Landing gear, unmanned aerial vehicle, aircraft, landing pad system, perch system and method

Abstract

A landing gear (1), an unmanned aerial vehicle, an aircraft (11), a landing pad system, a perch system and a method. The landing gear (1) is configured to be arranged on the back of the aircraft (11), and the landing gear (1) comprises a connector and locking members, wherein a first end of the connector is configured to be connected to the back of the aircraft (11); and a plurality of locking members are provided on a side portion of the connector, and the locking members are configured to fit with a locking mechanism in an aircraft perch apparatus (6).

Description

Landing gear, unmanned aerial vehicle, aircraft, apron system, habitat system and method TECHNICAL FIELD

[0001] The present application relates to the field of aircraft technology, in particular to a landing gear, unmanned aerial vehicle, aircraft, apron system, habitat system and method. BACKGROUND

[0002] An unmanned aerial vehicle, referred to as "drone", is a no-load aircraft controlled by wireless remote control equipment and self-provided program control device, which is widely used in technical fields such as aerial reconnaissance, monitoring, communication, anti-submarine electronic jamming, etc.

[0003] In the prior art, the aircraft such as unmanned aerial vehicle is habitat in the suspension structure of aircraft habitat equipment through mechanical gripper and other devices, but the setting of mechanical gripper and other structures increases the weight and power consumption of the unmanned aerial vehicle, and shortens the endurance time of the unmanned aerial vehicle.

[0004] Therefore, how to prolong the endurance time of the aircraft has become a technical problem to be solved by those skilled in the art. SUMMARY

[0005] The purpose of the present application is to provide a landing gear, unmanned aerial vehicle, aircraft, apron system, habitat system and method to prolong the endurance time of the aircraft.

[0006] To achieve the above purpose, the present application provides the following solutions:

[0007] The present application provides a landing gear, which is arranged on the back of an aircraft.

[0008] The landing gear comprises a connecting piece and a locking piece.

[0009] The first end of the connecting piece is connected with the back of the aircraft, and the side of the connecting piece is provided with a plurality of locking pieces which are matched with the locking mechanism in the suspension structure.

[0010] The present application provides an unmanned aerial vehicle, which comprises the above-mentioned landing gear arranged on the back of the unmanned aerial vehicle.

[0011] The present application provides an aircraft, which comprises the above-mentioned landing gear arranged on the back of the aircraft.

[0012] The present application provides an apron system, which comprises a plurality of aircraft habitat equipment arranged at the height required for aircraft operation, and the number of aircraft habitat equipment corresponds to the demand of aircraft operation.

[0013] The aircraft habitat equipment comprises a channel and a locking mechanism.

[0014] The channel is arranged towards a landing gear on the back of the aircraft, and is used for the landing gear to enter and exit the aircraft habitat device;

[0015] The locking mechanism is used in cooperation with the landing gear on the back of the aircraft to achieve unlocking and locking of the aircraft.

[0016] The present application provides a temporary aircraft habitat system, which comprises:

[0017] An aircraft habitat device is provided with a suspension structure, and the suspension structure is provided with a suspension habitat part.

[0018] A landing gear is arranged on the top of the aircraft, and the landing gear is provided with a suspension cooperation part, and the landing gear is made of light material.

[0019] The suspension cooperation part and the suspension habitat part have a lap joint cooperation state and a disengagement state, in the lap joint cooperation state, the suspension cooperation part and the suspension habitat part are lap jointed from top to bottom, and the aircraft is in a habitat state; in the disengagement state, the suspension cooperation part and the suspension habitat part are disengaged, and the aircraft is in a flight state.

[0020] The present application provides a temporary aircraft habitat method, which applies the above-mentioned temporary aircraft habitat system, and the temporary aircraft habitat method comprises: realizing temporary habitat of the aircraft by suspending the landing gear on the top of the aircraft on the suspension structure of the aircraft habitat device.

[0021] The present application has the following technical effects relative to the prior art:

[0022] The present application can make the aircraft stop in the aircraft habitat device through the cooperation of the locking part and the locking mechanism, which eliminates the setting of mechanical grippers and other complicated mechanical equipment, simplifies the structure of the landing gear, reduces the overall weight of the aircraft and the landing gear, and the power consumption of the aircraft, prolongs the endurance time of the aircraft; and in the present application, the landing gear is arranged on the back of the aircraft, which realizes the avoidance setting of the aircraft mounting device and the landing gear, so that the aircraft can stop in the aircraft habitat device through the landing gear when the endurance time is insufficient, and continue to carry out photography, video shooting and other operations, which saves the energy consumed by the aircraft constantly flying, thereby further prolonging the endurance time of the aircraft. BRIEF DESCRIPTION OF DRAWINGS

[0023] In order to make the technical solutions in the embodiments of the present application or the prior art clearer, the accompanying drawings needed in the embodiments will be briefly introduced below. Obviously, the accompanying drawings in the following description only need to be some embodiments of the present application, and other drawings can be obtained by those skilled in the art without any creative effort on the basis of these drawings.

[0024] Fig. 1 is a structural schematic diagram of a landing gear;

[0025] Fig. 2 is a structural schematic diagram of an aircraft habitat device;

[0026] Fig. 3 is a structural schematic diagram of the cooperation of the landing gear and the aircraft habitat device in the lapping cooperation state;

[0027] Fig. 4 is a structural schematic diagram of an aircraft applying the landing gear in the present application;

[0028] Fig. 5 is a structural schematic diagram of an aircraft applying the landing gear in the present application temporarily inhabiting in a suspension structure through the landing gear;

[0029] In the drawings, 1 is a landing gear; 2 is a habitat shaft; 3 is a habitat rod; 4 is a fixing rod; 5 is a first driving device; 6 is an aircraft habitat device; 7 is a suspension body; 8 is a limiting part; 9 is a dredging groove; 10 is a suspension groove; 11 is an aircraft; and 12 is a mounting device. DETAILED DESCRIPTION

[0030] The technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only some embodiments of the present application, but not all the embodiments. Based on the embodiments in the present application, all the other embodiments obtained by those skilled in the art without any creative effort belong to the protection scope of the present application.

[0031] In order to make the above-mentioned purposes, features and advantages of the present application more obvious and easy to understand, the present application will be further described in detail below with reference to the drawings and specific embodiments.

[0032] As shown in Figs. 1-5, the present application provides a landing gear 1, which is used for being arranged at the back of an aircraft 11; the landing gear 1 comprises a connecting piece and a locking piece; the connecting piece is arranged along the vertical direction, the first end of the connecting piece is used for being connected with the back of the aircraft 11, and the side of the connecting piece is provided with a plurality of locking pieces, which are used for cooperating with the locking mechanism in the aircraft habitat device.

