Parking device for aircraft

Abstract

The utility model provides a parking device of an aircraft. The parking device comprises a parking platform, the hatch cover structure is configured to move relative to the parking platform so as to close the parking platform or open the parking platform; when the hatch cover structure moves relative to the parking platform, at least part of the hatch cover structure can drive the aircraft landing on the parking platform to move, so that the aircraft is located at the target position of the parking platform. According to the aircraft parking device provided by the utility model, the cost of the parking device can be reduced.

Description

[0001] This utility model is a divisional application of an application with an application date of June 21, 2023, application number 2023216075619, and name “Aircraft parking device and aircraft system”. Technical Field

[0002] The utility model relates to the technical field of aircraft, in particular to a parking device for an aircraft. Background Art

[0003] With the continuous development of science and technology and aircraft technology, aircraft have been widely used in many fields. In related technologies, after the aircraft lands on the parking platform, it will be stored and returned through a relatively complex actuation system, resulting in poor reliability and increased system costs. Utility Model Content

[0004] The utility model provides a parking device for an aircraft, aiming to improve the reliability of the parking device and reduce the cost.

[0005] An embodiment of the present invention provides a parking device for an aircraft, comprising:

[0006] Shuttle platforms; and

[0007] A hatch cover structure, wherein the hatch cover structure is configured to be movable relative to the parking platform to close the parking platform or open the parking platform;

[0008] Wherein, when the hatch cover structure moves relative to the parking platform, at least a part of the hatch cover structure can drive the aircraft landing on the parking platform to move so that the aircraft returns to the target position of the parking platform.

[0009] Another embodiment of the utility model further provides a parking device for an aircraft, comprising:

[0010] Parking platform;

[0011] a guide structure, provided on the parking platform, the guide structure being used to guide the aircraft to slide downward to a target position on the parking platform; and

[0012] A first wireless charging module is disposed at the target position;

[0013] Wherein, when the aircraft returns to the target position, the parking device can wirelessly charge the aircraft through the first wireless charging module, or the aircraft can wirelessly charge the parking device through the first wireless charging module.

[0014] It should be understood that the above general description and the following detailed description are merely exemplary and explanatory and cannot limit the disclosure of the embodiments of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate the technical solutions of the embodiments of the utility model, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are some embodiments of the utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0016] Figure 1 It is a structural schematic diagram of an aircraft system provided by an embodiment of the utility model;

[0017] Figure 2 It is a structural schematic diagram of an aircraft provided by an embodiment of the utility model;

[0018] Figure 3 yes Figure 2 A local enlarged schematic diagram at point A;

[0019] Figure 4 It is a structural schematic diagram of a parking device provided by an embodiment of the utility model;

[0020] Figure 5 It is a partial structural schematic diagram of an aircraft provided by an embodiment of the utility model, wherein the aircraft arm is shown;

[0021] Figure 6 It is a structural schematic diagram of an aircraft system provided by an embodiment of the utility model;

[0022] Figure 7 yes Figure 4 A local enlarged schematic diagram at B;

[0023] Figure 8 yes Figure 6 A local enlarged schematic diagram at C;

[0024] Fig. 9 It is a structural schematic diagram of an aircraft system provided by an embodiment of the utility model;

[0025] Fig.10 It is a structural schematic diagram of an aircraft system provided by an embodiment of the utility model;

[0026] Fig.11 It is a structural schematic diagram of an aircraft system provided by an embodiment of the utility model.

[0027] Description of reference numerals:

[0028] 1000. Aircraft systems;

[0029] 100, aircraft; 101, fuselage; 102, aircraft arm; 1021, root; 1022, tip; 103, power device; 1031, power motor; 1032, propeller; 1033, motor seat; 1034, matching part; 10341, curved force surface; 104, first supporting foot; 105, second supporting foot;

[0030] 200. Parking device;

[0031] 10. Parking platform; 11. Load-bearing surface;

[0032] 20. guide structure; 21. first surface; 22. second surface;

[0033] 30. functional component; 31. hatch cover structure; 311. first force applying part; 3111. curved force applying surface; 312. first hatch cover; 313. second hatch cover; 314. second force applying part; 3141. first side; 3142. second side;

[0034] 40. Limiting portion; 50. Driving member; 60. First transmission mechanism; 61. First transmission connecting rod; 70. Second transmission mechanism; 71. Second transmission connecting rod. DETAILED DESCRIPTION

[0035] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments of the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0036] In the description of the present utility model, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are 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, and therefore cannot be understood as a limitation on the present utility model. In addition, the terms "first" and "second" are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present utility model, the meaning of "multiple" is two or more, unless otherwise clearly and specifically defined.

[0037] It should also be understood that the terms used in the utility model specification are only for the purpose of describing specific embodiments and are not intended to limit the utility model. As used in the utility model specification and the appended claims, unless the context clearly indicates otherwise, the singular forms "a", "an" and "the" are intended to include plural forms.

[0038] It should be further understood that the term “and / or” used in the present specification and the appended claims refers to any combination and all possible combinations of one or more of the associated listed items, and includes these combinations.

[0039] In the related art, after the aircraft lands on the parking platform of the parking device, it will be stored and returned to the center through the actuation system. The actuation system includes an actuation motor and four actuation elements (such as an actuation connecting rod). The actuation motor drives the four actuation elements to move, so that the actuation elements drive the aircraft to move and return to the target position. For example, one actuation motor drives two of the actuation elements to move, so that the two actuation elements drive the aircraft to return in one direction; another actuation motor drives the other two actuation elements to move, so that the other two actuation elements drive the aircraft to return in another direction, and then the aircraft is returned to the target position. In some schemes, the actuation motor is also connected to the actuation element through a transmission mechanism. In this homing method, the structure of the actuation system is complex and there are many active connection lines, which will greatly increase the possibility of system failure, resulting in poor reliability. The unmanned parking device requires frequent maintenance and replacement, and increases the system cost. In addition, the complex actuation system, due to the necessary connections and activities, will cause the parking platform of the parking device to be connected up and down, which may easily cause water leakage from the top to the bottom of the parking platform, affecting the normal use of electrical components located below the parking platform and reducing the reliability of the parking device.

