Aircraft

Abstract

The utility model discloses an aircraft. The aircraft comprises a chassis; the flight cabin body is suitable for being arranged on the chassis, and a locking part is arranged at the bottom of the flight cabin body; the locking device is movably arranged on the base plate in the vertical direction, and when the locking device is in a locking state, at least part of the locking device is located above the base plate and matched with the locking part. According to the aircraft, the flight cabin is suitable for being arranged on the chassis, the locking part is arranged at the bottom of the flight cabin, the locking device is movably arranged on the chassis in the vertical direction, and when the locking device is in the locking state, at least part of the locking device is located above the chassis and matched with the locking part; the flight cabin and the chassis can be connected, reliable connection of the flight cabin and the chassis is ensured, the problems of structural damage and the like caused by collision between the flight cabin and the locking device when the flight cabin falls on the chassis can be avoided, the landing safety is ensured, and the service life is prolonged.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft, and more specifically, to an aircraft. Background Art

[0002] In the related art, the flight cabin and the chassis of the aircraft adopt a separation and combination mode to meet different driving requirements. However, when the flight cabin is combined with the chassis, the connection between the flight cabin and the chassis is unreliable, affecting the user experience. Summary of the Utility Model

[0003] The utility model aims to solve at least one of the technical problems existing in the prior art. For this purpose, an object of the utility model is to provide an aircraft, which can ensure reliable connection between the flight cabin and the chassis, guarantee landing safety, and is conducive to extending the service life.

[0004] The aircraft according to an embodiment of the utility model includes: a chassis; a flight cabin, which is adapted to be arranged on the chassis, and a locking part is arranged at the bottom of the flight cabin; a locking device, which is movably arranged on the chassis in the up and down direction, and when the locking device is in the locking state, at least part of the locking device is located above the chassis and cooperates with the locking part.

[0005] The aircraft according to an embodiment of the utility model, by arranging the flight cabin to be adapted to be on the chassis, arranging a locking part at the bottom of the flight cabin, arranging the locking device to be movably arranged on the chassis in the up and down direction, and when the locking device is in the locking state, at least part of the locking device is located above the chassis and cooperates with the locking part, can realize the connection between the flight cabin and the chassis, ensure reliable connection between the flight cabin and the chassis, and can avoid problems such as structural damage caused by the collision between the flight cabin and the locking device when the flight cabin lands on the chassis, ensure landing safety, and is conducive to extending the service life.

[0006] In addition, the aircraft according to the above embodiment of the utility model may also have the following additional technical features:

[0007] According to some embodiments of the utility model, the locking device includes: a claw; a first driving mechanism, which is arranged on the chassis, and the first driving mechanism is connected to the claw to drive the claw to be clamped with the locking part.

[0008] According to some embodiments of the present utility model, a sliding hole is provided on the claw. In the length direction of the claw, the sliding hole extends obliquely toward one side in the width direction of the claw. The first driving mechanism includes: a housing, which is connected to the chassis and has an installation groove; a moving member, which is movably arranged in the installation groove in the up-and-down direction. The claws are multiple and arranged at intervals in the circumferential direction of the moving member. One end of the length direction of the multiple claws close to the bottom wall of the installation groove is rotatably connected to the moving member; a fixed shaft, which is fixedly arranged in the installation groove and passes through the sliding hole, and the fixed shaft is movable relative to the length direction of the sliding hole.

[0009] According to some embodiments of the present utility model, the first driving mechanism further includes: a motor, which has an output shaft; a lead screw, which extends in the up-and-down direction and is connected to the output shaft. A part of the lead screw passes through the installation groove, and the moving member is sleeved on the lead screw and is driven to move by the lead screw.

[0010] According to some embodiments of the present utility model, a guiding groove extending in the up-and-down direction is provided on the groove wall of the installation groove, and a guiding protrusion cooperating with the guiding groove is provided on the outer peripheral wall of the moving member; and / or, a drainage hole communicating with the installation groove is provided on the outer peripheral wall of the housing.

[0011] According to some embodiments of the present utility model, the locking portion has a flanging, and the claw is adapted to abut against the upper end of the flanging.

[0012] According to some embodiments of the present utility model, a mating groove is provided on the lower end surface of the locking portion, and a mating protrusion cooperating with the mating groove is provided on the upper end surface of the locking device.

[0013] According to some embodiments of the present utility model, in the up-and-down direction, the groove wall of the mating groove close to the central axis of the locking portion extends obliquely toward the direction close to the central axis of the locking portion. In the up-and-down direction, the groove wall of the mating protrusion close to the central axis of the locking portion extends obliquely toward the direction close to the central axis of the locking portion, and the groove wall of the mating groove close to the central axis of the locking portion abuts against the side wall of the mating protrusion close to the central axis of the locking device; and / or, in the up-and-down direction, the groove wall of the mating groove away from the central axis of the locking portion extends obliquely toward the direction away from the central axis of the locking portion.

[0014] According to some embodiments of the present utility model, the aircraft further includes: a lifting device, which is arranged on the chassis, the locking device is arranged on the lifting device, and the lifting device is used to drive the locking device to move in the up-and-down direction.

[0015] According to some embodiments of the present utility model, the lifting device includes: a base plate, a plurality of the base plates are spaced apart on the chassis, and each of the base plates is provided with the locking device, the locking device penetrates through the base plate, and the locking parts are a plurality corresponding to the locking devices one by one; a second driving mechanism, the second driving mechanism is connected to the chassis for driving the base plate to move in the up and down direction; a guide rail assembly, the guide rail assembly includes a guide rail body and a slider movable on the guide rail body, the guide rail body is connected to the chassis and extends in the up and down direction, and the slider is connected to the base plate.

[0016] According to some embodiments of the present utility model, the second driving mechanism is a plurality corresponding to the base plates one by one; or, the second driving mechanism is a plurality, at least some of the second driving mechanisms drive at least two of the base plates, and the plurality of base plates connected to the same second driving mechanism are connected by a connecting member; or, the second driving mechanism is one, and the second driving mechanism is used for driving a plurality of the base plates to move in the up and down direction.

[0017] According to some embodiments of the present utility model, the flight cabin body includes: a cabin body; a landing gear assembly, the landing gear assembly is connected to the cabin body, and the locking part is arranged on the landing gear assembly.

[0018] According to some embodiments of the present utility model, the chassis includes: a vehicle frame; a landing platform, the landing platform is arranged above the vehicle frame and connected to the vehicle frame, when the locking device is in a locked state, at least a part of the locking device penetrates through the landing platform to cooperate with the locking part.