[0033] The aircraft 11 can be parked in the aircraft habitat device by cooperation of the locking member and the locking mechanism, which eliminates the setting of complicated mechanical equipment such as mechanical grippers, simplifies the structure of the landing gear 1, reduces the overall weight of the aircraft 11 and the landing gear 1, and the power consumption of the aircraft 11, prolongs the endurance time of the aircraft 11; and the landing gear is arranged at the back of the aircraft 11, which realizes the avoidance setting of the mounting device 12 and the landing gear 1, so that the aircraft 11 can be parked in the aircraft habitat device through the landing gear 1 when the endurance time is insufficient, and continue to carry out photography, video shooting and other operations, which saves the energy consumed by the aircraft 11 constantly flying, thereby further prolonging the endurance time of the aircraft 11.

[0034] In the application, the connecting member has various setting forms, and can be habitat shaft 2, connecting plate, connecting block and the like, or other structures capable of connecting the landing gear 1 and the aircraft 11 together; similarly, the locking member can also be habitat rod 3, locking plate, locking block and the like, or other structures capable of cooperating with the locking mechanism in the aircraft habitat device 6 to enable the aircraft 11 using the landing gear 1 to be stably parked in the aircraft habitat device 6. The aircraft habitat device 6 in the application is fixed on high-rise buildings and the like, and the setting height of the aircraft habitat device 6 should meet the requirements of aerial photography and other operations of the aircraft 11.

[0035] The angle between the connecting member and the locking member in the application is not greater than 90°. This enables the gravity, dynamic load, wind force and other forces acting on the locking member to be directly transmitted in the direction of the habitat shaft 2, reduces the influence of side force on the locking member, improves the locking effect of the locking member, reduces the possibility of lateral movement of the locking member, and enables the locking member to provide stable support. Alternatively, if the working condition requires, the angle between the connecting member and the locking member can also be greater than or less than 90°.

[0036] As shown in FIG. 1-2, the connecting piece in the application comprises a habitat shaft 2; the first end of the habitat shaft 2 is used for connecting with the back of the aircraft 11, and the side of the habitat shaft 2 is provided with at least two locking pieces which are uniformly distributed along the circumference of the habitat shaft 2. The locking pieces which are uniformly distributed along the circumference of the habitat shaft 2 can be uniformly distributed around the habitat shaft 2 when subjected to external force, avoiding the problem of local stress concentration of the habitat shaft 2, and the plurality of locking pieces improves the overall fixing effect of the locking pieces, so that the aircraft 11 using the landing gear 1 in the application is less likely to loosen or separate when parked in the aircraft habitat equipment 6; the uniformly distributed locking pieces can effectively disperse and absorb vibration, avoiding the resonance phenomenon of certain frequencies, and improving the anti-vibration performance of the aircraft 11 using the landing gear 1 in the application; and the arrangement of the plurality of locking pieces improves the safety of the aircraft 11 using the landing gear 1 in the application: even if a locking piece fails, the aircraft 11 can still be stably parked in the aircraft habitat equipment 6 through other locking pieces.

[0037] Specifically, the application can also uniformly arrange three locking pieces along the circumference of the habitat shaft 2, and the three locking pieces form a triangle, and the triangle has stability, so that the locking pieces can provide balanced support force in all directions, so that the habitat shaft 2 is uniformly stressed on different sides, avoiding tilting or deformation caused by excessive unilateral stress.

[0038] The top of the connecting piece is provided with a fixing piece for fixing the landing gear 1 on the aircraft habitat equipment 6. The landing gear 1 can be fixed in the aircraft habitat equipment 6 through the fixing piece, thereby improving the ability of the aircraft 11 to resist external loads such as wind, so that the aircraft 11 using the landing gear 1 in the application is less likely to sway with the wind, and the stability of the aircraft 11 using the landing gear 1 in the application parked in the aircraft habitat equipment 6 is improved.

[0039] As shown in FIG. 1, 2, the fixing piece comprises a fixing rod 4 and a first driving device 5; the aircraft habitat equipment 6 is provided with a fixing plate, which can be the inner top wall of the aircraft habitat equipment 6, or an additional plate provided in the aircraft habitat equipment 6; the first end of the fixing rod 4 is connected with the output end of the first driving device 5, and the first driving device 5 is used to drive the fixing rod 4 to move away from and approach the fixing plate. When the aircraft 11 using the landing gear 1 in the application is parked in the aircraft habitat equipment 6, the first driving device 5 drives the fixing rod 4 to move towards the fixing plate, so that the top of the fixing rod 4 abuts against the fixing plate, and the friction between the fixing plate and the fixing rod 4 realizes further fixation of the aircraft 11 using the landing gear 1 in the application, thereby improving the ability of the aircraft 11 using the landing gear 1 in the application to resist external loads, so that the aircraft 11 using the landing gear 1 in the application can stably stay in the aircraft habitat equipment 6 and continue aerial photography work.

[0040] Alternatively, the fixing member in the present application can also not adopt the above structure, at this time, the fixing member comprises a clamping rod, and a limiting block is arranged on the side of the clamping rod; a clamping plate is arranged in the aircraft habitat device 6, and a limiting hole and a limiting member are arranged on the clamping plate; the limiting hole is matched with the clamping rod and the limiting block, and the limiting member is located at the top end of the clamping plate and is arranged around the limiting hole and is used to limit the rotation of the limiting block. Among them, the matching of the limiting hole with the clamping rod and the limiting block means that the clamping rod and the limiting block can pass through the limiting hole, when the aircraft 11 using the landing gear 1 in the present application is parked in the aircraft habitat device 6, the transition cooperation of the limiting hole with the clamping rod limits the movement of the fixing rod, so as to realize the fixation of the aircraft 11 using the landing gear 1 in the present application, and reduce the shaking of the aircraft 11 using the landing gear 1 in the present application under external load; after the aircraft 11 using the landing gear 1 in the present application enters the aircraft habitat device and the limiting block passes through the limiting hole, the aircraft 11 rotates so that the limiting block is no longer aligned with the limiting hole, at this time, the clamping plate prevents the clamping rod from moving in the horizontal direction, and the limiting member limits the rotation of the limiting block, thereby further improving the stability of the aircraft 11 parked in the aircraft habitat device. The limiting member can be specifically a plurality of arc-shaped plates arranged above the clamping plate, for example, when the limiting block has two, the arc-shaped plates have four, by arranging the limiting block between the two arc-shaped plates, the rotation of the landing gear 1 is limited.

[0041] The rotation of the clamping rod can be realized by the rotation of the aircraft 11, but at this time, it needs to be noted that the limiting member and the locking mechanism in the aircraft habitat device need to be matched and arranged, so that when the locking member is locked in the aircraft habitat device, the limiting block can be limited by the limiting member; or, a second driving device can also be arranged at the top of the habitat shaft 2, and the clamping rod is driven to rotate by the second driving device, so as to realize the rotation limitation of the limiting block by the limiting member.