[0040] To this end, an embodiment of the utility model provides a parking device for an aircraft and an aircraft system to improve the reliability of the parking device and reduce the cost.

[0041] In conjunction with the accompanying drawings, some embodiments of the present invention are described in detail below. In the absence of conflict, the following embodiments and features in the embodiments can be combined with each other.

[0042] See also Figure 1 An embodiment of the utility model provides an aircraft system 1000 , and the aircraft system 1000 includes an aircraft 100 and a parking device 200 .

[0043] For example, the aircraft 100 may include a rotorcraft, a fixed-wing aircraft, a helicopter, or a fixed-wing-rotor hybrid aircraft, etc. The rotorcraft includes a single-rotor aircraft or a multi-rotor aircraft. The multi-rotor aircraft includes a two-rotor unmanned aerial vehicle, a three-rotor unmanned aerial vehicle, a four-rotor unmanned aerial vehicle, a six-rotor unmanned aerial vehicle, an eight-rotor unmanned aerial vehicle, a ten-rotor unmanned aerial vehicle, or a twelve-rotor unmanned aerial vehicle, etc.

[0044] See also Figure 1In some embodiments, the aircraft 100 includes a fuselage 101, a plurality of arms 102, and a power device 103 disposed on the arms 102. Exemplarily, the power device 103 is disposed at one end of the arm 102 away from the fuselage 101. Exemplarily, the power device 103 includes a power motor 1031 and a propeller 1032, the power motor 1031 is carried by the arm 102, and the power motor 1031 is in transmission connection with the propeller 1032 to drive the propeller 1032 to rotate, thereby providing flight power for the aircraft 100.

[0045] See also Figure 1 In some embodiments, the parking device 200 of the aircraft 100 includes a parking platform 10, a guide structure 20 and a functional component 30, wherein the guide structure 20 is used to guide the aircraft 100 to move along a first direction to approach a target position on the parking platform 10; the functional component 30 is used to perform a preset function of the parking device 200; wherein the functional component 30 is configured to be movable, and when the functional component 30 is movable, the functional component 30 can drive the aircraft 100 to move along a second direction so that the aircraft 100 returns to the target position, thereby enabling the functional component 30 to realize a positioning function other than the preset function, and the first direction intersects with the second direction.

[0046] The parking device 200 of the above embodiment has a guide structure 20 for guiding the aircraft 100 to move along a first direction to approach a target position on the parking platform 10; the functional component 30 of the parking device 200 is used to perform a preset function of the parking device 200, and the functional component 30 is configured to be movable. When the functional component 30 is movable, it can drive the aircraft 100 to move along a second direction so that the aircraft 100 returns to the target position, so that the functional component 30 realizes a positioning function other than the preset function, thereby expanding the application scope of the functional component 30 and diversifying the functions of the functional component 30. Through the cooperation of the guide structure 20 and the functional component 30, the parking device 200 does not need to be separately provided with a complex actuation system for driving the aircraft 100 to return to the target position, thereby reducing the number of components set, simplifying the structure of the parking device 200, greatly reducing the possibility of failure of the parking device 200, reducing the frequency of maintenance and replacement of the parking device 200, improving the reliability of the parking device 200, saving the cost of setting the actuation system, and greatly reducing the control cost.

[0047] In addition, the guide structure 20 can guide the aircraft 100 to move along the first direction to approach the target position, and the functional component 30 can realize the preset function and the positioning function. There is no need to separately set up an actuation system for realizing the return of the aircraft 100, thereby avoiding the need to connect the upper and lower parts of the parking platform 10 due to the setting of the actuation system, thereby preventing the parking platform 10 from easily leaking downward, and realizing a dry and friendly environment under the parking platform 10, avoiding the electrical components located under the parking platform from being unable to be used normally due to the downward leakage of the parking platform 10, thereby improving the reliability of the parking device 200.

[0048] For example, the schematic diagram of the aircraft 100 returning to the target position of the parking platform 10 is as follows: Figure 2 shown.

[0049] Exemplarily, the first direction is perpendicular to the second direction. When the aircraft 100 is returned to the target position of the parking platform 10 , the horizontal plane is perpendicular to the heading axis of the aircraft 100 .

[0050] Exemplarily, the first direction is perpendicular to the second direction. The gravity direction of the aircraft 100 is perpendicular to the plane formed by the first direction and the second direction.

[0051] See also Figure 2 and Figure 3 , illustratively, the projection of the first direction on the surface where the bearing surface 11 of the parking platform 10 is located is perpendicular to the second direction.

[0052] For example, the first direction is Figure 2 The X direction is shown in the second direction. Figure 3 The Y direction is perpendicular to the plane where the X direction and the Z direction are located.

[0053] In some embodiments, when the aircraft 100 lands and contacts the guide structure 20, the guide structure 20 can make the aircraft 100 move under the gravity of the aircraft 100, thereby guiding the aircraft 100 to move in the first direction. When the aircraft 100 contacts the guide structure 20, the gravity of the aircraft 100 can make the aircraft 100 move a certain trajectory in the first direction, so that the aircraft 100 approaches the target position on the parking platform 10, and there is no need to separately set up a first actuation system (including a first actuation motor and a first actuation element) for driving the aircraft 100 to return to a certain direction or drive the aircraft 100 to approach the target position, thereby reducing the number of components, simplifying the structure of the parking device 200, reducing the possibility of failure of the parking device 200, reducing the frequency of maintenance and replacement of the parking device 200, improving the reliability of the parking device 200, saving the cost of setting the first actuation system, and reducing the control cost.