[0019] According to some embodiments of the present utility model, a groove is provided on the upper surface of the landing platform, and a part of the landing gear assembly is adapted to be located in the groove.

[0020] According to some embodiments of the present utility model, limit blocks are provided at both ends in the length direction of the groove, and the two limit blocks are respectively adapted to abut against both sides of the landing gear assembly in the length direction of the groove.

[0021] According to some embodiments of the present utility model, an abutting part is further provided on the vehicle frame, the abutting part is rotatably arranged on the vehicle frame, the abutting part is located on at least one side in the width direction of the groove, and one side of the abutting part in the width direction of the groove abuts against the landing gear assembly.

[0022] According to some embodiments of the present utility model, the lower end surface of the locking part is higher than the lowest point of the landing gear assembly, and the distance between the lower end surface of the locking part and the lowest point of the landing gear assembly is 5 mm - 10 mm.

[0023] Additional aspects and advantages of the present utility model will be given in part in the following description, become apparent in part from the following description, or be learned through the practice of the present utility model. Brief Description of the Drawings

[0024] The above and / or additional aspects and advantages of the present utility model will become apparent and be readily understood from the description of the embodiments in conjunction with the following drawings, where:

[0025] Figure 1 is a schematic diagram of a partial structure of an aircraft according to an embodiment of the present utility model, wherein the landing gear assembly is engaged with the chassis;

[0026] Figure 2 is Figure 1 a sectional view taken along the direction shown by line A-A;

[0027] Figure 3 is a schematic diagram of a partial structure of an aircraft according to an embodiment of the present utility model, wherein the landing gear assembly is disengaged from the chassis;

[0028] Figure 4 is a partial enlarged view of an aircraft according to an embodiment of the present utility model;

[0029] Figure 5 is a schematic diagram of the structure of a chassis according to an embodiment of the present utility model;

[0030] Figure 6 is a schematic diagram of the structure of a vehicle frame according to an embodiment of the present utility model;

[0031] Figure 7 is a schematic diagram of the structure of a plurality of substrates in cooperation with a locking device according to some embodiments of the present utility model;

[0032] Figure 8 is a schematic diagram of the structure of a plurality of substrates in cooperation with a locking device according to other embodiments of the present utility model;

[0033] Figure 9 is a schematic diagram of the structure of a locking device in cooperation with a lifting device according to an embodiment of the present utility model;

[0034] Figure 10 is a top view of the locking device in cooperation with the lifting device according to an embodiment of the present utility model;

[0035] Figure 11 is a front view of the locking device in cooperation with the lifting device according to an embodiment of the present utility model;

[0036] Figure 12 is a schematic diagram of the structure of a locking device according to an embodiment of the present utility model;

[0037] Figure 13It is a cross-sectional view of the locking device cooperating with the locking part according to an embodiment of the present utility model, wherein the locking device is in an open state;

[0038] Figure 14 It is a cross-sectional view of the locking device cooperating with the locking part according to an embodiment of the present utility model, wherein the locking device is in a locked state;

[0039] Figure 15 It is a cross-sectional view of the locking device according to an embodiment of the present utility model;

[0040] Figure 16 It is a schematic structural diagram of the housing according to an embodiment of the present utility model;

[0041] Figure 17 It is a schematic structural diagram of the moving part according to an embodiment of the present utility model;

[0042] Figure 18 It is a schematic structural diagram of the jaw according to an embodiment of the present utility model;

[0043] Figure 19 It is a partial structural schematic diagram of the lifting device according to an embodiment of the present utility model;

[0044] Figure 20 It is a schematic structural diagram of the guide rail assembly according to an embodiment of the present utility model;

[0045] Figure 21 It is a schematic structural diagram of the second driving mechanism according to an embodiment of the present utility model;

[0046] Figure 22 It is a schematic structural diagram of the substrate according to an embodiment of the present utility model;

[0047] Figure 23 It is a schematic structural diagram of the abutting part cooperating with the landing gear assembly according to an embodiment of the present utility model;

[0048] Figure 24 It is a schematic structural diagram of the landing platform cooperating with the landing gear assembly according to an embodiment of the present utility model;

[0049] Figure 25 It is a schematic structural diagram of the landing gear assembly according to an embodiment of the present utility model;

[0050] Figure 26 Is Figure 25 A cross-sectional view taken along the direction shown by line B-B;

[0051] Figure 27 It is a schematic structural diagram of the landing gear body according to an embodiment of the present utility model;

[0052] Figure 28It is a schematic structural diagram of a cross beam according to an embodiment of the present utility model;

[0053] Figure 29 It is a schematic structural diagram of a locking part according to an embodiment of the present utility model;

[0054] Figure 30 It is a schematic structural diagram of a landing platform according to an embodiment of the present utility model.

[0055] Reference numerals:

[0056] 100, aircraft;

[0057] 10, chassis; 11, vehicle frame; 12, landing platform; 111, abutting part; 121, groove; 122, limiting block;

[0058] 20, landing gear assembly; 21, locking part; 22, landing gear body; 23, cross beam; 211, flange; 212, mating groove; 221, longitudinal beam; 222, bending part;

[0059] 30, locking device; 31, claw; 32, first driving mechanism; 33, mating protrusion; 311, sliding hole;

[0060] 41, housing; 42, moving part; 43, fixed shaft; 44, fixing part; 45, motor; 46, lead screw; 411, installation groove; 412, guiding groove; 413, drain hole; 422, guiding protrusion; 423, rotating shaft; 451, sealing cover; 452, sealing member;

[0061] 50, lifting device; 51, substrate; 52, second driving mechanism; 53, guide rail assembly; 54, connecting member; 531, guide rail body; 532, slider; 533, limiting part;

[0062] 60, battery pack. Detailed implementation manners

[0063] The embodiments of the present utility model will be described in detail below. Examples of the embodiments are shown in the drawings, where the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the drawings are exemplary and are only used to explain the present utility model and should not be construed as a limitation of the present utility model.

[0064] In the description of the present utility model, it should be understood that the orientation or positional relationship indicated by terms such as "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation to the present utility model.

[0065] In the description of the present utility model, the "first feature" and "second feature" may include one or more of such features. The meaning of "a plurality" is two or more. The first feature being "above" or "below" the second feature may include the first and second features being in direct contact, or may include the first and second features not being in direct contact but being in contact through additional features therebetween. The first feature being "above", "above the top of", and "on the top of" the second feature includes the first feature being directly above and obliquely above the second feature, or merely indicating that the first feature is at a higher horizontal height than the second feature.