[0042] When the fixing rod, the clamping rod, the fixing plate and the clamping plate exist at the same time, the fixing plate can be the inner top wall of the aircraft habitat device, the clamping plate is a plate arranged in the aircraft habitat device below the inner top wall of the aircraft habitat device, the fixing rod and the clamping rod are actually a rod, and the rod can be in transition cooperation with the clamping hole on the clamping plate and can be in abutment with the fixing plate after passing through the clamping hole. That is to say, at this time, on the one hand, the abutment of the fixing rod and the fixing plate prevents the shaking of the aircraft, and the fixing plate can prevent the upward jumping of the aircraft, on the other hand, the clamping hole and the limiting member prevent the rotation of the aircraft, thereby further improving the stability of the aircraft using the landing gear in the present application when parked in the aircraft habitat device.

[0043] At this time, neither the first driving device nor the second driving device can be provided, or only the first driving device or the second driving device can be provided. When only the first driving device is provided, the fixed rod is driven upward by the first driving device to extend through the clamping hole and abut against the fixed plate, and the rotation of the aircraft itself is used to realize the rotation restriction of the limiting block by the limiting piece, and when the limiting block is rotationally restricted by the limiting piece, the locking piece can cooperate with the locking mechanism in the aircraft habitat device 6, so that the aircraft 11 is stably parked in the aircraft habitat device 6, that is, the function of the locking piece is not affected. When only the second driving device is provided, the length of the fixed rod is such that the fixed rod can abut against the fixed plate when the aircraft is parked in the aircraft habitat device 6 by the locking piece, and the second driving device drives the fixed rod to rotate, so that the limiting block can be rotationally restricted by the limiting piece.

[0044] The locking piece in the application includes a habitat rod 3. The end of the habitat rod 3 away from the habitat shaft 2 is provided with a clamping piece, the clamping piece is arranged to avoid the locking mechanism, and the clamping piece is used to extend out of the aircraft habitat device 6 and is used to be attached to the aircraft habitat device 6. The clamping piece is arranged to avoid the locking mechanism, which means that the functions of the clamping piece and the locking mechanism will not interfere with each other, and the functions of the two can be smoothly realized. The clamping piece is equivalent to the "locking claw" of the landing gear 1. When the aircraft 11 using the landing gear 1 in the application shakes, the clamping piece attached to the aircraft habitat device 6 can inhibit the shaking trend of the aircraft 11, thereby ensuring the stability of the aircraft 11 parked in the aircraft habitat device 6. The clamping piece can have various shapes, such as hook-shaped, plate-shaped or claw-shaped, but regardless of the shape of the clamping piece, the clamping piece satisfies the function of "the clamping piece can be attached to the aircraft habitat device 6".

[0045] The clamping piece includes a limiting part, which is arranged to be in close contact with the outer side wall of the aircraft habitat device 6 when the aircraft 11 using the landing gear 1 in the application is parked in the aircraft habitat device 6. The limiting part can be a flange of the habitat rod 3 extending in the direction of the side wall of the aircraft habitat device 6.

[0046] The landing gear 1 further includes a fastener, which is arranged around the first end of the connecting piece. The first end of the fastener is connected to the connecting piece, and the second end of the fastener is connected to the back of the aircraft 11. The fastener can be a fastening rod. By arranging multiple fasteners, the connection between the aircraft 11 and the connecting piece is strengthened.

[0047] Furthermore, the application also provides an unmanned aerial vehicle, which includes the landing gear 1 described above, and the landing gear 1 is arranged on the back of the unmanned aerial vehicle. The bottom of the unmanned aerial vehicle is provided with a mounting device 12, which can be selectively matched according to the working conditions to perform aerial photography, environmental monitoring and other operations. The back of the unmanned aerial vehicle can be understood as the top of the unmanned aerial vehicle.

[0048] Further, the application also provides an aircraft 11, which comprises the landing gear 1 described above, and the landing gear 1 is arranged on the back of the aircraft 11. The aircraft 11 includes a drone, a flying car, an amphibious aircraft, etc. which can be applied to the structure of the landing gear 1 in the application. And the landing gear 1 in the application can be adjusted according to the type of the applied aircraft 11, so that when the aircraft 11 is parked in the aircraft habitat device, the aircraft 11 can be stably suspended in the aircraft habitat device by the landing gear 1.

[0049] Further, as shown in FIG. 1, the application discloses a parking apron system, which comprises a plurality of aircraft habitat devices 6, the aircraft habitat devices 6 are arranged at the height required by the operation of the aircraft 11, and the number of the aircraft habitat devices 6 corresponds to the operation requirements of the aircraft 11; the aircraft habitat device 6 comprises a channel and a locking mechanism; the channel is arranged towards the landing gear 1 on the back of the aircraft 11, and the channel is used for the landing gear 1 to enter and exit the aircraft habitat device 6; and the locking mechanism is used for cooperating with the landing gear 1 on the back of the aircraft 11 to achieve the unlocking and locking of the aircraft 11.

[0050] Because the channel of the aircraft habitat device 6 in the application is arranged towards the landing gear 1 on the back of the aircraft 11, which makes the aircraft 11 be able to park in the aircraft habitat device 6 with the back upwards, so when the aircraft 11 is parked in the aircraft habitat device 6, the mounting device 12 at the bottom of the aircraft 11 will not be blocked by the aircraft habitat device 6, and the aerial photography or environmental detection operation can continue. And the parking apron system comprises a plurality of aircraft habitat devices 6, and the required number of aircraft habitat devices 6 are covered in the operation range of the aircraft 11, and the aircraft habitat devices 6 are arranged at the height required by the operation of the aircraft 11, which means that the aircraft 11 applied to the parking apron system in the application does not need to complete the aerial photography or environmental detection operation by continuous hovering flight, and the aircraft 11 only needs to complete the aerial photography or environmental detection operation at each aircraft habitat device 6 in the operation range one by one, and then the overall aerial photography or environmental detection operation can be completed, that is, the aircraft 11 only needs to be transferred from one aircraft habitat device 6 to another aircraft habitat device 6 in the overall operation process, and does not need to hover for a long time, thereby shortening the hovering flight time of the aircraft 11. Compared with the energy consumed by the continuous hovering flight of the aircraft 11, the energy consumed by the movement of the aircraft 11 between the aircraft habitat devices 6 is less, so the aircraft 11 does not need to be charged in the aircraft habitat device 6, and the charging network and other devices do not need to be arranged in the aircraft habitat device 6, thereby simplifying the structure of the aircraft habitat device 6, reducing the manufacturing cost of the aircraft habitat device 6, and reducing the failure rate of the aircraft habitat device 6.

[0051] It should be noted that the aircraft habitat 6 in the application can be used for the habitat of the unmanned aerial vehicle, and can also be used for other types of aircraft 11 that can be adapted to the aircraft habitat 6 in the application, such as flying cars; and the size and shape of the aircraft habitat 6 in the application can be adjusted according to the aircraft 11 used.