[0054] Exemplarily, since the functional component 30 can drive the aircraft 100 to move along the second direction so that the aircraft 100 returns to the target position when it is active, the functional component 30 can realize a positioning function other than the preset function. Therefore, there is no need to separately set up a second actuation system (including a second actuation motor and a second actuation connecting rod) for driving the aircraft 100 to move along the second direction so that the aircraft 100 returns to the target position. The number of components set up is reduced, the structure of the parking device 200 is simplified, the possibility of failure of the parking device 200 is reduced, the frequency of maintenance and replacement of the parking device 200 is reduced, the reliability of the parking device 200 is improved, the cost of setting up the second actuation system is saved, and the control cost is reduced.

[0055] It is understandable that in the solution of using the first actuation system and / or the second actuation system to realize the return of the aircraft 100 , at least one of the first actuation system and the second actuation system needs to be made of hardware materials, thereby increasing the weight of the parking device 200 .

[0056] Exemplarily, the guide structure 20 and the functional component 30 can both be made of plastic, eliminating the need to use expensive hardware materials to prepare the first actuation system or the second actuation system, thereby reducing costs and reducing the weight of the parking device 200, facilitating transportation, movement and maintenance.

[0057] See also Figure 1 In some embodiments, the functional component 30 is configured to be movable relative to the parking platform 10. When the functional component 30 is movable, the functional component 30 can drive the aircraft 100 to move along the second direction so that the aircraft 100 returns to the target position, thereby enabling the functional component 30 to achieve a positioning function other than the preset function.

[0058] In some embodiments, the functional component 30 is configured to guide the aircraft 100 that has landed on the parking platform 10 to the target position along the second direction, that is, the aircraft 100 first moves to a position along the first direction, and then moves in the second direction, so that the aircraft 100 can move smoothly and reliably along the second direction under the action of the functional component 30, so that the aircraft 100 returns to the target position. In other embodiments, the functional component 30 can also be configured to guide the aircraft 100 that has landed on the guide mechanism 20 to the target position along the second direction, so that the aircraft 100 moves in the first direction and the second direction at the same time.

[0059] In some embodiments, the functional component 30 is configured to be active to perform a preset function, and at the same time drive the aircraft 100 to move along the second direction so that the aircraft 100 returns to the target position. In this way, the functional component 30 can simultaneously perform the preset function and drive the aircraft 100 to move along the second direction so that the aircraft 100 returns to the target position, thereby improving the functional execution efficiency of the functional component 30. Exemplarily, in the process of the functional component 30 performing the preset function, when the functional component 30 performs to a certain stage, as the functional component 30 continues to perform the preset function, the functional component 30 can simultaneously drive the aircraft 100 to move along the second direction so that the aircraft 100 returns to the target position. It should be noted that in other embodiments, the preset function and positioning function of the functional component 30 may not be performed at the same time.

[0060] In some embodiments, the angle between the first direction and the second direction is a right angle. In other embodiments, the angle between the first direction and the second direction may also be an obtuse angle or an acute angle.

[0061] See also Figure 3 , exemplarily, the first direction is parallel to the first surface 21 or the second surface 22 of the guide structure 20 .

[0062] Exemplarily, the guide structure 20 is connected to the parking platform 10 ; or, the guide structure 20 is formed on the parking platform 10 .

[0063] In some embodiments, the guide structure 20 includes at least one of the following: a V-shaped groove, a U-shaped groove, a C-shaped groove, etc. The guide structure 20 adopts a structural design of a V-shaped groove, a U-shaped groove, a C-shaped groove, etc., which can guide the aircraft 100 to move along the first direction so as to approach the target position of the parking platform 10, and adopts a physical structure to assist in positioning. There is no need to separately design a first actuation system for driving the aircraft 100 to move along the first direction to approach the target position or to realize the return of the aircraft 100 in a certain direction, thereby improving the reliability of the parking device 200, reducing the number of components, reducing costs, and significantly reducing control costs.

[0064] See also Figure 3 and Figure 4In some embodiments, the guide structure 20 includes a first surface 21 and a second surface 22, the first surface 21 and the second surface 22 are spaced apart, and the first surface 21 and the second surface 22 are arranged opposite to each other on the parking platform 10. The first surface 21 and the second surface 22 are inclined surfaces inclined relative to the parking platform 10, and the distance between the first surface 21 and the second surface 22 decreases from top to bottom. When the aircraft 100 lands, at least one of the first surface 21 and the second surface 22 can make the aircraft 100 slide down along the inclined surface under the action of the gravity of the aircraft 100, so that the aircraft 100 can simultaneously descend in the direction of gravity and move in the first direction, thereby approaching the target position on the parking platform 10. Exemplarily, when the aircraft 100 lands and contacts at least one of the first surface 21 and the second surface 22, the decomposition force of the gravity of the aircraft 100 on the surface where the first surface 21 or the second surface 22 is located can cause the aircraft 100 to slide along at least one of the first surface 21 and the second surface 22, so that the aircraft 100 can simultaneously descend in the direction of gravity and move in the first direction to approach the target position of the parking platform 10.

[0065] See also Figure 3 Exemplarily, the first surface 21 and the second surface 22 are inclined surfaces inclined relative to the bearing surface 11 of the parking platform 10 .

[0066] For example, see Figure 2 and Figure 3 , the angle between the first surface 21 (or the second surface 22) and the first direction is an acute angle or an obtuse angle.

[0067] It can be understood that if the inclination angle of the first surface 21 (or the second surface 22) is too small, it will be difficult for the guide structure 20 to allow the aircraft 100 to slide smoothly along the first surface 21 (or the second surface 22), thereby making it difficult for the guide structure 20 to smoothly guide the aircraft to move along the first direction to approach the target position on the parking platform 10; if the inclination angle is too large, the power unit 103 and the arm 102 of the aircraft 100 may easily interfere with the guide structure 20 during the process of the aircraft 100 sliding along the first surface 21 (or the second surface 22), and the configuration of the aircraft needs to be changed. In some embodiments, the inclination angle range of the first surface 21 or the second surface 22 is [15°, 45°], so as to ensure that the aircraft 100 can smoothly slide down along at least one of the first surface 21 and the second surface 22, so that the aircraft 100 can smoothly move along the first direction to approach the target position, avoiding the problem that at least one of the power device 103 and the arm 102 of the aircraft 100 is easy to collide with the guide structure 20 due to the change of the landing posture of the aircraft 100 (such as the change of posture caused by factors such as wind resistance or position adjustment), or the problem that the aircraft 100 is easy to get stuck when it slides to a certain position; and it can prevent the aircraft 100 from easily tilting or overturning during the sliding process. Exemplarily, the inclination angle range of the first surface 21 is [15°, 45°], such as the inclination angle is 15°, 20°, 30°, 40°, 45° or any other suitable value between 15°-45°. Exemplarily, the inclination angle of the second surface 22 ranges from [15°, 45°], such as the inclination angle is 15°, 20°, 30°, 40°, 45° or any other suitable value between 15° and 45°.