[0066] The aircraft 100 according to an embodiment of the present utility model will be described below with reference to the drawings.

[0067] Refer to Figures 1 - 5 As shown, the aircraft 100 according to an embodiment of the present utility model may include: a chassis 10 and a flight cabin.

[0068] Specifically, the flight cabin may be disposed on the chassis 10. Through the separation and combination of the flight cabin and the chassis 10, the aircraft 100 can flexibly adapt to driving scenarios such as ground driving and air flight, meeting different driving requirements. For example, the aircraft 100 has a low-altitude flight mode and can achieve future three-dimensional space traffic.

[0069] In addition, as Figures 1 - 14 , Figure 29 shown, a locking portion 21 is provided at the bottom of the flight cabin. The aircraft 100 further includes a locking device 30. When the locking device 30 is in a locked state, at least a part of the locking device 30 is located above the chassis 10, and the locking device 30 cooperates with the locking portion 21 to enable the connection between the locking device 30 and the locking portion 21, thereby realizing the connection between the flight cabin and the chassis 10, ensuring the reliable connection between the flight cabin and the chassis 10, and being beneficial to improving the user experience. Thus, through the locking device 30 and the locking portion 21, it is convenient to realize the connection and unlocking of the flight cabin and the chassis 10, meeting different usage requirements of the aircraft 100.

[0070] Meanwhile, asFigure 2 As shown in the figure, the locking device 30 is movably arranged on the chassis 10 in the up and down direction. When the flight cabin needs to land, the locking device 30 can be located below the chassis 10. After the flight cabin lands stably, the locking device 30 moves upward and cooperates with the locking part 21, which can avoid problems such as structural damage caused by the collision between the flight cabin and the locking device 30 when the flight cabin lands on the chassis 10, ensure the landing safety, and is beneficial to extending the service life.

[0071] In some embodiments, the locking device 30 is made of aluminum alloy, which can reduce the weight of the locking device 30, facilitate the lightweight of the chassis 10, has good corrosion resistance, is beneficial to extending the service life, and is convenient for processing and manufacturing.

[0072] According to the aircraft 100 of the embodiment of the present invention, the flight cabin is suitably arranged on the chassis 10, and the bottom of the flight cabin is provided with a locking part 21. The locking device 30 is movably arranged on the chassis 10 in the up and down direction. When the locking device 30 is in the locked state, at least part of the locking device 30 is located above the chassis 10 and cooperates with the locking part 21, which can realize the connection between the flight cabin and the chassis 10, ensure the reliable connection between the flight cabin and the chassis 10, and can avoid problems such as structural damage caused by the collision between the flight cabin and the locking device 30 when the flight cabin lands on the chassis 10, ensure the landing safety, and is beneficial to extending the service life.

[0073] In some embodiments of the present invention, such as Figures 12 - 14 , Figure 18 As shown in the figure, the locking device 30 includes a claw 31 and a first driving mechanism 32. The first driving mechanism 32 is arranged on the chassis 10, which can realize the fixation of the first driving mechanism 32, and the first driving mechanism 32 is connected with the claw 31, so that the first driving mechanism 32 can drive the claw 31 to be clamped with the locking part 21, thereby realizing the cooperation between the locking device 30 and the locking part 21, ensuring the reliable connection between the locking device 30 and the locking part 21, ensuring high connection stiffness, avoiding problems such as connection loosening, and can realize the repeated automatic docking and unlocking between the flight cabin and the chassis 10, which is beneficial to improving the docking efficiency and has high reliability.

[0074] At the same time, by clamping the claw 31 with the locking part 21, it can avoid the problem of easy tooth slipping of the bolt when connecting the flight cabin and the chassis by bolts in the related technology, and avoid the problem of bolt connection loosening under alternating loads, ensure the reliable connection between the flight cabin and the chassis 10, solve the problem that the connection between the flight cabin and the chassis 10 cannot be reused repeatedly, can reduce the number of disassembly and replacement times, facilitate the quick and effective docking between the flight cabin and the chassis 10, and can reduce the damage rate, thereby reducing the use cost.

[0075] According to some embodiments of the present invention, such asFigures 12 - 14 As shown in the figure, the first driving mechanism 32 includes a housing 41, a moving member 42 and a fixed shaft 43. The housing 41 is connected to the chassis 10, which can meet the connection requirement between the first driving mechanism 32 and the chassis 10. The housing 41 has an installation groove 411. The moving member 42 is movably arranged in the installation groove 411 in the up and down direction. The fixed shaft 43 is fixedly arranged in the installation groove 411. The housing 41 can protect the moving member 42 and the fixed shaft 43, avoiding damage caused by the exposure of the moving member 42 and the fixed shaft 43, which is beneficial to extending the service life.

[0076] In addition, as Figure 13 , Figure 14 and Figure 18 shown, a sliding hole 311 is provided on the claw 31. In the length direction of the claw 31 (for example, the up and down direction shown in Figure 13 ), the sliding hole 311 extends obliquely towards one side in the width direction of the claw 31. One end of the claw 31 in the length direction close to the bottom wall of the installation groove 411 (for example, the lower end shown in Figure 13 ) is rotatably connected to the moving member 42, and the fixed shaft 43 passes through the sliding hole 311, and the fixed shaft 43 is movable relative to the length direction of the sliding hole 311. Thus, through the cooperation of the sliding hole 311 and the fixed shaft 43, the claw 31 can move along a specific track under the drive of the moving member 42, which is convenient for realizing the opening and locking of the claw 31 and the locking part 21. And through the claw 31 and the moving member 42, the movement stability of the claw 31 can be ensured. At the same time, the composition structure of the first driving mechanism 32 is simple, which is convenient for processing and manufacturing, beneficial to reducing the production cost, and can thus solve the problems of complex connection structure, high cost, unstable connection and high failure rate in the related technology between the flight cabin body and the chassis, making the control simpler.

[0077] In some embodiments of the present utility model, as Figures 12 - 14 shown, the first driving mechanism 32 further includes a motor 45 and a lead screw 46. The motor 45 has an output shaft. The lead screw 46 extends in the up and down direction, and the lead screw 46 is connected to the output shaft, so that the lead screw 46 can be driven to rotate by the output shaft. A part of the lead screw 46 passes through the installation groove 411, and the moving member 42 is sleeved on the lead screw 46, and the moving member 42 can be driven by the lead screw 46 to move.

[0078] When the motor 45 starts to work, the output shaft of the motor 45 starts to rotate, and the output shaft drives the lead screw 46 to rotate. The lead screw 46 can drive the moving member 42 to move, which can meet the moving requirement of the moving member 42 in the up and down direction, making the drive of the moving member 42 reliable and the movement stable. And the structure of the first driving mechanism 32 is simple, which is beneficial to reducing the production cost.