[0052] The aircraft habitat 6 in the application can be arranged on a building such as a high-rise building, or a support member such as a cylindrical or cuboid support column can be arranged separately for installing the aircraft habitat 6; because the aircraft habitat is arranged in the above-mentioned area; a certain height from the ground, so the aircraft habitat 6 can be called a suspended structure.

[0053] The aircraft habitat 6 is arranged at a height required for the operation of the aircraft 11, which means that when the aircraft 11 is parked in the aircraft habitat 6, the aircraft 11 can continue to carry out aerial photography, environmental detection and other operations through the mounting device 12 (the mounting device 12 can be a camera, an environmental detection device, etc., the specific type depends on the specific task of the aircraft 11).

[0054] The number of aircraft habitats 6 arranged in the application corresponds to the operation requirements of the aircraft 11, which means that within the range where the aircraft 11 needs to operate, there are a number of aircraft habitats 6 that can meet the operation requirements of the aircraft 11. The number of aircraft habitats 6 is related to the range of the aircraft 11 operation area, the coverage range of the mounting device 12 of the aircraft 11, etc.

[0055] The channel refers to the path passed by the aircraft 11 from the beginning of entering the aircraft habitat 6 to the cooperation of the back landing gear 1 of the aircraft 11 with the locking mechanism, and the locking of the locking part in the landing gear 1 on the locking mechanism.

[0056] The locking mechanism in the application completes the locking and unlocking of the locking part of the landing gear 1 of the aircraft 11 through the cooperation of the structure, reduces the use of power, hydraulic and other equipment, reduces the weight and volume of the locking mechanism and the aircraft habitat 6 in the application, and further reduces the manufacturing cost of the aircraft habitat 6.

[0057] As shown in FIGS. 1-2, the locking mechanism in the application includes a limiting part 8 and a suspension habitat part; the limiting part 8 and the suspension habitat part are arranged in sequence along the rotation direction of the aircraft 11; the limiting part 8 is used to limit the aircraft 11 from leaving the aircraft habitat 6, and the side of the aircraft habitat 6 is provided with at least two locking mechanisms, and the suspension habitat part is used to support the landing gear 1 of the aircraft 11.

[0058] The limiting part 8 is used to limit the landing gear 1 from leaving the aircraft habitat 6. When the aircraft 11 using the aircraft habitat 6 of the present application stays in the aircraft habitat 6, the limiting part 8 makes the aircraft 11 not easy to leave the aircraft habitat 6. However, this does not mean that the aircraft 11 cannot leave the aircraft habitat 6. When the aircraft 11 needs to move to the next aircraft habitat 6 or complete the work, the aircraft 11 starts and unlocks the locking mechanism, and the aircraft 11 can leave the suspension structure.

[0059] The direction of rotation of the aircraft 11 is the clockwise or counterclockwise direction of rotation with the center line in the vertical direction of the aircraft habitat 6 as the axis. Regardless of the direction, when the landing gear 1 enters the aircraft habitat 6, it first passes through the limiting part 8 and then reaches the suspension habitat.

[0060] Three locking mechanisms are uniformly arranged along the side of the aircraft habitat 6. This means that three locking pieces need to be arranged on the landing gear 1 at the back, i.e., the top, of the aircraft 11. The locking piece can be a habitat rod 3 arranged along the habitat axis 2. This makes the locking piece of the landing gear 1 of the aircraft 11 provide balanced support force to the landing gear 1 in multiple directions, so that the landing gear 1 is uniformly stressed in different sides, avoiding tilting or deformation caused by excessive stress on one side. At the same time, the three suspension habitats are uniformly arranged on the side of the aircraft habitat 6, which also avoids the problem of local stress concentration of the aircraft habitat 6, making the aircraft habitat 6, especially the locking mechanism, less likely to be damaged.

[0061] The suspension habitat includes a suspension groove 10, which is used to contact the part of the side surface of the locking piece in the landing gear 1. The suspension groove 10 is used to contact the part of the side surface of the locking piece, which means that when the locking piece enters the suspension groove 10 and contacts the suspension groove 10, the suspension groove 10 does not completely wrap the side surface of the locking piece (for example, when the locking piece is a habitat rod, the habitat rod has a length of 0.2 cm in contact with the suspension groove 10, and the groove wall of the suspension groove 10 does not support the entire side surface of the 0.2 cm length area of the habitat rod. Only the bottom of the 0.2 cm length area of the habitat rod is in contact with the suspension groove 10, and the top of the 0.2 cm length area of the habitat rod is not in contact with the suspension groove 10). This reduces the contact area between the suspension habitat, i.e., the locking mechanism, and the locking piece, making it less likely for the aircraft 11 to stick when flying into and out of the locking mechanism in low temperature conditions such as rainy and snowy weather, allowing the aircraft habitat 6 of the present application to have stronger environmental adaptability.

[0062] Specifically, the hanging groove 10 has various setting forms, for example, the cross section of the hanging groove 10 is in the shape of a cone, an arc, an inverted T or a trapezoid, it should be noted that the hanging groove 10 in the present application is not limited to the above-mentioned forms, and can also be a structure that can be partially separated from the side surface of a certain region of the locking member when supporting the landing gear 1; and / or, the aircraft habitat 6 is provided with a limiting plate for clamping or abutting with the top fixing member in the landing gear 1 of the aircraft 11 (the fixing member can be a fixing rod 4 arranged at the top of the landing gear 1 and driven upward by the first driving device 5). When the limiting plate abuts with the fixing member, the limiting plate can be the inner side wall of the aircraft habitat 6, or another plate arranged in the aircraft habitat 6. At this time, when the aircraft 11 is parked in the aircraft habitat 6, the fixing member abuts with the limiting plate, and through the friction between the fixing member and the limiting plate, the possibility of the aircraft 11 shaking under the action of external loads such as wind is reduced, so that the aircraft 11 can be stably parked in the aircraft habitat 6; when the limiting plate clamps with the fixing member, the fixing rod 4 (at this time, the fixing member is the fixing rod 4), the limiting plate is provided with a clamping hole matched with the fixing rod 4, when the aircraft 11 is parked in the aircraft habitat 6, the fixing rod 4 moves upward and passes through the clamping hole, and the clamping hole and the fixing rod 4 are matched to prevent the aircraft 11 from shaking when parked in the aircraft habitat 6, so that the aircraft 11 can be stably parked in the aircraft habitat 6; in this way, when the aircraft 11 is parked in the aircraft habitat 6 (the aircraft 11 is parked in the aircraft habitat 6, which means that the landing gear 1 at the back of the aircraft 11 is clamped with the locking mechanism), the aircraft 11 can be clamped with the clamping hole through the fixing member in the landing gear 1, so as to fix the aircraft 11 and improve the ability of the aircraft 11 to resist external loads such as wind.