[0068] See also Figure 2 and Figure 5 In some embodiments, multiple arms 102 are connected to the fuselage 101, and the arms 102 are provided with a root 1021 and a tip 1022. The root 1021 is connected to the fuselage 101, and the tip 1022 is arranged opposite to the root 1021. The arms 102 gradually move away from the bottom of the aircraft 100 along the direction from the root 1021 to the tip 1022, so that the arms 102 of the aircraft 100 are tilted and upward to ensure that the guide structure 20 can smoothly guide the aircraft 100 to move along the first direction to approach the target position on the parking platform 10.

[0069] Exemplarily, the power device 103 is disposed at the tip 1022 of the arm 102 .

[0070] See also Figure 3In some embodiments, the aircraft 100 includes a first support leg 104 and a second support leg 105 that are spaced apart, and the first support leg 104 and the second support leg 105 are used to support the aircraft 100 on the support surface 11 of the parking platform 10. Exemplarily, the first surface 21 (or the second surface 22) is smoothly connected to the support surface 11, so that the guide structure 20 can more smoothly slide the aircraft 100 along the first surface 21 (or the second surface 22) to the support surface 11, so that the aircraft 100 can more smoothly move along the first direction to approach the target position.

[0071] See also Figure 3 In some embodiments, the spacing distance between the first support foot 104 and the second support foot 105 is d1, and the minimum spacing distance between the first surface 21 and the second surface 22 is d2, and d1 is less than or equal to d2, so that the aircraft 100 can smoothly move along the first direction to approach the target position on the parking platform 10, which provides a guarantee for the aircraft 100 to return to the target position, and prevents the first support foot 104 and the second support foot 105 from easily interfering with the guide structure 20 when the aircraft 100 slides down under the guidance of the guide structure 20. Exemplarily, d1 is slightly smaller than d2, such as the difference between d2 and d1 is greater than zero and less than a preset value, so as to prevent the first support foot 104 and the second support foot 105 from being stuck with the guide structure 20 when the aircraft 100 returns to the target position due to dust or the like at the contact point between the support foot and the guide structure 20, thereby affecting the normal take-off of the aircraft 100 from the parking device 200.

[0072] In some embodiments, the functional component 30 is configured to contact the arm 102 or the power device 103 of the aircraft 100 when it is active, so as to drive the aircraft 100 to move in the second direction. In this way, the structure of the functional component 30 is simple, and the interference or collision between the aircraft 100 and the functional component 30 can be minimized in the process of the functional component 30 driving the aircraft 100 to move in the second direction. For example, the functional component 30 is configured to contact the arm 102 of the aircraft 100 when it is active, so as to drive the aircraft 100 to move in the second direction. For another example, the functional component 30 is configured to contact the power device 103 of the aircraft 100 when it is active, so as to drive the aircraft 100 to move in the second direction. Exemplarily, the functional component 30 is configured to contact the power motor 1031 or the motor seat 1033 of the power device 103 when it is active, so as to drive the aircraft 100 to move in the second direction.

[0073] In some embodiments, the functional component 30 includes at least one of the following: at least part of the hatch cover structure 31, a component replacement mechanism (not shown), a material supply mechanism (not shown), etc. The hatch cover structure 31 is used to open or close the parking platform 10, the component replacement mechanism is used to replace the functional components on the aircraft 100, and the material supply mechanism is used to supply materials to the aircraft 100. The preset functions include at least one of the following: closing the hatch cover structure 31, replacing the functional components of the aircraft 100, and supplying materials to the aircraft 100.

[0074] See also Figure 1 For example, the functional component 30 includes at least part of a hatch cover structure 31, and the hatch cover structure 31 is used to open or close the parking platform 10. When the hatch cover structure 31 closes the parking platform 10, the hatch cover structure 31 can protect the aircraft 100 parked on the parking platform 10, shield the aircraft 100 from wind and rain, reduce the aging problem of the aircraft 100 caused by long-term exposure to the outdoor environment, and extend the service life of the aircraft 100.

[0075] For another example, the functional component 30 includes a component replacement mechanism, which is used to replace the functional components on the aircraft 100. Exemplarily, the functional components of the aircraft 100 may include at least one of the following: a battery module, a sensing module, etc. The sensing module is used to obtain the attitude information and / or surrounding environment information of the aircraft 100, and the surrounding environment information is used to achieve obstacle avoidance, etc. Exemplarily, the component replacement mechanism includes a component replacement manipulator, etc.

[0076] For another example, the functional component 30 includes a material supply mechanism, which is used to supply materials to the aircraft 100. Exemplarily, the material supply mechanism includes a material supply manipulator, etc. Exemplarily, the material includes at least one of the following: liquid medicine, solid material, water, etc. When the aircraft 100 is used in scenes such as agriculture or rescue, the aircraft 100 can spread materials to meet user needs.

