Aircraft suspension device, mobile cutting equipment

Abstract

The present invention relates to the technical field of aircraft, and provides an aircraft suspension device and a mobile cutting device. The aircraft suspension device includes a telescopic device assembled to the aircraft through a connecting device; the telescopic device includes a first mounting seat for accommodating a first driving device, a driving plate driven by the first driving device and moving up and down along a first direction, two guiding plates provided with guiding grooves and arranged parallel to the first direction, a telescopic link mechanism and a driving rod clamped by the two guiding plates; the driving rod is hinged to the driving plate and the telescopic link mechanism, and drives the telescopic link mechanism to expand or contract under the drive of the first driving device, so as to integrally drive the guiding plates to move up and down along the first direction. Through the present invention, the flight stability of the aircraft is improved, and the telescopic distance of the mobile cutting device along the first direction and the structural stability of the mobile cutting device are improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and particularly to an aircraft suspension device and a mobile cutting device. Background Art

[0002] A drone is an aircraft that can be remotely controlled or fly autonomously, consisting of an aircraft and a control station. The aircraft includes a fuselage, a power device, and a navigation and flight control system, and can fly automatically or be remotely guided and can carry tools for aerial operations. It is widely used in industries such as industry, agriculture, and military. The drone can carry operation devices such as a spraying device, and realize various specific operations through a ground remote control or a GPS flight control system. For example, the drone is used for various specific operations such as sowing seeds, spraying pesticides, transporting items, or pruning shrubs and lawns.

[0003] In the above-mentioned operation scenarios, it is usually necessary to suspend specific operation devices on the fuselage of the drone, such as a medicine box for spraying pesticides or a cutting device for pruning shrubs and lawns. Since the operation devices are usually heavy in mass, during the processes of the drone flying such as accelerating, decelerating, and rotating, the above-mentioned operation devices will generate large displacements under the action of inertia, resulting in the drone stalling, rolling, or spinning. Therefore, it will pose a great potential safety hazard to the attitude control and flight safety of aircraft such as drones. In particular, in the operation scenario of pruning shrubs and lawns, the cutting devices mounted under the fuselage in the prior art usually cannot effectively perform the elongation / shortening operation, or have defects such as a small elongation / shortening operation range, or poor structural stability.

[0004] In view of this, it is necessary to improve the suspension device connecting the operation device and the fuselage of the specific operation performed by the drone in the prior art to solve the above problems. Summary of the Invention

[0005] The purpose of the present invention is to disclose an aircraft suspension device and a mobile cutting device, so as to solve the possible backward tilt, forward tilt, or swing of the aircraft during the flight processes such as accelerating, decelerating, or rotating of the aircraft mounted with the suspension device, improve the stability of the suspension device, and at the same time improve the flight stability of the aircraft and avoid flight accidents such as the aircraft crashing; at the same time, increase the telescopic distance of the mobile cutting device mounted on the aircraft in the vertical direction and the structural stability of the mobile cutting device.

[0006] To achieve one of the above purposes, the present application first provides an aircraft suspension device, including:

[0007] A telescopic device assembled to the aircraft through a connecting device;

[0008] The telescopic device includes a first mounting seat for housing a first driving device, a driving plate driven by the first driving device and moving up and down in a first direction, two guiding plates each having a guiding groove and arranged parallel to the first direction, a telescopic link mechanism clamped by the two guiding plates, and a driving rod;

[0009] The driving rod is hinged to the driving plate and the telescopic link mechanism, and drives the telescopic link mechanism to expand or contract under the drive of the first driving device, so as to integrally drive the guiding plates to move up and down in the first direction. The telescopic link mechanism and the guiding plates form a fixed hinge point and a moving hinge point.

[0010] As a further improvement of the present invention, the telescopic link mechanism includes two sets of symmetrically arranged and mutually hinged first folding rods, second folding rods and third folding rods. The first folding rod is hinged to the first mounting seat, and the driving rod is hinged to the driving plate and the first folding rod.

[0011] As a further improvement of the present invention, the distance between the hinge point formed by the driving rod and the first folding rod and the hinge point formed by the first folding rod and the first mounting seat is less than the distance between the hinge point formed by the driving rod and the first folding rod and the hinge point formed by the first folding rod and the second folding rod. The length of the first folding rod is greater than the length of the third folding rod.