[0079] For example, when the locking state is in the initial state, that is, when the flight cabin body is not located on the chassis 10, asFigure 13 As shown, the moving member 42 is located at the top of the lead screw 46, and the fixed shaft 43 is located at the bottom of the sliding hole 311. At this time, the locking device 30 is in the open state.

[0080] After the flight cabin lands on the chassis 10, the output shaft of the motor 45 drives the lead screw 46 to rotate. Under the action of the screw rotation and rising, the lead screw 46 drives the moving member 42 to move downward. The moving member 42 can pull the claw 31 to move downward accordingly. And under the action of the movement of the fixed shaft 43 in the length direction of the sliding hole 311 relative to the sliding hole 311, the fixed shaft 43 can pull the claw 31 to rotate for attitude adjustment on the moving member 42 until the moving member 42 moves to the bottom of the lead screw 46. At this time, the claw 31 is snap-connected to the locking portion 21, and the locking device 30 is in the Figure 14 locking state as shown.

[0081] When the locking device 30 needs to be opened, the opening method of the locking device 30 is opposite to the above process, which will not be elaborated here.

[0082] In some embodiments, as Figures 12 - 14 shown, the first driving mechanism 32 further includes a fixing member 44. The fixing member 44 is sleeved on one end of the lead screw 46 away from the bottom wall of the mounting groove 411 (for example, Figure 13 the upper end shown in the figure), and the fixing member 44 is connected to the housing 41. The fixed shaft 43 is provided on the fixing member 44, which can meet the requirement of fixedly connecting the fixed shaft 43 to the housing 41, making the structure simple, reducing the processing complexity of the housing 41, and being beneficial to reducing the production cost.

[0083] In some embodiments, as Figure 13 shown in Figure 14 and

[0084] shown, the moving member 42 has a rotating shaft 423. The rotating shaft 423 passes through the claw 31, and the claw 31 can rotate relative to the rotating shaft 423, thereby realizing the rotational connection between the claw 31 and the moving member 42. The structure is simple and convenient for processing and manufacturing. Figure 13 shown in Figure 14 and

[0085] In some embodiments of the present invention, as Figures 12 - 14As shown, there are multiple jaws 31. The multiple jaws 31 are arranged at intervals in the circumferential direction of the moving member 42. One end of the multiple jaws 31 in the length direction, which is close to the bottom wall of the mounting groove 411, is rotatably connected to the moving member 42. By engaging the multiple jaws 31 with the engaging portion, it is beneficial to improve the firmness and stability of the locking, and ensure the connection reliability between the flight cabin and the locking device 30.

[0086] In an embodiment of the present invention, the number of the jaws 31 can be flexibly set according to the actual situation. For example, the jaws 31 can be Figure 12 as shown in three, or can be two, four, five, six or more, which are all within the protection scope of the present invention.

[0087] In some embodiments of the present invention, as Figures 15 - 17 shown, a guiding groove 412 is provided on the groove wall of the mounting groove 411. The guiding groove 412 extends in the up and down direction. A guiding protrusion 422 is provided on the outer peripheral wall of the moving member 42. The guiding protrusion 422 cooperates with the guiding groove 412. Thus, the guiding groove 412 can guide the guiding protrusion 422, ensure the reliable movement of the moving member 42 in the up and down direction, avoid problems such as the deviation of the movement of the moving member 42, ensure the linear movement of the moving member 42 in the housing 41, and thus ensure the reliable engagement between the jaws 31 and the engaging portion.

[0088] In some embodiments, as Figures 15 - 17 shown, there are multiple guiding grooves 412. The multiple guiding grooves 412 are arranged at intervals in the circumferential direction of the mounting groove 411. The guiding protrusions 422 are multiple and correspond to the multiple guiding grooves 412 one by one. By the cooperation of the multiple guiding protrusions 422 and the multiple guiding grooves 412, it can be ensured that the moving member 42 is uniformly stressed, ensure the reliable movement of the moving member 42 in the mounting groove 411, avoid problems such as the skew of the movement of the moving member 42 and avoid damage, etc., which is beneficial to extend the service life.

[0089] In an embodiment of the present invention, the number of the guiding grooves 412 can be flexibly set according to the actual situation. For example, the guiding grooves 412 can be Figure 16 as shown in three, or can be two, four, five, six or more, which are all within the protection scope of the present invention.

[0090] According to some embodiments of the present invention, as Figure 15 and Figure 16As shown, a drain hole 413 is provided on the outer peripheral wall of the housing 41. The drain hole 413 is communicated with the installation groove 411, which can enable liquids such as rainwater entering the installation groove 411 to flow out through the drain hole 413, avoiding problems such as corrosion of the first driving mechanism 32 caused by accumulation in the installation groove 411, being beneficial to improving the overall durability and reliability, and being able to extend the service life of the locking device 30.

[0091] In some embodiments, as Figure 16 shown, there can be multiple (greater than or equal to two) drain holes 413. The multiple drain holes 413 are arranged at intervals in the circumferential direction of the housing 41. Through the multiple drain holes 413, the drainage effect of the liquid in the installation groove 411 can be good, reducing the accumulation time of the liquid in the installation groove 411, which is beneficial to extending the service life.

[0092] In some embodiments of the present utility model, as Figure 13 shown in Figure 14 connection, the locking part 21 has a flanging 211, and the claw 31 can abut against the upper end of the flanging 211, which can realize the clamping connection between the claw 31 and the locking part 21, ensuring the reliable connection between the flight cabin body and the chassis 10, and the matching structure is simple, which is convenient for reducing the production cost.

[0093] According to some embodiments of the present utility model, as Figure 13 shown in Figure 14 connection, a mating groove 212 is provided on the lower end surface of the locking part 21, and a mating protrusion 33 is provided on the upper end surface of the locking device 30. The mating protrusion 33 cooperates with the mating groove 212. Thus, through the cooperation of the mating protrusion 33 and the mating groove 212, the automatic alignment of the locking part 21 can be realized, without the need for active attitude adjustment, and the docking deviation can be automatically absorbed, avoiding problems such as skewing when the flight cabin lands and affecting subsequent cooperation, solving the deviation problem of the automatic docking between the flight cabin body and the chassis 10 when the flight cabin lands, ensuring reliable positioning, and thus ensuring the reliable cooperation between the claw 31 and the locking part 21.