[0077] For example, after the guide structure 20 completes guiding the aircraft 100 to move in the first direction, the functional component 30 moves to a certain position and contacts the aircraft 100; at this time, as the functional component 30 further moves, the functional component 30 can drive the aircraft 100 to move in the second direction so that the aircraft 100 returns to the target position. Figure 1 Exemplarily, the functional component 30 includes a hatch cover structure 31. After the guide structure 20 completes guiding the aircraft 100 to move in the first direction, at least part of the hatch cover structure 31 contacts the aircraft 100 when it moves to a certain position; at this time, with the further movement of at least part of the hatch cover structure 31, at least part of the hatch cover structure 31 can drive the aircraft 100 to move in the second direction so that the aircraft 100 returns to the target position.

[0078] See also Figure 1 and Figure 6 In some embodiments, the functional component 30 includes a hatch cover structure 31, and the hatch cover structure 31 is configured to move to close the parking platform 10 or open the parking platform 10; when the hatch cover structure 31 closes the parking platform 10, the hatch cover structure 31 can drive the aircraft 100 that has landed on the parking platform 10 to return to its position along the second direction. In the process of the hatch cover structure 31 closing the parking platform 10, as the hatch cover structure 31 moves to a certain position, the hatch cover structure 31 contacts the aircraft 100. At this time, as the hatch cover structure 31 further moves, the hatch cover structure 31 can drive the aircraft 100 to return to the target position along the second direction. Only a driving member 50 (see FIG. 5 ) designed to drive the hatch cover structure 31 to open or close is required. Fig. 9 ) can realize the return of the aircraft 100 along the second direction and the opening and closing of the canopy structure 31, without the need to separately set up a second actuation system for driving the aircraft 100 to return along the second direction, thereby reducing the number of components, simplifying the structure of the parking device 200, greatly reducing the possibility of failure of the parking device 200, reducing the frequency of maintenance and replacement of the parking device 200, improving the reliability of the parking device 200, and reducing the cost. It can be understood that when the canopy structure 31 opens the parking platform 10, the aircraft 100 can land on the parking platform 10, or the aircraft 100 parked on the parking platform 10 can also take off from the parking platform 10.

[0079] For example, the schematic diagram of the hatch cover structure 31 opening the parking platform 10 is as follows: Figure 1 The schematic diagram corresponding to the hatch cover structure 31 closing the parking platform 10 is shown in Figure 6 shown.

[0080] See also Figure 7 and Figure 8 In some embodiments, the canopy structure 31 is provided with a first force-applying portion 311, and the first force-applying portion 311 can contact the aircraft 100 and push the aircraft 100 to move so that the aircraft 100 returns to its position along the second direction. In the process of the canopy structure 31 closing the parking platform 10, when the canopy structure 31 moves to the point where the first force-applying portion 311 contacts the aircraft 100, if the canopy structure 31 moves further, the first force-applying portion 311 can apply a propulsive force to the aircraft 100 to push the aircraft 100 to move, so that the aircraft 100 returns to its target position along the second direction.

[0081] It is understandable that the number of the first force applying parts 311 can be set according to actual needs, such as one, two, three, four or more. For example, the number of the first force applying parts 311 includes four, two of which are used to return the aircraft 100 along the positive direction of the second direction, and the other two first force applying parts 311 are used to return the aircraft 100 along the negative direction of the second direction.

[0082] Exemplarily, each first force applying part 311 is used to contact different positions of the aircraft 100 to apply force. Exemplarily, the number of the first force applying parts 311 includes a plurality, and each first force applying part 311 is used to apply force to a power motor 1031 or a motor seat 1033 to push the aircraft 100 to move, so that the aircraft 100 returns to the target position along the second direction.

[0083] See also Figure 7 and Figure 8 In some embodiments, the first force applying part 311 includes a curved force applying surface 3111, which can contact the power device 103 of the aircraft 100 to drive the aircraft 100 to return to the second direction. In this way, the curved force applying surface adopts a curved surface design, which can reduce friction, so that the aircraft 100 can return to the target position more smoothly along the second direction.

[0084] See also Figure 8 Exemplarily, the power unit 103 includes a mating portion 1034. During the process of the hatch cover structure 31 closing the parking platform 10, the curved force-applying surface 3111 can contact the mating portion 1034, and the curved force-applying surface 3111 can apply force to the mating portion 1034 to drive the aircraft 100 to return to the target position along the second direction.

[0085] See also Figure 8 Exemplarily, the mating portion 1034 includes a curved force-bearing surface 10341. In the process of the canopy structure 31 closing the parking platform 10, the curved force-applying surface 3111 can contact the curved force-bearing surface 10341, and the curved force-applying surface 3111 can apply force to the curved force-bearing surface 10341 to drive the aircraft 100 to return to its position along the second direction. Exemplarily, the contact mode between the curved force-applying surface 3111 and the curved force-bearing surface 10341 can include at least one of the following: point contact, line contact, and surface contact. Exemplarily, the curved force-applying surface 3111 and the curved force-bearing surface 10341 both include curved surfaces, and the curved force-bearing surface 10341 has a different shape from the curved force-applying surface 3111.

[0086] In some embodiments, the angle between the force applied by the curved force-applying surface 3111 to the mating portion 1034 and the preset plane is in the range of [-15°, 15°], so as to ensure that the aircraft 100 can smoothly return to the target position along the second direction under the drive of the curved force-applying surface 3111, and prevent the aircraft 100 from easily tilting and overturning when the curved force-applying surface 3111 pushes the aircraft 100 to return along the second direction. Exemplarily, the angle between the force applied by the curved force-applying surface 3111 to the mating portion 1034 and the preset plane is -15°, 0°, 15°, or any other suitable value between -15° and 15°.

[0087] For example, the preset plane and Figure 2 The preset plane is perpendicular to the Z direction in FIG. 1 . For example, the preset plane is a horizontal plane. For example, the preset plane is parallel to the bearing surface 11 (see FIG. 1 ) for parking the aircraft 100 in the parking platform 10. Figure 3 ).

[0088] See also Figure 4 In some embodiments, the hatch cover structure 31 includes a first hatch cover 312 and a second hatch cover 313, and the first hatch cover 312 and the second hatch cover 313 cooperate to close the parking platform 10. When the first hatch cover 312 and the second hatch cover 313 move to close the parking platform 10, they can drive the aircraft 100 to move so that the aircraft 100 returns to the target position along the second direction.