[0063] As shown in FIG. 1-2, the passage in the present application includes the communication of the dredging groove 9 and the suspension groove 10; the dredging groove 9 is located at the limiting part 8, and the effective passing area of the suspension groove 10 is smaller than the effective passing area of the dredging groove 9 (the effective passing area refers to the area for the landing gear 1 of the aircraft 11 or the area through which the habitat rod passes). On the one hand, this reduces the area that needs to be processed for the passage, reducing the processing cost of the aircraft habitat equipment 6; on the other hand, when the aircraft 11 landing gear 1 is in contact with the locking mechanism, the smaller suspension groove 10 makes the limiting part 8 play a limiting role more easily, thereby stably locking the aircraft 11 in the aircraft habitat equipment 6, preventing the aircraft 11 from accidentally escaping. The effective passing area refers to the area occupied by the aircraft 11 when passing through the passage; at the same time, the effective passing area of the suspension groove 10 is smaller than the effective passing area of the dredging groove 9, which makes the operator control the aircraft 11 to enter the aircraft habitat equipment 6 in the present application, and the aircraft 11 can only enter along the direction of the dredging groove 9 and the suspension groove 10, until the habitat rod of the aircraft 11 cooperates with the locking mechanism, and the aircraft 11 is stably parked in the suspension structure, reducing the error that may occur when the operator controls the aircraft 11 to enter the suspension structure in the non-passage direction.

[0064] The aircraft habitat equipment 6 in the present application has various shapes, such as cylindrical, conical, and prismatic structures. As shown in FIG. 1 and FIG. 2, the aircraft habitat equipment 6 is a cylindrical structure, the bottom of the aircraft habitat equipment 6 has an opening for the landing gear 1 of the aircraft 11 to enter, the top of the aircraft habitat equipment 6 is used to be fixed on a building or other structure that can install the aircraft habitat equipment 6, and the opening is in communication with the hollow cavity inside the aircraft habitat equipment 6; the locking mechanism is arranged along the circumference of the aircraft habitat equipment 6.

[0065] The aircraft habitat equipment 6 is set as a cylinder, compared with the rectangular suspension structure, it can provide a larger internal volume in a limited space, so that the aircraft habitat equipment 6 can accommodate larger landing gear 1 in the same area. Moreover, the cylindrical aircraft habitat equipment 6 has good structural stability and wind resistance: due to the symmetry of the cylinder, the aircraft habitat equipment 6 can uniformly distribute stress and load, making it more stable and safe in strong winds, heavy snow and other harsh weather conditions; the shape of the cylinder can help guide airflow and reduce wind impact; the cylindrical structure can facilitate the modular design of the aircraft habitat equipment 6, making it easy to expand and maintain; the shape of the cylinder is easy to identify visually, and also has obvious signal characteristics in radar and other detection systems, which helps the aircraft 11 accurately identify the position of the aircraft habitat equipment 6 during flight and landing.

[0066] Alternatively, the hanging habitat in the present application can also not be provided with the hanging groove 10, at this time, the hanging habitat is provided with a plurality of support protrusions in the channel in addition to being communicated with the drainage groove 9, the support protrusions are used for supporting the side of the locking member in the landing gear 1, and the support protrusions are used for being in contact with the partial area of the side of the locking member in the landing gear 1. The point contact or line contact is formed between the support protrusions and the side of the locking member. The support protrusions have various setting forms, for example, the support protrusions can be in the structure of a cone, a column and the like. When the cross section of the support protrusion is in the shape of a cone, that is, the support protrusion is in the shape of a cone, the tip of the support protrusion is arranged towards the locking member and is used for being in contact with the side of the locking member. In this way, the actual point contact is formed between the hanging habitat and the locking member, which further reduces the contact area between the hanging habitat and the locking member, so that the aircraft habitat 6 in the present application is more suitable for the unlocking and locking of the aircraft 11 and the locking mechanism under the low-temperature weather such as rain and snow, and the locking member of the aircraft 11 is less likely to be adhered to the locking mechanism.

[0067] When the line contact is formed between the support protrusions and the side of the locking member, the support protrusions can be in the shape of a prism, and the edges of the prism are arranged towards the side of the locking member of the aircraft 11 in the aircraft habitat 6.

[0068] The tip of the support protrusion is arranged towards the locking member, which means that when the aircraft 11 is parked in the aircraft habitat 6, the tip of the support protrusion is arranged towards the locking member. It does not mean that the tip of the support protrusion is arranged towards the locking member outside the aircraft habitat 6.

[0069] The limiting part 8 in the present application also has different setting modes. As shown in FIGS. 1-2, only one limiting part 8 is arranged, which eliminates the setting of multiple limiting parts 8, reduces the processing cost of the aircraft habitat 6, and multiple limiting parts 8 can be arranged as follows to strengthen the limiting function of the limiting part 8, so that the aircraft 11 is less likely to accidentally separate when parked in the aircraft habitat 6.

[0070] Specifically, the locking mechanism includes a plurality of limiting parts 8, the limiting parts 8 are arranged in sequence along the direction in which the aircraft 11 enters the channel, that is, the direction in which the aircraft 11 rotates, and the limiting parts 8 located on the upper side of the channel are arranged in a staggered manner with the limiting parts 8 located on the lower side of the channel. The limiting parts 8 arranged in this way form a structure similar to “interlocking teeth”, so that multiple limiting parts 8 can form multiple limiting positions for the aircraft 11. Even if the limiting part 8 closest to the aircraft 11 is separated from the limiting position of the aircraft 11 under the action of external force, that is, the aircraft 11 moves outward under the action of external force, the remaining limiting parts 8 can still play a limiting role, so that the aircraft 11 can continue to be parked in the aircraft habitat 6 without falling, and this provides time for the operator to adjust the position of the aircraft 11 when the aircraft 11 is found to be displaced under the action of external force.

[0071] The application discloses an aircraft temporary habitat system, which comprises an aircraft habitat device 6 and a landing gear 1.

[0072] The aircraft habitat device 6 adopts a suspension structure, and the suspension structure is provided with a suspension habitat part; the landing gear 1 is arranged on the top of the aircraft 11, and the landing gear 1 is provided with a suspension matching part and is made of a light material; the suspension matching part and the suspension habitat part have a lap joint matching state and a separation state; in the lap joint matching state, the suspension matching part and the suspension habitat part are lap joint matched from top to bottom, and the aircraft 11 is in a habitat state; in the separation state, the suspension matching part and the suspension habitat part are separated, and the aircraft 11 is in a flight state.

