferably, the inclined top plate and the side plate form an obtuse angle, and when the side plate is closed, the inclined top plate tilts downward.

[0028] Preferably, the unmanned helicopter transport container further includes a landing gear fixing unit disposed at the bottom of the fixed cabin body for fixing the landing gear of the unmanned aerial vehicle, the landing gear fixing unit comprising:

[0029] Two fixed plates are provided and spaced apart at the bottom of the fixed cabin, and the landing gear of the UAV is located between the two fixed plates;

[0030] The pin passes through both fixed plates simultaneously.

[0031] And an R-pin, which is inserted into the pin shaft to prevent the pin shaft from detaching from the fixing plate.

[0032] Preferably, the landing gear fixing unit further includes two baffles, and the landing gear of the UAV is placed between the two baffles.

[0033] On the other hand, according to an embodiment of the present invention, a transport vehicle is also provided, which includes an unmanned helicopter transport container and a vehicle body, wherein the unmanned helicopter transport container is disposed on the vehicle body.

[0034] Compared with the prior art, the present invention has at least one of the following beneficial effects:

[0035] 1. By rotating connecting wing doors on both sides of the cabin and setting two propeller boxes to hold the propellers of two UAVs, and by using the lifting unit and the horizontal moving unit in combination, the main structure of the two UAVs can be loaded and unloaded into the cabin from the openings on both sides of the cabin at the same time. With one cabin and two UAVs, the two UAVs can be loaded and unloaded at the same time, which has a faster deployment and retrieval time. This improves the problem of low space utilization and high transportation cost in the existing technology of transporting UAVs by one UAV, one cabin and one vehicle.

[0036] 2. The lifting unit and the horizontal moving unit are detachably connected. When loading the main structure of the UAV onto a vehicle, the lifting unit can be simultaneously retracted into the belly of the UAV, improving the utilization of space. At the same time, when unloading, the lifting unit can be used to quickly unload the UAV without the need for other auxiliary tools, making loading and unloading faster. This improves the problem of high cost and time-consuming loading and unloading of UAV 1 in the existing technology.

[0037] 3. The tail section is not disassembled from the fuselage, allowing for faster deployment and retraction. The drone can be loaded and unloaded directly from the side of the cabin, providing more space and a shorter pushing distance, making loading and unloading more convenient. After being loaded into the cabin, there is no need to adjust its position by rotating it, allowing for quick and easy loading and unloading. Attached Figure Description

[0038] Figure 1 This is a schematic diagram of the first overall structure of Embodiment 1 of the present invention, mainly showing the use of the mobile cabin;

[0039] Figure 2 This is a schematic diagram of the second overall structure of Embodiment 1 of the present invention;

[0040] Figure 3This is a top view of an embodiment of the present invention;

[0041] Figure 4 This is an exploded view of the blade box according to an embodiment of the present invention;

[0042] Figure 5 yes Figure 2 An enlarged structural diagram of section A in the middle, mainly showing the driving components;

[0043] Figure 6 yes Figure 2 Enlarged structural diagram of section B in the middle;

[0044] Figure 7 This is a partial structural diagram of an embodiment of the present invention, mainly showing the structure of the lifting unit and the horizontal moving unit in use;

[0045] Figure 8 Structural diagram of the lifting unit according to an embodiment of the present invention;

[0046] Figure 9 This is a structural diagram of the horizontal moving unit according to an embodiment of the present invention;

[0047] Figure 10 This is a structural diagram of the landing gear fixing unit according to an embodiment of the present invention;

[0048] Figure 11 This is a first usage state diagram of Embodiment 2 of the present invention, showing the lifting unit being pushed onto the belly of the drone;

[0049] Figure 12 This is a second usage state diagram of Embodiment 2 of the present invention, showing the state in which the lifting unit lifts the drone;

[0050] Figure 13 This is a third usage state diagram of Embodiment 2 of the present invention, showing the state in which the lifting unit is retracted and the horizontal moving unit supports the lifting unit;

[0051] Figure 14 This is the fourth usage state diagram of Embodiment 2 of the present invention, showing the state in which the horizontal moving unit moves the drone into the cabin.