[0089] Exemplarily, in the process of the first hatch cover 312 and the second hatch cover 313 moving to close the parking platform 10, the first hatch cover 312 can contact the aircraft 100 and push the aircraft 100 to return to the target position along the positive direction of the second direction, and the second hatch cover 313 can contact the aircraft 100 and push the aircraft 100 to return to the target position along the negative direction of the second direction. The positions in the aircraft 100 used to contact and apply force with the first hatch cover 312 and the second hatch cover 313 are different.

[0090] Exemplarily, the first hatch cover 312 and the second hatch cover 313 are arranged opposite to each other.

[0091] Exemplarily, the first hatch cover 312 and the second hatch cover 313 are respectively rotatably connected to the parking platform 10. Exemplarily, one side of the first hatch cover 312 is rotatably connected to the parking platform 10, and one side of the second hatch cover 313 is rotatably connected to the parking platform 10; the other side of the first hatch cover 312 and the other side of the second hatch cover 313 can be close to each other to close the bearing surface 11 of the parking platform 10, or move away from each other to open the bearing surface 11 of the parking platform 10.

[0092] In some embodiments, the parking device 200 also includes a first wireless charging module (not shown) disposed at the target position, and the aircraft 100 is provided with a second wireless charging module (not shown) used in conjunction with the first wireless charging module. When the first hatch 312 and the second hatch 313 are closed in place, the aircraft 100 is pushed to the target position so that the positions of the first wireless charging module and the second wireless charging module match. Through the first wireless charging module and the second wireless charging module, the parking device 200 can wirelessly charge the aircraft 100, or the aircraft 100 can wirelessly charge the parking device 200, without the need to use a connecting cable, and without the need for frequent plugging and unplugging during charging, thereby avoiding reliability issues caused by frequent plugging and unplugging, and the charging method is simple.

[0093] Exemplarily, when the functional component 30 returns the aircraft 100 to the target position, the parking device 200 can perform at least one of the following functions: charging, replacing functional components of the aircraft 100, replenishing materials of the aircraft 100, etc.

[0094] Exemplarily, when the functional component 30 returns the aircraft 100 to the target position, the positions of the first wireless charging module and the second wireless charging module match, and the parking device 200 can wirelessly charge the aircraft 100 , or the aircraft 100 can wirelessly charge the parking device 200 .

[0095] See also Figure 4 and Figure 7 In some embodiments, the hatch cover structure 31 is provided with a second force applying portion 314. When the hatch cover structure 31 closes the parking platform 10, the second force applying portion 314 can contact the blades of the aircraft 100 and drive the blades to fold. In addition to the functions of opening and closing the parking platform 10 and the above-mentioned positioning function, the hatch cover structure 31 can also fold the blades of the propeller 1032, thereby reducing the storage space of the aircraft 100, which is conducive to the miniaturization of the parking device 200, and expands the function of the functional component 30. There is no need to separately set up a third actuation system (including a third actuation motor) for folding the blades, which reduces the number of components set, simplifies the structure of the parking device 200, greatly reduces the possibility of failure of the parking device 200, reduces the frequency of maintenance and replacement of the parking device 200, improves the reliability of the parking device 200, and reduces the cost.

[0096] Exemplarily, during the process of the hatch cover structure 31 closing the parking platform 10, the second force applying part 314 can drive the blades of the propeller 1032 to fold. After the blades of the propeller 1032 are folded, as the hatch cover structure 31 further moves, the hatch cover structure 31 can drive the aircraft 100 to move in the second direction so that the aircraft 100 returns to the target position.

[0097] It is understandable that the number of the second force applying parts 314 can be set according to actual needs, such as one, two, three, four or more. Exemplarily, the number of the second force applying parts 314 is set corresponding to the number of the propellers 1032 of the aircraft 100. For example, the number of the second force applying parts 314 is the same as the number of the propellers 1032 of the aircraft 100, and each propeller 1032 is correspondingly provided with a second force applying part 314, so that when the hatch cover structure 31 closes the parking platform 10, each propeller 1032 can be folded under the action of the corresponding second force applying part 314.

[0098] Exemplarily, the second force applying portion 314 may be disposed at any suitable position of the hatch cover structure 31 , for example, the second force applying portion 314 may be disposed at a side wall of the hatch cover structure 31 .

[0099] See also Figure 7 , illustratively, the second force applying portion 314 includes a wedge-shaped surface, etc.

[0100] Exemplarily, when the hatch cover structure 31 opens the parking platform 10, the angle between the wedge-shaped surface of the second force-applying portion 314 and the horizontal plane is an acute angle. Exemplarily, when the hatch cover structure 31 is fully opened, the angle between the wedge-shaped surface of the second force-applying portion 314 and the bearing surface 11 of the parking platform 10 is an acute angle.

[0101] See also Figure 7 Exemplarily, the wedge-shaped surface includes a first side 3141 and a second side 3142 ; when the hatch cover structure 31 is opened into place, the first side 3141 and the second side 3142 are spaced apart and arranged opposite to each other, and the wedge-shaped surface is inclined downward from the first side 3141 toward the second side 3142 .

[0102] In some embodiments, the outer end of the blade of the aircraft 100 is pointed, so that the contact area between the blade and the second force-applying portion 314 is reduced, thereby preventing the blade from getting stuck during the process of pushing the blade to fold.

[0103] See also Fig. 9 In some embodiments, the parking device 200 further includes a driving member 50, which is used to drive the functional component 30 to move; and is used to drive the functional component 30 to perform a preset function of the parking device 200. The driving member 50 may include at least one of the following: a motor, an electric push rod, a pneumatic push rod, etc. Exemplarily, the driving member 50 is used to drive at least part of the hatch cover structure 31 to move.