[0073] The aircraft temporary habitat system is used for a UAV; when the aircraft 11 needs to be temporarily habited or needs to work at a fixed position for a long time, the aircraft 11 only needs to be moved below the suspension structure, then the aircraft 11 is lifted to a preset height, the landing gear 1 on the top of the aircraft 11 is moved above the suspension habitat part, the landing gear 1 is rotated to a preset angle or the aircraft 11 drives the landing gear 1 to rotate to the preset angle, finally the aircraft 11 is lowered by a certain height, the suspension matching part and the suspension habitat part are lap joint matched from top to bottom, the temporary habitat of the aircraft 11 on the aircraft habitat device 6 is realized, and when the aircraft 11 needs to take off again, the suspension matching part and the suspension habitat part only need to be separated, so that the aircraft 11 can re-enter the flight state; since the power loss of the aircraft 11 is mostly used for resisting the gravity of the earth when the aircraft 11 is in flight and hovering, the aircraft temporary habitat system provided by the application realizes the temporary habitat by suspending the landing gear 1 on the top of the aircraft 11, and the habitat can be realized only by lap joint between mechanical structures, without the need of providing power, so that the aircraft 11 can continuously work in the airport habitat state, without the need of additional power to keep the aircraft 11 in the hovering state, the battery endurance pressure is relieved, the endurance capability of the aircraft 11 is improved, and since the temporary habitat state only relies on mechanical lap joint, power is not needed, therefore, the airport also does not need to set up a power grid, the weight and size of the aircraft field are reduced, and the cost of the aircraft habitat device 6 is reduced.

[0074] It should be noted that the aircraft habitat device 6 can be installed on the structure such as the bottom of the beam or the bottom of the platform of the building through a support rod or a support frame or the like, or the aircraft habitat device 6 can be directly arranged on the structure such as the bottom of the beam or the bottom of the platform of the building, as long as the installation mode and the installation position can meet the use requirements, and the installation mode and the installation position belong to the protection scope of the application.

[0075] In addition, the landing gear 1 is made of light material, which is beneficial to reduce the load of the aircraft and reduce the endurance pressure of the aircraft; the landing gear 1 can be made of resin, carbon fiber or plastic, as long as the material is beneficial to realize light weight and reduce the influence on the endurance of the aircraft, which belongs to the protection scope of the present application; optionally, the landing gear 1 is made of light alloy, which has the advantages of light weight, good strength and easy processing.

[0076] In addition, the landing gear 1 can be a rod or a bracket structure, and the suspension habitat can be a lapping platform or a lapping rod, as long as the structure type can meet the lapping requirement, which belongs to the protection scope of the present application.

[0077] As shown in FIGS. 1-5, the landing gear 1 includes a habitat shaft 2 and a habitat rod 3 arranged on the habitat shaft 2; one end of the habitat shaft 2 is connected to the top of the aircraft 11, and the other end is provided with the habitat rod 3, the axis of the habitat rod 3 and the axis of the habitat shaft 2 satisfy the vertical condition, and the suspension cooperation part is located on the outer circumferential wall of the habitat rod 3, so that the outer circumferential wall of the habitat rod 3 forms a suspension cooperation part, and the landing gear 1 formed by the habitat shaft 2 and the habitat rod 3 has the advantages of simple structure and low failure rate.

[0078] It should be understood that the suspension cooperation part formed by the habitat rod 3 can be a surface structure or a corner structure, as long as the structure type can meet the use requirement, which belongs to the protection scope of the present application; optionally, the suspension cooperation part provided by the embodiment of the present application is lapped on the suspension habitat by line contact or point contact, that is, the habitat rod 3 can be cylindrical, multi-prism or a plurality of lapping protrusions are arranged on the outer circumference of the habitat rod 3, so as to reduce the contact area between the suspension cooperation part and the suspension habitat, prevent the suspension cooperation part and the suspension habitat from freezing together in extremely low temperature weather or rainy and snowy weather, and because the freezing area is large, the aircraft 11 needs to overcome larger resistance when taking off again, which causes the aircraft 11 to take off difficultly or unable to take off.

[0079] In addition, the vertical condition between the axis of the habitat rod 3 and the axis of the habitat shaft 2 means that the axis of the habitat rod 3 and the axis of the habitat shaft 2 are perpendicular to each other or close to being perpendicular; and the number of the habitat rod 3 is not specifically limited in the present application, and any number that can meet the use requirements is within the protection scope of the present application; optionally, the number of the habitat rod 3 is designed to be three in the embodiment of the present application in consideration of stability and economy, and the three habitat rods 3 are uniformly distributed on the outer circumference of the habitat shaft 2, so that the contact position connecting line between the suspension matching part and the suspension habitat part forms a triangular shape when the aircraft 11 is habitat, and the aircraft 11 can be stably habitat on the aircraft habitat equipment 6 by using the principle that the triangular shape has high stability, which can improve the stability of the aircraft 11 when habitat and save the processing production, and has good economy.

[0080] The suspension structure related in the present application can be a shell structure or a support structure, and any structure type that can meet the use requirements is within the protection scope of the present application; optionally, the suspension structure provided in the embodiment of the present application includes a suspension body 7, the suspension body 7 is a hollow shell with an open bottom, the suspension habitat part includes a suspension groove 10 arranged on the suspension body 7, and the side wall of the suspension body 7 is provided with a dredging groove 9 capable of passing the habitat rod 3, each suspension groove 10 corresponds to one dredging groove 9, the dredging groove 9 extends upward from the bottom opening of the hollow shell and then extends along the outer circumference of the hollow shell to communicate with the suspension groove 10, so that when the aircraft 11 needs temporary habitat, with the upward movement of the aircraft 11, the habitat shaft 2 penetrates the dredging groove 9, then with the rotation of the aircraft 11, the habitat shaft 2 enters the suspension groove 10, and finally the aircraft 11 lands in the suspension groove 10 to realize the habitat of the aircraft 11, and based on the design of the suspension groove 10, the rotation of the aircraft 11 during temporary habitat can be reduced, which is beneficial to improve the stability, and the suspension structure is simple, low in manufacturing cost, low in failure rate, smooth in appearance, light in weight, suitable for various buildings and columnar objects, low in installation difficulty and high in installation universality.

[0081] The above-mentioned dredging groove 9 includes a guide groove and a communicating groove, the guide groove extends upward from the bottom opening of the hollow shell, and the size of the guide groove gradually increases from bottom to top, so as to guide the habitat rod 3 and make the habitat rod 3 smoothly slide into the guide groove; the communicating groove extends from the top of the guide groove to the suspension groove 10 to communicate the guide groove and the suspension groove 10, so that the habitat rod 3 enters the suspension groove 10 through the communicating groove.

[0082] The suspension structure further includes a suspension connecting piece for installing the suspension body 7 on the required building, and the suspension connecting piece can be a hook, a ring or a magnetic attraction accessory, and the type of the suspension connecting piece is not specifically limited in the present application, and any part type that can meet the installation requirements of the suspension body 7 is within the protection scope of the present application.

[0083] The upper part of the habitat shaft 2 is provided with a fixed rod 4, the hollow shell is provided with an abutting part, the suspension matching part and the suspension habitat part are in the lap joint matching state, and the fixed rod 4 is extended to the preset length. After the fixed rod 4 is abutted and pressed against the abutting part, the fixed rod 4 is abutted and pressed against the abutting part to prevent strong wind force generated by airflow in windy weather from causing the aircraft 11 in the habitat state to sway, thereby further improving the stability of the temporary habitat system.