[0094] In some embodiments, as Figure 13 shown in Figure 14 connection, in the up-and-down direction, the groove wall of the mating groove 212 on the side away from the central axis of the locking part 21 extends obliquely in the direction away from the central axis of the locking part 21. When the mating protrusion 33 cooperates with the mating groove 212, the groove wall of the mating groove 212 on the side away from the central axis of the locking part 21 can move relative to the mating protrusion 33, so that the mating groove 212 can be guided on the mating protrusion 33, which is convenient for realizing the automatic alignment of the locking part 21, and the structure is simple, which is convenient for processing and manufacturing.

[0095] In some embodiments, as Figure 13 shown in Figure 14As shown, in the vertical direction, the side wall of the mating groove 212 closer to the central axis of the locking portion 21 extends obliquely towards the direction closer to the central axis of the locking portion 21. In the vertical direction, the side wall of the mating projection 33 closer to the central axis of the locking device 30 extends obliquely towards the direction closer to the central axis of the locking device 30. The side wall of the mating groove 212 closer to the central axis of the locking portion 21 abuts against the side wall of the mating projection 33 closer to the central axis of the locking device 30, which can ensure reliable mating between the mating projection 33 and the mating groove 212, improve the structural strength of the mating projection 33, avoid problems such as deformation, and thus extend the service life of the locking device 30.

[0096] In some embodiments, such as Figure 13 and Figure 14 As shown, in the vertical direction, the side wall of the mating groove 212 farther from the central axis of the locking portion 21 extends obliquely away from the central axis of the locking portion 21, and the side wall of the mating groove 212 closer to the central axis of the locking portion 21 extends obliquely towards the direction closer to the central axis of the locking portion 21, that is, the mating groove 212 can be generally formed in a flared shape. In the vertical direction, the side wall of the mating projection 33 closer to the central axis of the locking device 30 extends obliquely towards the direction closer to the central axis of the locking device 30, so that the side wall of the mating groove 212 closer to the central axis of the locking portion 21 abuts against the side wall of the mating projection 33 closer to the central axis of the locking device 30, ensuring reliable mating between the mating projection 33 and the mating groove 212, and facilitating the movement of the side wall of the mating groove 212 farther from the central axis of the locking portion 21 relative to the mating projection 33, enabling the mating groove 212 to be guided on the mating projection 33 and facilitating the automatic alignment of the locking portion 21.

[0097] In some embodiments of the present invention, such as Figures 7 - 11 As shown, the aircraft 100 further includes a lifting device 50. The lifting device 50 is provided on the chassis 10, and the locking device 30 is provided on the lifting device 50. The lifting device 50 can drive the locking device 30 to move in the vertical direction, thereby realizing the movement of the locking device 30 in the vertical direction and ensuring more reliable movement of the locking device 30.

[0098] According to some embodiments of the present invention, such as Figures 7 - 11 and Figure 21As shown, the lifting device 50 includes a base plate 51 and a second driving mechanism 52. The locking device 30 is inserted through the base plate 51, enabling the connection between the locking device 30 and the lifting device 50. The second driving mechanism 52 is connected to the chassis 10, allowing the second driving mechanism 52 to drive the base plate 51 to move in the up and down direction. Thus, the base plate 51 can drive the locking device 30 to move in the up and down direction to meet the required movement needs, enabling automatic control, making the control more convenient, and the structure of the lifting device 50 is simple, facilitating processing and manufacturing, and conducive to reducing production costs. For example, the second driving mechanism 52 can be an electric push cylinder.

[0099] In some embodiments, the second driving mechanism 52 and the chassis 10 are connected by fasteners or welded, both of which can ensure reliable connection between the second driving mechanism 52 and the chassis 10 to meet the required connection needs.

[0100] In some embodiments of the present utility model, such as Figures 9 - 11 、 Figure 19 and Figure 20 As shown, the lifting device 50 further includes a guide rail assembly 53. The guide rail assembly 53 includes a guide rail body 531 and a slider 532. The slider 532 is movable on the guide rail body 531. The guide rail body 531 is connected to the chassis 10 to fix the guide rail body 531, and the guide rail body 531 extends in the up and down direction. The slider 532 is connected to the base plate 51. Thus, when the second driving mechanism 52 drives the base plate 51 to move up and down, the base plate 51 can drive the slider 532 to move on the guide rail body 531, enabling the guide rail body 531 to guide the movement of the base plate 51, avoiding deviation of the movement of the base plate 51, and ensuring the smooth operation of the base plate 51.

[0101] In some embodiments, the guide rail body 531 and the chassis 10 are connected by fasteners or welded, both of which can ensure reliable connection between the guide rail body 531 and the chassis 10 to meet the required connection needs.

[0102] In some embodiments, such as Figure 11 、 Figure 19 and Figure 20 As shown, the upper end of the guide rail body 531 has a limiting portion 533. The slider 532 is located below the guiding body. The limiting portion 533 can achieve safety limiting of the slider 532 to prevent the slider 532 from disengaging from the guiding body during the rising process, ensuring the working reliability of the lifting device 50.

[0103] In some embodiments, such as Figure 19As shown, the distance that the slider 532 moves upward from the bottom of the guide rail body 531 is 25 mm - 30 mm, that is, the distance that the slider 532 moves upward from the bottom of the guide rail body 531 is H1 and satisfies 25 mm ≤ H1 ≤ 30 mm. Within the above range, while meeting the requirement of the moving distance of the substrate 51, the movement of the slider 532 can be limited, preventing the slider 532 from disengaging from the guide rail body 531, and ensuring the working reliability of the lifting device 50. For example, in some specific embodiments, the distance that the slider 532 moves upward from the bottom of the guide rail body 531 can be 25 mm, 26 mm, 27 mm, 28 mm, 29 mm, 30 mm, etc.

[0104] In some embodiments, as Figures 7 - 10 shown, there can be multiple guide rail assemblies 53, and the multiple guide rail assemblies 53 are spaced in the circumferential direction of the substrate 51. By means of the multiple guide rail assemblies 53, it is convenient to guide multiple different positions of the substrate 51, preventing problems such as skewing of the substrate 51 and ensuring the stable operation of the substrate 51.

[0105] In the embodiments of the present invention, the number of the guide rail assemblies 53 can be flexibly set according to the actual situation. For example, the guide rail assemblies 53 can be as Figure 9 shown, four in number, or can be two, three, five, six or more, and all these are within the protection scope of the present invention.