[0052] In the above attached figures: 1. Unmanned Aerial Vehicle (UAV); 2. Cabin; 21. Fixed Cabin; 211. Column; 22. Wing Door; 221. Sloping Top Plate; 222. Side Plate; 23. Drive Component; 231. Fixed Base; 232. Electric Push Rod; 233. Rotating Base; 3. Propeller Box; 4. Lifting Unit; 41. Two-Stage Scissor Lifting Platform; 42. Landing Gear Support Frame; 43. Forklift Fixing Pipe; 44. Pin; 5. Horizontal Movement Unit; 51. Slide Rail; 52. Forklift Body; 53. Lifting Rod; 54. Front Fork; 6. Landing Gear Fixing Unit; 61. Fixing Plate; 62. Pin; 63. R-Pin; 64. Baffle; 7. Vehicle Body; 71. Power Supply Box. Detailed Implementation

[0053] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the following description is provided in conjunction with the appendix. Figure 1-14 The present invention will be further described below; the technical solutions in the embodiments of the present invention will be clearly and completely described. Obviously, the described embodiments are some embodiments of the present invention, but not all embodiments.

[0054] In the description of this invention, it should be noted that the terms "upper," "lower," "inner," "outer," "top / bottom," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0055] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installed," "equipped with," "sleeved / connected," "connected," etc., should be interpreted broadly. For example, "connection" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; it can be a connection within two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0056] Example 1

[0057] Reference Figures 1 to 3 On the one hand, Embodiment 1 of the present invention proposes an unmanned helicopter transport container for placing a drone 1. Typically, the drone includes rotor blades and a main structure having a fuselage, a tail, and landing gear located on the belly of the fuselage.

[0058] In Embodiment 1 of the present invention, the unmanned helicopter transport container includes a cabin body 2, two rotor boxes 3, two lifting units 4, and two horizontal moving units 5.

[0059] The cabin 2 includes a fixed cabin 21, two wing doors 22 and multiple drive components 23. The fixed cabin 21 is a box structure made of aluminum alloy profiles welded together. It has horizontal openings on both sides in the width direction and upward openings at both ends in the width direction, and long hinges are provided on both sides of its top.

[0060] Two wing-shaped doors 22 are respectively located at the two horizontal openings of the fixed cabin 21 and are adapted to fit the horizontal openings. The ends of the wing-shaped doors 22 are rotatably connected to the fixed cabin 21 through long hinges, thereby closing the openings of the fixed cabin 21 through the two wing-shaped doors 22. The drive unit 23 is located inside the fixed cabin 21 and is evenly distributed and connected to the two wing-shaped doors 22 to realize the opening and closing action of the two wing-shaped doors 22.

[0061] Two blade boxes 3 are provided, both placed inside the fixed compartment 21, with the two blade boxes 3 respectively placed on the left side floor at the front and the right side floor at the rear of the compartment. Each blade box includes a side-opening box assembly and a cover over the opening of the box assembly. Multiple storage slots are provided inside the box assembly for placing the blades. In this first embodiment, the blade box 3 opens outwards, i.e., towards the horizontal opening of the fixed compartment 21, to facilitate the placement and removal of the blades.

[0062] Two lifting units 4 are used to place the two main structures respectively, so as to drive the main structures to move vertically and realize the movement in the vertical direction.

[0063] Both horizontal moving units 5 are located inside the cabin 2 and are close to the two propeller boxes 3 respectively. The two horizontal moving units 5 are detachably connected to the two lifting units 4 to drive the lifting units 4 and the main structure placed on the lifting units 4 to enter and exit the cabin 2 horizontally at the same time. The two main structures enter and exit the cabin 2 from the two wing openings 22 in a 180° symmetrical state.

[0064] Reference Figures 11 to 14When loading the UAV 1 into the cabin, first activate the drive unit 23 to open the two wing doors 22; then proceed with the loading. During the loading process, first remove the propellers of the two UAVs 1 and install them into the two propeller boxes 3 respectively; then push the two lifting units 4 to the belly of the main structure of the two UAVs 1 respectively, and lift the main structure off the ground using the lifting units 4; then push the lifting units 4 and the main structure they are placed on together to the side of the cabin 2, that is, to the horizontal opening of the fixed cabin 21; lift the main structure again using the lifting units 4, so that the main structure is higher than the bottom of the cabin 2, that is, the landing gear is higher than the bottom of the cabin 2; then, establish the connection between the horizontal moving unit 5 and the lifting unit 4, and retract the lifting unit 4 to lower its overall height until the lowest point of the lifting unit 4 is higher than the bottom of the cabin 2; then, push the main structure of the UAV 1, the lifting unit 4, and the horizontal moving unit 5 together into the cabin 2; finally, lower the lifting unit 4 so that the landing gear of the main structure contacts the bottom of the cabin 2. After loading, the main structures of the two UAVs 1 are 180° symmetrical, and the two propeller boxes 3 are close to the tail of the two main structures respectively.