[0012] As a further improvement of the present invention, the first driving device forms a first driving shaft that partially extends in the first direction over the driving plate and is provided with an external thread, and the driving plate is provided with an internal thread that meshes with the external thread of the first driving shaft.

[0013] As a further improvement of the present invention, one side of the two guiding plates close to the connecting device is separated from each other and the other side far from the connecting device is connected to each other. The two guiding plates are respectively provided with corresponding guiding grooves. The guiding grooves extend in the first direction and penetrate through the guiding plates or are arranged oppositely on the opposite inner sides of the two guiding plates.

[0014] As a further improvement of the present invention, the connecting device includes: a mounting plate, a receiving seat formed at the center of the mounting plate, a connecting rod extending into the receiving seat and being universally connected to the receiving seat, a hanging seat rigidly connected to the connecting rod, and a reset assembly for restoring the initial state formed by the hanging seat and the mounting plate. A connecting arm for movably hoisting the first mounting seat is provided at the bottom of the hanging seat;

[0015] An enlarged hole for the connecting rod to penetrate through is opened at the bottom of the receiving seat, and the diameter of the enlarged hole is greater than the diameter of the connecting rod.

[0016] As a further improvement of the present invention, a limiting block with a cavity is provided in the receiving seat, and a rotating body received by the limiting block and rotatable in all directions within the cavity formed by the limiting block, and the connecting rod vertically extends into the rotating body and is fixedly connected to the rotating body.

[0017] As a further improvement of the present invention, the reset assembly is composed of at least two torsionally elastic elements arranged axially symmetrically with respect to the connecting rod, and two end portions of the torsionally elastic element are connected to the end portion extending along the length direction of the mounting plate and the end portion of the hanging seat;

[0018] The torsionally elastic element is selected from a spring or an elastic rubber strip.

[0019] As a further improvement of the present invention, two bent portions with through holes are formed at the end of the mounting plate, and the reset assembly is composed of at least one torsion spring; the torsion spring forms two free ends extending through the bent portions, and the torsion spring is vertically penetrated and fixed by the connecting rod.

[0020] As a further improvement of the present invention, the connecting rod is provided with a positioning hole, and the torsion spring is composed of a spiral section and two free ends connected to the spiral section, and a positioning member penetrates through the spiral section and is placed in the positioning hole to limit the rotation of the torsion spring.

[0021] As a further improvement of the present invention, a contraction section for restricting the longitudinal movement of the spiral section is formed radially inward on the connecting rod, and the spiral section is embedded in the contraction section.

[0022] Based on the same inventive concept, the present application also provides a mobile cutting device, including:

[0023] The aircraft suspension device disclosed in any one of the above invention creations, and

[0024] A cutting device assembled below the guiding plate along the first direction;

[0025] The cutting device includes a second driving device provided at the bottom of two guiding plates, a protective cover, a cutting tool holder, and a plurality of blades transversely assembled with the cutting tool holder and rotatable within the area enclosed by the protective cover;

[0026] The cutting device is controlled by the aircraft suspension device and makes a telescopic movement along the longitudinal extension direction of the guiding plate as the telescopic link mechanism expands or contracts.

[0027] As a further improvement of the present invention, the mobile cutting device further includes: a protective shell that laterally partially shields the cutting tool holder;

[0028] The bottom of the guiding plate is connected to form a base, the protective shell is assembled at the bottom of the base, and the protective cover is formed by movably splicing two semi-circular cover bodies.

[0029] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0030] The aircraft suspension device and the mobile cutting device disclosed by the present invention effectively avoid the phenomena of backward tilt, forward tilt or swing that may occur during the flight of the aircraft, such as acceleration, deceleration or rotation of the aircraft, of the suspension device installed at the bottom of the fuselage of the aircraft. Thereby, the stability of the suspension device is improved, the stability of the aircraft is improved, and the flight accident of the aircraft crashing is avoided, and the telescopic distance of the mobile cutting device mounted on the aircraft in the first vertical direction and the structural stability of the mobile cutting device are improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1 Is a perspective view of an aircraft suspension device for assembling a cutting device at the bottom;