[0106] According to some embodiments of the present invention, as Figure 7 and Figure 8 shown, there are multiple substrates 51, and the multiple substrates 51 are spaced on the chassis 10. A locking device 30 is provided on each substrate 51, and there are multiple locking parts 21 that correspond one-to-one with the locking devices 30. By cooperating the multiple locking parts 21 with the multiple locking devices 30, it can further ensure the reliable connection between the flight cabin body and the chassis 10, prevent problems such as shaking of the flight cabin body on the chassis 10, ensure the reliable fixation of the flight cabin body, and by means of the substrate 51, it is convenient to control the up and down movement of the locking device 30, and can prevent problems such as structural damage caused by the collision between the flight cabin body and the locking device 30 when the flight cabin body lands on the chassis 10, ensuring the landing safety.

[0107] In the embodiments of the present invention, the number of the substrates 51 can be flexibly set according to the actual situation. For example, the substrates 51 can be as Figure 7 shown, four in number, or can be two, three, five, six or more, and all these are within the protection scope of the present invention.

[0108] In some embodiments, the number and installation positions of the locking devices 30 can be determined according to the overall weight of the flight cabin body, the running speed and the overall strength and durability analysis of the aircraft 100, so as to meet different usage requirements.

[0109] In some embodiments of the present utility model, as Figure 7 shown, there are multiple second driving mechanisms 52 corresponding one by one to the substrates 51, so that each substrate 51 is controlled by an independent second driving mechanism 52, enabling high-precision position adjustment and meeting different usage requirements.

[0110] Alternatively, as Figure 8 shown, the second driving mechanisms 52 are multiple (greater than or equal to two), and at least some of the second driving mechanisms 52 drive at least two substrates 51. The multiple substrates 51 connected to the same second driving mechanism 52 are connected by a connecting member 54. Thus, one second driving mechanism 52 can drive at least two substrates 51 connected by the connecting member 54, which can reduce the number of second driving mechanisms 52, is beneficial to reducing production costs, and makes the structure compact, capable of reducing the occupied space.

[0111] Or, the second driving mechanism 52 is one, and the second driving mechanism 52 can drive multiple substrates 51 to move in the up and down direction, so that a single second driving mechanism 52 can control the movement of all substrates 51, which is beneficial to reducing production costs, and makes the structure simple, easy to maintain and manage.

[0112] According to some embodiments of the present utility model, as Figures 1 - 5 shown, the flight cabin body includes a cabin body main body and a landing gear assembly 20. The landing gear assembly 20 is connected to the cabin body main body, and a locking portion 21 is provided on the landing gear assembly 20. Through the landing gear assembly 20, stable support during the landing of the flight cabin body can be achieved, ensuring the stability and safety of the flight cabin body during landing.

[0113] In some embodiments, by connecting with different cabin body main bodies through the landing gear assembly 20, the matching requirements of different cabin body main bodies and the chassis 10 can be achieved, facilitating the realization of a standardized structure design, enabling structural versatility, and reducing development costs.

[0114] In some embodiments of the present utility model, as Figures 1 - 6 shown, the chassis 10 includes a vehicle frame 11 and a landing platform 12. The landing platform 12 is arranged above the vehicle frame 11 and is connected to the vehicle frame 11. Through the landing platform 12, the support requirement for the flight cabin body can be achieved, ensuring reliable support. When the locking device 30 is in the locked state, at least part of the locking device 30 penetrates through the landing platform 12, so that the locking device 30 can cooperate with the locking portion 21 to realize the connection between the flight cabin body and the chassis 10, ensuring reliable connection between the flight cabin body and the chassis 10, and making the structure of the chassis 10 simple, capable of reducing the structural complexity of the chassis 10, facilitating the processing manufacture and structural assembly of the chassis 10, and being beneficial to reducing production costs.

[0115] In some embodiments, the aircraft 100 further includes a battery pack 60. The battery pack 60 is disposed on the vehicle frame 11, which can fix the battery pack 60. The battery pack 60 can provide necessary power supply for the aircraft 100 to meet the required usage needs.

[0116] In some embodiments, the vehicle frame 11 and the landing platform 12 are connected by fasteners or welded, which can ensure reliable connection between the vehicle frame 11 and the landing platform 12 to meet the required connection needs.

[0117] According to some embodiments of the present invention, as Figure 2 、 Figure 5 and Figure 30 shown, a groove 121 is provided on the upper surface of the landing platform 12. A part of the landing gear assembly 20 can be located in the groove 121. The groove 121 can provide a placement position for the landing gear assembly 20, and can roughly position the landing gear assembly 20 through the groove 121, which can correct the docking attitude between the flight cabin and the chassis 10, solve the deviation problem of automatic docking between the flight cabin and the chassis 10 during landing, and ensure smoother and more reliable cooperation between the subsequent locking device 30 and the locking portion 21.

[0118] In some embodiments, as Figure 5 and Figure 30 shown, there are multiple grooves 121. The multiple grooves 121 are spaced in the width direction of the landing platform 12 (for example, the left - right direction shown in Figure 30 ). The multiple grooves 121 can position multiple different positions of the landing gear, further ensuring accurate positioning of the flight cabin on the chassis 10.

[0119] In the embodiments of the present invention, the number of the grooves 121 can be flexibly set according to actual situations. For example, the grooves 121 can be two as Figure 30 shown, or three, four, five, six or more, which are all within the protection scope of the present invention.

[0120] In some embodiments of the present invention, as Figure 4 、 Figure 5 、 Figure 24 and Figure 30 shown, the length direction of the groove 121 (for example Figure 30At both ends in the front - rear direction (as shown) are provided with limiting blocks 122. The two limiting blocks 122 can respectively abut against both sides of the landing gear assembly 20 in the length direction of the groove 121. Through the two limiting blocks 122, rough positioning of the landing gear assembly 20 can be achieved, realizing the correction of the docking attitude between the flight cabin and the chassis 10, solving the deviation problem of the automatic docking between the flight cabin and the chassis 10 during landing, and ensuring that the subsequent locking device 30 and the locking part 21 cooperate more smoothly and reliably.

[0121] According to some embodiments of the present invention, as Figures 3 - 5 , Figure 23 shown, the vehicle frame 11 is further provided with an abutting part 111. The abutting part 111 is rotatably arranged on the vehicle frame 11. The abutting part 111 is located on at least one side in the width direction of the groove 121. One side of the abutting part 111 along the width direction of the groove 121 abuts against the landing gear assembly 20. Thus, through the abutting part 111, the position of the landing gear assembly 20 can be adjusted, realizing the preliminary alignment of the landing position of the landing gear assembly 20, being able to realize the correction of the docking attitude between the flight cabin and the chassis 10, solving the deviation problem of the automatic docking between the flight cabin and the chassis 10 during landing, and ensuring that the subsequent locking device 30 and the locking part 21 cooperate more smoothly and reliably.