[0065] When unloading the drone 1, simply follow the reverse procedure as when loading it.

[0066] The above-described loading and unloading method, which involves two drones in one compartment, improves upon the existing technology of transporting drones 1 using a single drone, compartment, and vehicle, which suffers from low space utilization and high transportation costs. It eliminates the need to load and unload the tail of drone 1, allowing for faster deployment and retrieval. Furthermore, drone 1 is loaded and unloaded directly from the side of the compartment 2, providing more space and a shorter pushing distance, making loading and unloading more convenient. Once loaded into the compartment, no position adjustment through rotation or other means is required, ensuring rapid and efficient loading and unloading. In addition, two drones 1 can be loaded and unloaded simultaneously, and the tools used for loading and unloading drone 1 (lifting unit 4 and horizontal movement unit 5) can be loaded and unloaded along with the drones, eliminating the need for additional loading and unloading equipment. This makes loading and unloading faster and addresses the high cost and time-consuming issues associated with loading and unloading drones 1 in existing technologies.

[0067] Reference Figure 2 and Figure 3 In one embodiment of the present invention, a column 211 is vertically arranged in the middle of the fixed cabin 21. The column 211 supports the top and bottom of the fixed cabin 21, improves the structural strength, and forms a partition between the main structures of the two UAVs 1 to prevent collision.

[0068] As one embodiment, the blade box assembly consists of a box body assembly, a box cover assembly, a support frame assembly, a skeleton assembly, vibration damping filler, and locking hinges. The blade box 3 can hold three main blades, one horizontal stabilizer fin, and two tail blades. The blades are positioned at a 6° downward angle, allowing them to be tilted and reducing the probability of them slipping out of the blade box 3. A rubber sleeve is fitted onto the support frame for vibration damping. Except for the space occupied by the blades and the hand access area, the remaining space is filled with EVA (Effective Vapor Absorber) to prevent damage to the blades inside the blade box 3 due to vibration. The overall dimensions of the box are 3000mm × 250mm × 350mm (length × width × height). Of course, the specific dimensions of the blade box 3 can be designed according to actual needs.

[0069] Reference Figure 2 In one embodiment of the present invention, the wing-opening door 22 includes a sloping top plate 221 and a side plate 222. One end of the sloping top plate 221 is rotatably connected to the top side of the fixed cabin 21 via a long hinge to close the upper opening of the fixed cabin 21; and the side plate 222 is fixed to the other end of the sloping top plate 221 to close the side of the cabin 2. Air-tight rubber strips are provided at the joints between the sloping top plate 221 and the side plate 222 and the fixed cabin 21 to enhance the sealing performance of the wing-opening door after it is closed.

[0070] Reference Figure 5 The drive unit 23 includes a fixed base 231, an electric push rod 232, and a rotating base 233. The fixed base 231 is fixed to the fixed cabin 21, and the base of the electric push rod 232 is connected to the fixed base 231. The rotating base 233 is fixed to the inclined top plate 221 of the wing door 22 and is rotatably connected to the piston end of the electric push rod 232.

[0071] When the wing door 22 is opened or closed by the drive component 23, the electric push rod 232 can be activated.

[0072] The inclined top plate 221 and the side plate 222 form an obtuse angle. When the side plate 222 is closed, the inclined top plate 221 tilts downward. Compared with the right angle state, this tilt state makes it easier to pass through the tunnel with the arc-shaped inner wall.

[0073] Reference Figures 6 to 8 In one embodiment of the present invention, the lifting unit 4 includes a two-stage scissor lift platform 41, a landing gear support frame 42, and a forklift mounting tube 43. The two-stage scissor lift platform 41 is a common lifting structure in the prior art and can be purchased from the market; its structure will not be described in detail here. The forklift mounting tube 43 is a tube structure with an opening in the horizontal direction.

[0074] The landing gear support frame 42 is located on the top of the platform of the secondary scissor lift platform 41. It is an upward-opening groove structure to facilitate the placement of the landing gear of the main structure of the UAV 1. The landing gear support frame 42 provides support for the main structure, and the secondary scissor lift platform 41 completes the lifting and lowering of the main structure of the UAV 1.