[0104] See also Fig. 9 and Fig.10In some embodiments, the aircraft 100 further includes a limiter 40 for limiting the movement of the aircraft 100. When the canopy structure 31 closes the parking platform 10, the canopy structure 31 can cooperate with the limiter 40 to allow the aircraft 100 to return to its position along the second direction, wherein when the canopy structure 31 pushes the aircraft 100 to move in a preset direction, the limiter 40 is provided at the end of the target position of the aircraft 100 facing the preset direction, so that the aircraft 100 can accurately move to the target position along the second direction under the push of the canopy structure 31. Exemplarily, the preset direction is the movement direction of the aircraft 100 under the push of the canopy structure 31. Exemplarily, the preset direction is the positive direction or negative direction of the second direction.

[0105] For example, the schematic diagram corresponding to the hatch cover structure 31 being closed in place is as follows: Fig. 9 As shown. For example, the schematic diagram corresponding to the hatch cover structure 31 being opened to the full position is as shown Fig.10 shown.

[0106] In some embodiments, when the first hatch cover 312 and the second hatch cover 313 close the parking platform 10, the first hatch cover 312 can drive the parking platform 10 to move relative to the second hatch cover 313, and the first hatch cover 312 can push the aircraft 100 to move; the limit portion 40 is provided on the second hatch cover 313, and the limit portion 40 is used to limit the movement of the aircraft 100.

[0107] Exemplarily, the first hatch cover 312 is movable relative to the second hatch cover 313. In the process of the first hatch cover 312 and the second hatch cover 313 opening the parking platform 10, the first hatch cover 312 rotates relative to the second hatch cover 313 along the preset first rotation direction, and the first hatch cover 312 can drive the parking platform 10 to move relative to the second hatch cover 313 along the positive direction of the second direction, so that the first hatch cover 312 and the second hatch cover 313 open the parking platform 10. In the process of the first hatch cover 312 and the second hatch cover 313 closing the parking platform 10, the first hatch cover 312 rotates relative to the second hatch cover 313 along the preset second rotation direction, and the first hatch cover 312 can drive the parking platform 10 to move relative to the second hatch cover 313 along the negative direction of the second direction, so that the first hatch cover 312 and the second hatch cover 313 close the parking platform 10; wherein the first rotation direction is opposite to the second rotation direction. During the process of the first hatch cover 312 and the second hatch cover 313 closing the parking platform 10, the first hatch cover 312 can push the aircraft 100 to move in the negative direction of the second direction, and the limit portion 40 can limit the aircraft 100 from further moving in the negative direction of the second direction away from the target position, so that the aircraft 100 can move accurately to the target position along the second direction under the push of the hatch cover structure 31.

[0108] See also Fig. 9 and Fig.10In some embodiments, the parking device 200 further includes a driving member 50, a first transmission mechanism 60, and a second transmission mechanism 70. The driving member 50 is in transmission connection with the first hatch cover 312 to drive the first hatch cover 312 to move, so that the first hatch cover 312 and the second hatch cover 313 open or close the parking platform 10. The first hatch cover 312 is connected to the parking platform 10 through the first transmission mechanism 60, and the second hatch cover 313 is connected to the parking platform 10 through the second transmission mechanism 70; the first transmission mechanism 60 and the second transmission mechanism 70 are arranged so that the first hatch cover 312 can move to open or close the parking platform 10, and can push the parking platform 10 to move relative to the second hatch cover 313.

[0109] See also Fig. 9 , illustratively, the first transmission mechanism 60 includes a first transmission connecting rod 61 and the like. The second transmission mechanism 70 includes a second transmission connecting rod 71 and the like.

[0110] See also Fig.11 In some embodiments, the position limiting portion 40 is provided on at least one of the parking platform 10 and the first hatch 312, and the parking platform 10 is provided on the first hatch 312; when the first hatch 312 and the second hatch 313 close the parking platform 10, the aircraft 100 can slide down under the gravity of the aircraft 100; the position limiting portion 40 is used to limit the aircraft 100 from sliding down to the target position of the parking platform 10. Exemplarily, the position limiting portion 40 is provided on the parking platform 10. Exemplarily, the position limiting portion 40 is provided on the first hatch 312.

[0111] See also Fig.11 For example, during the process of the first hatch cover 312 moving to close the parking platform 10, the parking platform 10 can move synchronously with the first hatch cover 312; when the parking platform 10 moves to a certain angle relative to the horizontal plane, the aircraft 100 can slide down along the second direction under the action of the gravity of the aircraft 100, and there is no need to set a propulsion structure on the first hatch cover 312 to propel the movement of the aircraft 100, thereby simplifying the structure of the first hatch cover 312.

[0112] Exemplarily, the first hatch cover 312 is provided with a first force applying portion 311 , and when the first hatch cover 312 moves to close the parking platform 10 , the first force applying portion 311 can push the aircraft 100 to move so that the aircraft 100 moves along the second direction to the target position of the parking platform 10 .

[0113] See also Figure 1 and Figure 5The utility model also provides an aircraft system 1000, comprising an aircraft 100 and a parking device 200, the parking device 200 being used to park the aircraft 100, and the parking device 200 comprising the parking device 200 of any one of the above-mentioned embodiments. The aircraft 100 comprises a fuselage 101, a plurality of arms 102 and a power device 103 disposed on the arms 102, the plurality of arms 102 being connected to the fuselage 101, the arms 102 being provided with a root 1021 connected to the fuselage 101 and a tip 1022 disposed opposite to the root 1021, the arms 102 gradually moving away from the bottom of the aircraft 100 along the direction from the root 1021 to the tip 1022.

[0114] In the aircraft system 1000 of the above-mentioned embodiment, since the guide structure 20 of the parking device 200 is used to guide the aircraft 100 to move along the first direction to approach the target position on the parking platform 10; the functional component 30 of the parking device 200 is used to perform the preset function of the parking device 200, and the functional component 30 is configured to be movable. When the functional component 30 is movable, it can drive the aircraft 100 to move along the second direction so that the aircraft 100 returns to the target position, so that the functional component 30 realizes the positioning function beyond the preset function, thereby expanding the application scope of the functional component 30 and diversifying the functions of the functional component 30. Through the cooperation of the guide structure 20 and the functional component 30, the parking device 200 does not need to be separately provided with a complex actuation system for driving the aircraft 100 to return to the target position, the number of components set is reduced, the structure of the parking device 200 is simplified, the possibility of failure of the parking device 200 is greatly reduced, the frequency of maintenance and replacement of the parking device 200 is reduced, the reliability of the parking device 200 is improved, the cost of setting the actuation system is saved, and the control cost is also greatly reduced.