[0122] In some embodiments, as Figures 3 - 5 , Figure 23 shown, there are multiple abutting parts 111. The multiple abutting parts 111 are spaced along the length direction of the groove 121. Through the multiple abutting parts 111, multiple different positions of the landing gear assembly 20 can be adjusted, ensuring the reliability of the landing position of the landing gear assembly 20 and effectively solving the deviation problem of the automatic docking between the flight cabin and the chassis 10 during landing.

[0123] In the embodiments of the present invention, the number of the abutting parts 111 arranged along the length direction of the groove 121 can be flexibly set according to the actual situation. For example, the number of the abutting parts 111 arranged along the length direction of the groove 121 can be two as Figure 4 shown, or three, four, five, six or more, which are all within the protection scope of the present invention.

[0124] For example, in some specific embodiments, as Figure 3 , Figure 4 , Figure 23 and Figure 30 shown, the upper surface of the landing platform 12 is provided with a groove 121. At both ends in the front - rear direction of the groove 121 are provided with limiting blocks 122. The vehicle frame 11 is further provided with an abutting part 111. The abutting part 111 is rotatably arranged on the vehicle frame 11. The abutting part 111 is located on at least one side in the left - right direction of the groove 121.

[0125] When the flight cabin needs to land, the groove 121 is formed to position the landing gear assembly 20 at the parking position on the landing platform 12. When the flight cabin lands on the landing platform 12, the two limit blocks 122 respectively abut against the front and rear sides of the landing gear assembly 20 to realize the limit of the landing gear assembly 20 in the front and rear directions. And by rotating the abutting portion 111, one side of the abutting portion 111 in the left and right directions abuts against the landing gear assembly 20, ensuring that a part of the landing gear assembly 20 is accurately located in the groove 121, so as to realize the limit of the landing gear assembly 20 in the left and right directions, realize the preliminary alignment of the landing position of the landing gear assembly 20, thereby realizing the correction of the docking attitude between the flight cabin and the chassis 10, solving the deviation problem of the automatic docking between the flight cabin and the chassis 10 during landing, and ensuring that the subsequent locking device 30 and the locking portion 21 cooperate more smoothly and reliably.

[0126] In some embodiments where there are multiple grooves 121, such as Figures 3 - 5 , Figure 23 shown, there are two grooves 121 spaced apart in the width direction of the landing platform 12. The abutting portion 111 is provided on one side of the groove 121 in the width direction close to and / or away from each other, that is, the abutting portion 111 is provided on one side of the groove 121 in the width direction close to each other, or the abutting portion 111 is provided on one side of the groove 121 in the width direction away from each other, or the abutting portion 111 is provided on both sides of the groove 121 in the width direction close to and away from each other. Through the above settings, the reliability of the position adjustment of the landing gear assembly 20 can be realized, ensuring the reliability of the preliminary alignment of the landing position of the landing gear assembly 20, effectively solving the deviation problem of the automatic docking between the flight cabin and the chassis 10 during landing, and ensuring that the subsequent locking device 30 and the locking portion 21 cooperate more smoothly and reliably.

[0127] In some embodiments of the present invention, such as Figure 26 shown, the lower end surface of the locking portion 21 is higher than the lowest point of the landing gear assembly 20. When the flight cabin lands, it can prevent the locking portion 21 from contacting the landing chassis 10 first and causing instability, solving the problem of knocking of the locking portion 21 during landing, protecting the integrity and functionality of the locking portion 21, and being beneficial to extending the service life.

[0128] In some embodiments, such as Figures 23 - 27 shown, the landing gear assembly 20 includes a landing gear body 22. The landing gear body 22 includes two longitudinal beams 221 and two bending portions 222. The two longitudinal beams 221 are spaced apart in the width direction of the cabin body (for example Figure 1 the left and right directions shown), and the two bending portions 222 are respectively located in the length direction of the two longitudinal beams 221 (for example Figure 1At both ends in the front-rear direction (as shown), and both ends in the length direction of the bent portion 222 are connected to the same end of the two longitudinal beams 221. The bent portion 222 is bent upward, which can meet the connection requirements between the landing gear assembly 20 and the cabin body, and at the same time ensure the stability of the landing gear assembly 20 when placed on the chassis 10. Moreover, the structure of the landing gear body 22 is simple, which is convenient for processing and manufacturing.

[0129] In addition, as Figures 23 - 26 , Figure 28 shown, the landing gear assembly 20 further includes a cross beam 23. The cross beam 23 extends along the width direction of the cabin body, and both ends in the length direction of the cross beam 23 are connected to the two longitudinal beams 221. By means of the cross beam 23, the structural strength of the landing gear assembly 20 can be improved, and problems such as deformation can be avoided. The middle part of the cross beam 23 is bent upward, and the locking part 21 is arranged on the lower end surface of the cross beam 23, so that the lower end surface of the locking part 21 is higher than the lowest point of the landing gear assembly 20, meeting the required setting requirements. Moreover, the structure of the landing gear assembly 20 is simple, which is convenient for processing and manufacturing, and is beneficial to reducing production costs.

[0130] In some embodiments, as Figure 24 , Figure 25 and Figure 28 shown, there are multiple cross beams 23. The multiple cross beams 23 are arranged at intervals in the length direction of the longitudinal beam 221. By means of the multiple cross beams 23, the structural strength of the landing gear assembly 20 can be further improved, thereby ensuring the stability of the flight cabin when placed and prolonging the service life of the landing gear assembly 20.

[0131] In the embodiments of the present utility model, the number of the cross beams 23 can be flexibly set according to the actual situation. For example, the cross beams 23 can be two as Figure 25 shown, or can be three, four, five, six or more, which are all within the protection scope of the present utility model.

[0132] In some embodiments, the cross beam 23 and the longitudinal beam 221 are connected by fasteners or welded connection, which can ensure the reliable connection between the cross beam 23 and the longitudinal beam 221 and meet the required connection requirements.

[0133] In some embodiments, the locking part 21 and the bent portion 222 are connected by fasteners or welded connection, which can ensure the reliable connection between the locking part 21 and the bent portion 222 and meet the required connection requirements.