[0075] Reference Figure 6 , Figure 7 as well as Figure 9 The horizontal moving unit 5 includes a slide rail 51, a forklift body 52, a lifting rod 53, front forks 54, and a moving drive component. The slide rail 51 is located at the bottom of the fixed compartment 21 and extends along the opening direction of the wing door 22. The forklift body 52 is slidably connected to the slide rail 51 via a slider adapted to it; one end of the lifting rod 53 is vertically slidably connected to the forklift body 52; two front forks 54 are horizontally spaced, one end of which is fixed to the lifting rod 53, and the other end extends horizontally towards the opening direction of the wing door 22. The moving drive component, not shown in the figure, is connected to the forklift body 52, and its driving end is connected to the lifting rod 53. Specifically, the moving drive component can be a linear motion structure such as a cylinder, electric cylinder, gear rack, or worm gear, designed to drive the lifting rod and front forks to move vertically simultaneously.

[0076] When establishing the connection between the horizontal moving unit 5 and the lifting unit 4, push the forklift body 52 so that the front fork 54 extends into the forklift fixing tube 43. Then retract the secondary scissor lift platform 41 and move the lifting rod 53 upward until the lowest point of the secondary scissor lift platform 41 is higher than the bottom of the cabin 2. After that, the main structure, lifting unit 4 and horizontal moving unit 5 can be pushed into the cabin 2 together.

[0077] In another embodiment of the present invention, a plurality of pins 44 are provided on the secondary scissor lift platform 41, and a socket for inserting the pins 44 is provided at the bottom of the fixed cabin 21. After the secondary scissor lift platform 41 is lowered and made to fit against the bottom of the cabin 2, the pins 44 are inserted into the socket to form a limit and restrict the displacement of the secondary scissor lift platform 41 in the direction of movement of the slide rail 51.

[0078] Reference Figure 6 , Figure 7 as well as Figure 10 According to another embodiment of the present invention, the unmanned helicopter transport container further includes a landing gear fixing unit 6, which is disposed at the bottom of the fixed container 21. Specifically, the landing gear fixing unit 6 includes a fixing plate 61, a pin 62, and an R-pin 63.

[0079] The fixing plate 61 is L-shaped, and there are two of them. The two fixing plates 61 are fixed to the bottom of the fixing chamber 21 by screws. The pin 62 is T-shaped, with one end being a thin end that passes through both fixing plates 61. The R pin 63 is inserted into the thin end to prevent the pin 62 from detaching from the fixing plate 61.

[0080] When the main structure of the UAV 1 is lowered into the cabin 2, the landing gear of the UAV 1 is located between the two fixed plates 61, and then the pin 62 and R pin 63 are inserted in sequence to further restrict the movement of the UAV 1.

[0081] Furthermore, in this embodiment, the landing gear fixing unit 6 also includes two baffles 64. The landing gear of the UAV 1 is placed between the two baffles 64 to form a limit through the baffles 64, preventing the landing gear and the UAV 1 from moving in another direction.

[0082] Reference Figures 11 to 14 On the other hand, Embodiment 2 of the present invention also proposes a transport vehicle, which includes the unmanned helicopter transport container described in Embodiment 1 above, and also includes a vehicle body 7, wherein the unmanned helicopter transport container is disposed on the vehicle body 7.

[0083] During the loading of drone 1 onto the vehicle:

[0084] a. First, start the electric push rod 232 to open the two wing doors 22;

[0085] b. Then remove the propellers of the two drones 1 and install them into the two propeller boxes 3 respectively.

[0086] c. Then push the secondary scissor lift platform 41 to the belly of the main structure of the UAV 1, so that the landing gear enters the landing gear support frame 42, and start the secondary scissor lift platform 41 to make the main structure of the UAV 1 leave the ground.

[0087] d. Push the lifting unit 4 and the main structure of the UAV together to the side of the cabin 2;

[0088] e. Then, the secondary scissor lift platform 41 continues to lift, so that the drone 1 is raised above the bottom plate of the cabin 2;

[0089] f. The forklift body 52 of the lowering horizontal moving unit 5 causes the front fork 54 to descend simultaneously and slide to the edge of the compartment 2 via the slide rail 51 until the front fork 54 extends into the forklift fixing tube 43.

[0090] g. The lifting forklift body 52 makes the landing gear of the UAV 1 slightly higher than the cabin floor;

[0091] h. Retract the secondary scissor lift platform 41 until the rollers at the bottom of the platform are slightly higher than the bottom plate of the cabin 2;

[0092] i. Push the main structure of the drone 1, the lifting unit 4, and the horizontal moving unit 5 into the cabin 2 together.

[0093] j. Lower the forklift body 52 so that the landing gear of the drone 1 enters between the two fixed plates 61 and fits against the base plate;

[0094] k. Finally, insert the pin 44, the pin shaft 62, and the R pin to complete the installation.