[0084] Furthermore, the driving part of the fixed rod 4 can be directly arranged in the aircraft 11 and directly powered by the power module of the aircraft 11, without the need to additionally arrange a power supply. After the fixed rod 4 abuts and presses against the abutting part, the power supply can be turned off, thereby saving power and reducing the influence on the endurance of the aircraft 11. Alternatively, the driving part can also be arranged at the top of the aircraft 11, in which case the driving part is the first driving device 5.

[0085] The aircraft temporary habitat system further comprises a reference object arranged on the aircraft habitat device 6 or around the aircraft habitat device 6, and an information acquisition element arranged on the aircraft 11. The information acquisition element is signal-connected with the control unit of the aircraft 11, so as to acquire information of the reference object around the aircraft habitat device 6 through the information acquisition element, and transmit the acquired signal to the control unit of the aircraft 11 in the form of an electric signal. The control unit adjusts and controls the coordinates and attitude of the aircraft 11 according to the received reference object information, so that the aircraft 11 can automatically land on the suspension structure of the aircraft habitat device 6, thereby improving the degree of automation. The information acquisition element can be a visual sensor, a laser radar, an infrared sensor or other structures capable of acquiring the above information.

[0086] It should be understood that the information acquired by the information acquisition element includes one or more of image information, height information and position information, and in actual application, the type of information can be modified according to actual needs. As long as the type of information meets the use requirements, it belongs to the protection scope of the present application.

[0087] In addition, the landing gear 1 is fixedly arranged at the top of the aircraft 11, and the habitat rod 3 enters the suspension groove through the dredging groove 9 by the rotation of the aircraft 11. Alternatively, the landing gear 1 is rotatably arranged at the top of the aircraft 11, the rotation shaft of the landing gear 1 is signal-connected with the remote controller of the aircraft 11, and the rotation of the landing gear 1 is controlled by the remote controller of the aircraft 11, so that the habitat rod 3 enters the suspension groove through the dredging groove 9. As long as the arrangement meets the use requirements, it belongs to the protection scope of the present application.

[0088] In addition, the application also discloses an aircraft temporary habitat method, which applies the aircraft temporary habitat system, and realizes temporary habitat of the aircraft 11 by suspending the landing gear 1 at the top of the aircraft 11 on the suspension structure of the aircraft habitat equipment 6, so that the habitat can be realized by the lapping between the mechanical structures, and power supply is not needed, so that the aircraft 11 can continuously work in the airport habitat state, and the aircraft 11 is not needed to be kept in the hovering state by additional power supply, the battery endurance pressure is relieved, the endurance capability of the aircraft 11 is improved, and since the temporary habitat state only relies on the mechanical lapping, power supply is not needed, so that the airport, i.e. the aircraft habitat equipment 6, is also free of the need of setting up a power grid, the weight and volume of the aircraft field are reduced, and the cost of the aircraft field is reduced.

[0089] The aircraft temporary habitat method also collects reference information of the reference object by the information collection element, and controls the flight state of the aircraft 11 according to the reference information, so as to adjust the coordinates and posture of the aircraft 11.

[0090] The above-mentioned reference information includes but is not limited to distance information, angle information and image information of the reference object relative to the aircraft 11, as long as the information can be used to judge the flight state of the aircraft 11, so as to adjust the coordinates and posture of the aircraft 11, and the information belongs to the protection scope of the application.

[0091] In the aircraft temporary habitat method, after the suspension cooperation part of the landing gear 1 and the suspension habitat part of the suspension structure are in the lapping cooperation state, the fixed rod 4 on the habitat rod 3 is stretched out until abutting and pressing against the abutting part in the suspension body 7, so as to improve the stability of the aircraft 11 in the habitat state by the friction force between the fixed rod 4 of the habitat rod 3 and the abutting part in the suspension body 7, and reduce the shaking phenomenon of the aircraft 11 in the temporary habitat state caused by the wind force.

[0092] The top of the above-mentioned habitat rod 3 can also be provided as a disc structure with a large surface area, and the abutting part of the suspension body 7 is also designed as a disc structure, so that the two disc structures are abutted together, on the one hand, the shaking phenomenon caused by the wind force can be reduced by the friction force between the two disc structures, and on the other hand, the degrees of freedom of the aircraft 11 are limited by the surface contact between the two disc structures, and the stability of the aircraft 11 is ensured by the two aspects.

[0093] The habitat rod 3 structure is manufactured by using a light alloy, which has small processing difficulty, is suitable for batch production, has low manufacturing cost and large hardness, can be mass-produced and widely used, and is suitable for popularization and application.

[0094] It should be understood that the aerial vehicle 11 involved in the present application can be, but is not limited to, a UAV, and in practical applications, the aerial vehicle 11 can also be a glider, an airship, or an airplane, and the like, and thus the present application does not specifically limit the application range of the temporary habitat system.

[0095] The bottom of the aerial vehicle 11 in the drawings of the present application is also provided with a landing gear, but it does not undertake the main landing function, and the landing function of the aerial vehicle is still completed by the landing gear, and the landing gear at the bottom is only used to complete landing and parking in other suspension structures (the other suspension structures can be the suspension structures in the present application, or can be other types of suspension structures that can be adapted to the aerial vehicle) when the landing gear fails, is damaged, or the suspension structure has a fault, and the like, and the aerial vehicle cannot be parked in the suspension structure through the landing gear. In addition, the landing gear at the bottom can also be removed to further reduce the power consumption of the aerial vehicle in flight, and only the landing gear at the back of the aerial vehicle is retained.

[0096] In the present application, several means at least one, and more than one means. In the present application and / or the text content located in and / or before the text content, and the text content located in and / or after the text content can exist simultaneously, and can exist separately, for example, A and / or B includes only A or B, and A and B exist simultaneously. The present application discloses a plurality of technical solutions, but there is no opposite technical inspiration. The content of the present application is applicable to the prior art.

[0097] In the present application, specific examples are used to illustrate the principles and implementation modes of the present application, and the above examples are only used to help understand the method of the present application and its core idea; at the same time, for those skilled in the art, according to the idea of the present application, the specific implementation mode and application range will be changed. In view of the above, the content of the present application should not be understood as a limitation.

Claims

1. A landing gear, characterized in that, The landing gear is arranged on the back of the aircraft; The landing gear comprises a connecting member and a locking member; The first end of the connecting member is arranged to be connected to the back of the aircraft, and the side of the connecting member is provided with a plurality of locking members which are arranged to cooperate with the locking mechanism in the aircraft habitat device.

2. The landing gear of claim 1, wherein, The angle between the connecting member and the locking member is not greater than 90°; The connecting member comprises a habitat shaft, the first end of the habitat shaft is arranged to be connected to the back of the aircraft, and the side of the habitat shaft is provided with at least two locking members which are uniformly distributed along the circumference of the habitat shaft; The top of the connecting member is provided with a fixing member which is arranged to fix the landing gear on the aircraft habitat device.