[0134] According to some embodiments of the present utility model, as Figure 26As shown, the distance between the lower end surface of the locking portion 21 and the lowest point of the landing gear assembly 20 is 5 mm - 10 mm, that is, the distance between the lower end surface of the locking portion 21 and the lowest point of the landing gear assembly 20 is H2 and satisfies 5 mm ≤ H2 ≤ 10 mm. Within the above range, while ensuring reliable cooperation between the locking device 30 and the locking portion 21, it can prevent the locking portion 21 from contacting the landing chassis 10 first and causing instability, solve the problem of the locking portion 21 being knocked during landing, protect the integrity and functionality of the locking portion 21, and is beneficial to extending the service life. For example, in some specific embodiments, the distance between the lower end surface of the locking portion 21 and the lowest point of the landing gear assembly 20 can be 5 mm, 6 mm, 7 mm, 8 mm, 9 mm, 10 mm, etc.

[0135] Other configurations and operations of the aircraft 100 according to the embodiments of the present invention are known to those of ordinary skill in the art and will not be described in detail here.

[0136] In the description of the present invention, it should be noted that unless otherwise clearly specified and limited, the terms "installation", "connection", and "connection" should be understood in a broad sense. For example, it 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 directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations.

[0137] In the description of this specification, the descriptions referring to terms such as "embodiment", "specific embodiment", "example", etc. mean that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described can be combined in a suitable manner in any one or more embodiments or examples.

[0138] Although the embodiments of the present invention have been shown and described, those of ordinary skill in the art can understand that various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principles and purposes of the present invention. The scope of the present invention is defined by the claims and their equivalents.

Claims

1. An aircraft, characterized in that: include: Chassis; A flight cabin body, the flight cabin body is suitable for being arranged on the chassis, and a locking portion is provided at the bottom of the flight cabin body; A locking device is movably arranged on the chassis in the up-down direction. When the locking device is in a locked state, at least a part of the locking device is located above the chassis and cooperates with the locking portion.

2. The aircraft according to claim 1, characterized in that The locking device comprises: Claws; A first driving mechanism is disposed on the chassis and connected to the claw to drive the claw to engage with the locking portion.

3. The aircraft according to claim 2, characterized in that: The claw is provided with a sliding hole, and in the length direction of the claw, the sliding hole extends obliquely toward one side in the width direction of the claw, and the first driving mechanism includes: A housing, the housing being connected to the chassis and having a mounting groove; A moving member, the moving member is movably arranged in the installation groove along the up-down direction, the claws are multiple and spaced along the circumferential direction of the moving member, and one end of the multiple claws close to the bottom wall of the installation groove in the length direction is rotatably connected to the moving member; A fixed shaft is fixed in the mounting groove and penetrates into the sliding hole, and the fixed shaft is movable relative to the length direction of the sliding hole.

4. The aircraft according to claim 3, characterized in that The first driving mechanism further comprises: a motor having an output shaft; The screw rod extends in the up-down direction and is connected to the output shaft. Part of the screw rod is inserted into the mounting groove. The moving part is sleeved on the screw rod and is driven to move by the screw rod.

5. The aircraft according to claim 3, characterized in that: A guide groove extending in the up-down direction is provided on the groove wall of the installation groove, and a guide protrusion cooperating with the guide groove is provided on the outer peripheral wall of the moving member; And / or, a drainage hole communicating with the mounting groove is provided on the outer peripheral wall of the shell.

6. The aircraft according to claim 2, characterized in that: The locking portion has a flange, and the claw is suitable for abutting against the upper end of the flange.

7. The aircraft according to claim 1, characterized in that: A matching groove is arranged on the lower end surface of the locking portion, and a matching protrusion matching with the matching groove is arranged on the upper end surface of the locking device.

8. The aircraft according to claim 7, characterized in that In the direction from top to bottom, a groove wall on one side of the matching groove close to the central axis of the locking portion extends obliquely toward the direction close to the central axis of the locking portion, and in the direction from top to bottom, a groove wall on one side of the matching protrusion close to the central axis of the locking portion extends obliquely toward the direction close to the central axis of the locking portion, and a groove wall on one side of the matching groove close to the central axis of the locking portion abuts against a side wall of the matching protrusion close to the central axis of the locking device; And / or, in the direction from top to bottom, a groove wall on one side of the matching groove away from the central axis of the locking portion extends obliquely toward a direction away from the central axis of the locking portion.

9. The aircraft according to claim 1, characterized in that: Also includes: A lifting device is arranged on the chassis, and the locking device is arranged on the lifting device. The lifting device is used to drive the locking device to move in the up and down directions.

10. The aircraft according to claim 9, characterized in that The lifting device comprises: A base plate, wherein the base plate is arranged on the chassis at intervals, each base plate is provided with the locking device, the locking device is passed through the base plate, and the locking parts are a plurality of locking parts corresponding to the locking devices one by one; a second driving mechanism, the second driving mechanism being connected to the chassis and used for driving the substrate to move in an up-down direction; A guide rail assembly comprises a guide rail body and a slider movable on the guide rail body, wherein the guide rail body is connected to the chassis and extends in the up-down direction, and the slider is connected to the base plate.

11. The aircraft according to claim 10, characterized in that The second driving mechanisms are multiple and correspond one to one with the substrates; Or, there are multiple second driving mechanisms, at least some of the second driving mechanisms drive at least two substrates, and the multiple substrates connected to the same second driving mechanism are connected via a connecting member; Alternatively, there is one second driving mechanism, and the second driving mechanism is used to drive the plurality of substrates to move in the up-down direction.

12. The aircraft according to claim 1, characterized in that The flight cabin comprises: cabin body; A landing gear assembly is connected to the cabin body, and the locking portion is arranged on the landing gear assembly.

13. The aircraft according to claim 12, characterized in that The chassis comprises: A frame, wherein the locking device is movably arranged on the frame in an up-down direction; A landing platform is arranged above the frame and connected to the frame. When the locking device is in a locked state, at least a portion of the locking device is passed through the landing platform to cooperate with the locking portion.

14. The aircraft according to claim 13, characterized in that A groove is provided on the upper surface of the landing platform, and a portion of the landing gear assembly is adapted to be located in the groove.

15. The aircraft according to claim 14, characterized in that Limit blocks are provided at both ends of the groove in the length direction, and the two limit blocks are respectively suitable for abutting against the two sides of the landing gear assembly in the length direction of the groove.

16. An aircraft according to claim 14 or 15, characterized in that The frame is also provided with an abutment portion, which is rotatably provided on the frame and is located on at least one side in the width direction of the groove. One side of the abutment portion along the width direction of the groove abuts against the landing gear assembly.

17. The aircraft according to claim 12, characterized in that: The lower end surface of the locking portion is higher than the lowest point of the landing gear assembly, and the distance between the lower end surface of the locking portion and the lowest point of the landing gear assembly is 5mm-10mm.

Images