[0115] In addition, the guide structure 20 can guide the aircraft 100 to move along the first direction to approach the target position, and the functional component 30 can realize the preset function and the positioning function. There is no need to separately set up an actuation system for realizing the return of the aircraft 100, thereby avoiding the need to connect the upper and lower parts of the parking platform 10 due to the setting of the actuation system, thereby preventing the parking platform 10 from easily leaking downward, and realizing a dry and friendly environment under the parking platform 10, avoiding the electrical components located under the parking platform from being unable to be used normally due to the downward leakage of the parking platform 10, thereby improving the reliability of the parking device 200.

[0116] Exemplarily, the aircraft 100 includes the aircraft 100 of any one of the above embodiments.

[0117] In the description of the present utility model, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "mechanically coupled" and "coupled" 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. It can be the internal connection of two elements or the interaction relationship between two elements. The mechanical coupling or coupling of two components includes direct coupling and indirect coupling, for example, direct fixed connection, connection through a transmission mechanism, etc. For ordinary technicians in this field, the specific meanings of the above terms in the present utility model can be understood according to the specific circumstances.

[0118] In the present utility model, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0119] The disclosure above provides many different embodiments or examples for realizing different structures of the utility model. In order to simplify the disclosure of the utility model, the components and settings of specific examples are described above. Of course, they are only examples, and the purpose is not to limit the utility model. In addition, the utility model can repeat reference numbers and / or reference letters in different examples, and this repetition is for the purpose of simplification and clarity, and does not indicate the relationship between the various embodiments and / or settings discussed in itself. In addition, the utility model provides various specific examples of processes and materials, but those of ordinary skill in the art can be aware of the application of other processes and / or the use of other materials.

[0120] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "illustrative embodiments", "examples", "specific examples", or "some examples" means that the specific method steps, features, structures, materials or characteristics described in conjunction with the embodiments or examples are included in at least one embodiment or example of the utility model. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific method steps, features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

[0121] The above is only a specific implementation of the utility model, but the protection scope of the utility model is not limited thereto. Any technician familiar with the technical field can easily think of various equivalent modifications or replacements within the technical scope disclosed by the utility model, and these modifications or replacements should be included in the protection scope of the utility model. Therefore, the protection scope of the utility model should be based on the protection scope of the claims.

Claims

1. A parking device for an aircraft, characterized in that: include: Parking platform; as well as A hatch cover structure, wherein the hatch cover structure is configured to be movable relative to the parking platform to close the parking platform or open the parking platform; When the hatch cover structure moves relative to the parking platform, at least a portion of the hatch cover structure can drive the aircraft that has landed on the parking platform to move so that the aircraft returns to the target position of the parking platform.

2. The parking device according to claim 1, characterized in that: The parking device also includes a guide structure arranged on the parking platform; when the aircraft lands and contacts the guide structure, the guide structure can make the aircraft move under the action of the gravity of the aircraft, thereby guiding the aircraft to approach the target position.

3. The parking device according to claim 2, characterized in that: The guide structure includes at least one of the following: a V-shaped groove, a U-shaped groove, a C-shaped groove; and / or, The guiding structure comprises: First side; A second surface is formed on the parking platform opposite to the first surface and spaced apart therefrom. The first surface and the second surface are inclined surfaces inclined relative to the parking platform, and the distance between the first surface and the second surface decreases from top to bottom. When the aircraft lands, at least one of the first surface and the second surface can enable the aircraft to slide down under the action of the gravity of the aircraft.

4. The parking device according to any one of claims 1 to 3, characterized in that: The canopy structure is configured to contact the aircraft arm or power device when in motion, so as to drive the aircraft to move.

5. The parking device according to any one of claims 1 to 3, characterized in that: When the hatch cover structure closes the parking platform, the hatch cover structure can drive the aircraft that has landed on the parking platform to return to the target position.

6. The parking device according to any one of claims 1 to 3, characterized in that: The hatch cover structure comprises: A first hatch cover and a second hatch cover, the first hatch cover and the second hatch cover cooperate to close the parking platform, and the first hatch cover and the second hatch cover, when moving to close the parking platform, can drive the aircraft to move so that the aircraft returns to the target position.

7. The parking device according to claim 6, characterized in that: The parking device also includes a first wireless charging module arranged at the target position, and the aircraft is provided with a second wireless charging module used in conjunction with the first wireless charging module. When the first hatch and the second hatch are closed in place, the aircraft is pushed to the target position so that the positions of the first wireless charging module and the second wireless charging module match.

8. A parking device for an aircraft, characterized in that: include: Parking platform; A guide structure, provided on the parking platform, and used to guide the aircraft to slide downward to approach a target position on the parking platform; as well as A first wireless charging module is disposed at the target position; Wherein, when the aircraft returns to the target position, the parking device can wirelessly charge the aircraft through the first wireless charging module, or the aircraft can wirelessly charge the parking device through the first wireless charging module.

9. The parking device according to claim 8, characterized in that: The guide structure includes at least one of the following: a V-shaped groove, a U-shaped groove, and a C-shaped groove.

10. The parking device according to claim 8, characterized in that: The guiding structure comprises: First side; A second surface is formed on the parking platform opposite to the first surface and spaced apart therefrom. The first surface and the second surface are inclined surfaces inclined relative to the parking platform, and the distance between the first surface and the second surface decreases from top to bottom. When the aircraft lands, at least one of the first surface and the second surface can enable the aircraft to slide down under the action of the gravity of the aircraft.

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