3. A landing gear as claimed in claim 2, characterised in that, The fixing member comprises a fixing rod and a first driving device, the first end of the fixing rod is connected to the output end of the first driving device, the aircraft habitat device is provided with a fixing plate, and the first driving device is arranged to drive the fixing rod to move away from and close to the fixing plate; The fixing member comprises a clamping rod, and the side of the clamping rod is provided with a limiting block; The aircraft habitat device is provided with a clamping plate, the clamping plate is provided with a limiting hole and a limiting member, the limiting hole cooperates with the clamping rod and the limiting block, the limiting member is located at the top end of the clamping plate, the limiting member is arranged around the limiting hole, and the limiting member is arranged to limit the rotation of the limiting block.

4. A landing gear according to claim 1 or 2, characterised in that, The locking member comprises a habitat rod, one end of the habitat rod away from the habitat shaft is provided with a clamping member, the clamping member is arranged to avoid the locking mechanism, and the clamping member is arranged to extend out of the aircraft habitat device and to be attached to the aircraft habitat device.

5. A landing gear as claimed in claim 4, characterised in that, The clamping member comprises a limiting part which is arranged to be attached to the outer wall of the aircraft habitat device.

6. A drone, characterized in that, The unmanned aerial vehicle comprises the landing gear according to any one of claims 1-5, and the landing gear is arranged on the back of the unmanned aerial vehicle.

7. An aircraft, characterized in that The aircraft comprises the landing gear according to any one of claims 1-5, and the landing gear is arranged on the back of the aircraft.

8. A system for a parking apron, characterized in that The parking apron system comprises a plurality of aircraft habitat devices which are arranged at a height required for aircraft operation, and the number of the aircraft habitat devices corresponds to the requirement of aircraft operation; The aircraft habitat device comprises a channel and a locking mechanism; The channel is arranged to face the landing gear on the back of the aircraft, and the channel is arranged to allow the landing gear to enter and exit the aircraft habitat device; The locking mechanism is arranged to cooperate with the landing gear on the back of the aircraft to achieve unlocking and locking of the aircraft.

9. The apron system according to claim 8, characterized in that The side of the aircraft habitat device is provided with at least two locking mechanisms; The locking mechanism comprises a limiting part and a hanging part which are arranged in sequence along the rotation direction of the aircraft, the limiting part is arranged to limit the landing gear from leaving the aircraft habitat device, and the hanging part is arranged to carry the landing gear.

10. The apron system according to claim 9, characterized in that Three locking mechanisms are uniformly arranged along the side of the aircraft habitat device; And / or, the channel comprises a drainage groove and a hanging groove which are connected, the drainage groove is located at the limiting part, and the effective passing area of the hanging groove is smaller than that of the drainage groove. And / or, the hanging part comprises a hanging groove which is used to contact with a partial area of the side of the locking member in the landing gear.

11. The apron system according to claim 10, characterized in that The cross section of the hanging groove is in the shape of a cone, an arc, an inverted T or a trapezoid. And / or, the aircraft resting device is internally provided with a limiting plate which is used to be clamped or abutted with the top fixing member in the landing gear. And / or, the aircraft resting device is a cylinder. The bottom of the aircraft resting device is provided with an opening which is used for the landing gear to enter, and the opening is connected with a hollow cavity inside the aircraft resting device. The locking mechanism is arranged along the circumference of the aircraft resting device.

12. The apron system according to claim 9, characterized in that The hanging part comprises a plurality of supporting protrusions which are used to support the side of the locking member in the landing gear and contact with a partial area of the side of the locking member in the landing gear.

13. The apron system according to claim 12, characterized in that The supporting protrusions and the locking member are in point contact or line contact. And / or, the locking mechanism comprises a plurality of limiting parts which are arranged in sequence along the direction of the aircraft rotation, and the limiting parts on the upper side of the channel are arranged in a staggered manner with the limiting parts on the lower side of the channel.

14. An aircraft temporary habitat system, characterized by, The aircraft temporary resting system comprises: An aircraft resting device which adopts a hanging structure and is provided with a hanging resting part; A landing gear which is arranged at the top of the aircraft and is provided with a hanging matching part, and the landing gear is made of light material; The hanging matching part and the hanging resting part have a lapping matching state and a disengaging state, in the lapping matching state, the hanging matching part and the hanging resting part are lapped and matched from top to bottom, and the aircraft is in a resting state; in the disengaging state, the hanging matching part and the hanging resting part are disengaged, and the aircraft is in a flying state.

15. The aircraft interim habitat system of Claim 14, wherein, The aircraft temporary resting system further comprises a reference object which is arranged on the aircraft resting device or the periphery of the aircraft resting device, and an information acquisition element which is arranged on the aircraft and is signal connected with a control unit of the aircraft; And / or, the landing gear is fixedly arranged at the top of the aircraft; or, the landing gear is rotatably arranged at the top of the aircraft, and the rotation shaft of the landing gear is signal connected with a remote controller of the aircraft; And / or, the hanging matching part is lapped on the hanging resting part in a line contact or point contact manner; And / or, the landing gear comprises a resting shaft and a resting rod which is arranged on the resting shaft; one end of the resting shaft is connected with the top of the aircraft, the other end is provided with the resting rod, the axis of the resting rod and the axis of the resting shaft satisfy the perpendicular condition, and the hanging matching part is located on the outer circumferential wall of the resting rod.

16. The aircraft interim habitat system of Claim 15, wherein, The suspension structure comprises a suspension body in the form of a bottom-opened hollow shell, the suspension habitat is a suspension groove arranged on the suspension body, and the side wall of the suspension body is provided with a dredging groove capable of passing the habitat rod, each suspension groove corresponds to one dredging groove, the dredging groove extends upward from the bottom opening of the hollow shell and then extends along the outer circumferential direction of the hollow shell to communicate with the suspension groove; And / or, the upper part of the habitat shaft is provided with a fixing rod, the hollow shell is provided with an abutting part, the suspension matching part and the suspension habitat are in the lapping and matching state, and the fixing rod is in contact and pressed with the abutting part after being stretched to a preset length.

17. A method of temporarily inhabiting an aircraft, the method comprising: The application discloses an aircraft temporary habitat system and an aircraft temporary habitat method. The aircraft temporary habitat method comprises the following steps: realizing temporary habitat of the aircraft by hanging the landing gear at the top of the aircraft on the suspension structure of the aircraft habitat equipment.

18. The aircraft temporary perching method according to claim 17, wherein, The aircraft temporary habitat method further comprises the following steps: collecting reference information of a reference object by an information collection element, and controlling the flight state of the aircraft according to the reference information to adjust the coordinates and the attitude of the aircraft; and / or after the suspension matching part of the landing gear and the suspension habitat of the suspension structure are in the lapping and matching state, the fixing rod on the habitat rod is stretched out until the fixing rod is in contact and pressed with the abutting part in the suspension body.

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