[0095] In the second embodiment of the present invention, a power supply box 71 is provided on the vehicle body 7 so that it can be installed in the power supply vehicle for easy use.

[0096] Furthermore, a folding ladder is installed at the rear of cabin 2. This ladder is foldable and features non-slip steps. When in use, the folding ladder can be unfolded to facilitate personnel access to the top for work; when transported, the ladder can be folded up to ensure that the vehicle's passability is not affected.

[0097] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit it. Although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can be made to the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention, and all such modifications or substitutions should be covered within the scope of the claims of the present invention.

Claims

1. An unmanned helicopter transport container for housing a drone (1), the drone (1) comprising rotor blades and a main structure having a fuselage, a tail, and landing gear disposed on the belly of the fuselage, characterized in that, The unmanned helicopter transport container includes: The cabin (2) includes a fixed cabin (21), two opposing wing doors (22) rotatably connected to the fixed cabin (21) at their top ends, and a drive unit (23) for driving the wing doors (22) to open and close. The blade box (3) is located inside the cabin (2) and there are two of them, so as to place the blades of the two drones (1) respectively, and the two blade boxes (3) are respectively close to the tail of the two main structures. Two lifting units (4) are provided to hold the two main structures respectively, so as to drive the main structures to move vertically; And a horizontal moving unit (5) is provided inside the cabin (2). There are two of them and they are detachably connected to the two lifting units (4) to drive the lifting units (4) and the main structure to enter and exit the cabin (2) horizontally at the same time. The two main structures enter and exit the cabin (2) from the two wing opening doors (22) in a 180° symmetrical state. The lifting unit (4) includes: Two-stage scissor lift platform (41); The landing gear support frame (42) is installed on top of the secondary scissor lift platform (41) to support the main structure; And a forklift mounting tube (43) is installed on the top of the secondary scissor lift platform (41) and is detachably connected to the horizontal moving unit (5); The horizontal movement unit (5) includes: The slide rail (51) is located at the bottom of the fixed cabin (21) and extends along the opening direction of the wing door (22); The forklift body (52) is slidably connected to the slide rail (51); The lifting arm (53) is vertically slidably connected to the forklift body (52); The front fork (54) is fixed at one end to the lifting rod (53) and extends towards the opening of the wing door (22); And a moving drive unit, which is set on the forklift body (52) and the drive end is connected to the lifting rod (53) to drive the lifting rod (53) and the front fork (54) to move vertically.

2. The unmanned helicopter transport container according to claim 1, characterized in that, The secondary scissor lift platform (41) is provided with multiple pins (44), and the bottom of the fixed cabin (21) is provided with a socket for the pins (44) to be inserted.

3. The unmanned helicopter transport container according to claim 1, characterized in that, The driving element (23) includes: The fixed seat (231) is fixed to the fixed cabin (21); An electric actuator (232) is rotatably connected to a fixed base (231); And a rotating seat (233), which is rotatably connected to the piston end of the electric push rod (232) and fixed to the wing door (22).

4. The unmanned helicopter transport container according to claim 1, characterized in that, The wing door (22) includes: The inclined top plate (221) is rotatably connected to the fixed cabin (21) at one end. And a side plate (222), fixed to the other end of the inclined top plate (221), to enclose the side of the cabin (2).

5. The unmanned helicopter transport container according to claim 4, characterized in that, The inclined top plate (221) and the side plate (222) form an obtuse angle, and when the side plate (222) is closed, the inclined top plate (221) tilts downward.

6. An unmanned helicopter transport container according to any one of claims 1-5, characterized in that, The unmanned helicopter transport container also includes a landing gear fixing unit (6) located at the bottom of the fixed cabin (21) for fixing the landing gear of the unmanned aerial vehicle (1). The landing gear fixing unit (6) includes: Two fixed plates (61) are provided and spaced apart at the bottom of the fixed cabin (21), and the landing gear of the UAV (1) is located between the two fixed plates (61); The pin (62) is simultaneously inserted into both fixed plates (61); And R pin (63), which is inserted through pin (62) to prevent pin (62) from detaching from fixing plate (61).

7. The unmanned helicopter transport container according to claim 6, characterized in that, The landing gear fixing unit (6) also includes two baffles (64), and the landing gear of the UAV (1) is placed between the two baffles (64).

8. A transport vehicle, characterized in that, Includes the unmanned helicopter transport container and vehicle body (7) as described in any one of claims 1-7, wherein the unmanned helicopter transport container is disposed on the vehicle body (7).

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