[0032] Figure 2 Is Figure 1 A perspective view of the connecting device in the aircraft suspension device shown;

[0033] Figure 3 Is along Figure 2 A sectional view taken along the A-A direction of the connecting device shown;

[0034] Figure 4 Is Figure 1 A perspective view of the hanging seat in the aircraft suspension device shown;

[0035] Figure 5 Is a perspective view of the telescopic device;

[0036] Figure 6 Is a perspective view of the cutting device at the bottom of the mounting plate configured in the telescopic device after being assembled with the mounting plate;

[0037] Figure 7 Is a partial sectional view of the mounting plate and the cutting device after being assembled;

[0038] Figure 8 Is a schematic diagram of the telescopic device stretched to the maximum stroke in the vertical direction;

[0039] Figure 9 Is a schematic diagram of the telescopic device stretched to the minimum stroke in the vertical direction;

[0040] Figure 10 Is a schematic diagram of multiple elastic torsion members that horizontally connect the hanging seat and the connecting plate recovering along the arrow K direction after being twisted;

[0041] Figure 11 Is a partial perspective view of the guide plate in the aircraft suspension device in a deformation example;

[0042] Figure 12Stereogram of the connecting device in a variant;

[0043] Figure 13 is Figure 12 front view of the connecting device shown;

[0044] Figure 14 is along Figure 13 sectional view taken along line H-H in;

[0045] Figure 15 is Figure 12 front view of the connecting device shown in a variant, with the mounting plate omitted;

[0046] Figure 16 is along Figure 15 sectional view taken along line J-J in;

[0047] Figure 17 Stereogram of an aircraft suspension device with a bottom assembly cutting device in another variant;

[0048] Figure 18 Schematic diagram of an aircraft equipped with the mobile cutting device of the present invention. Detailed implementation manners

[0049] The present invention will be described in detail below in conjunction with the various implementation manners shown in the drawings. It should be noted, however, that these implementation manners do not limit the present invention, and any equivalent transformation or substitution in function, method, or structure made by those of ordinary skill in the art based on these implementation manners shall fall within the protection scope of the present invention.

[0050] It should be understood that the orientation or positional relationship indicated by the terms "center", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present technical solution 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 thus should not be construed as a limitation to the present technical solution.

[0051] Example 1:

[0052] Refer Figures 1 to 11 to a specific implementation manner of an aircraft suspension device (hereinafter referred to as "suspension device") of the present invention shown. The bottom of the suspension device can hoist a specific actuator, and the actuator can be a cutting device for cutting crops, trees, shrubs or lawns, or a box for transporting items, or a water tank for high-rise building fire fighting, etc.

[0053] As Figure 1 shown in Figure 5 Figure 1, an aircraft suspension device includes a telescopic device 20 assembled to the aircraft through a connecting device 10. The connecting device 10 is assembled to the fuselage of the aircraft by using connecting parts such as bolts. During flight, the aircraft hoists the entire suspension device, and hoists the aforementioned actuator at the bottom of the suspension device to perform specific operations.

[0054] As Figure 2 shown in Figure 3 Figure 2, the connecting device 10 includes a mounting plate 101, a receiving seat 104 formed at the center of the mounting plate 101. The receiving seat 104 is located below the mounting plate 101. A connecting rod 105 extends into the receiving seat 104 and is universally connected to the receiving seat 104. A hanging seat 103 is rigidly connected to the connecting rod 105, and a reset assembly for restoring the initial state formed by the hanging seat 103 and the mounting plate 101. A connecting arm 1031 for movably hoisting a first mounting seat 201 is provided at the bottom of the hanging seat 103. The connecting arm 1031 symmetrically forms a bending portion 1032 inward. A bolt 106 passes through the bending portion 1032. The bolt head 1062 of the bolt 106 is placed above the bending portion 1032. The bolt 106 passes through a through hole 2101, and after being assembled with a nut 1061, the nut 1061 and the bending portion 1032 clamp the top plate 210 up and down, thereby fixedly assembling the connecting device 10 and the first mounting seat 201. In this embodiment, the connecting device 10 is assembled above the first mounting seat 201. At the same time, a plurality of waist-shaped holes 1011 are formed in the mounting plate 101 to reliably fix the mounting plate 101 to the fuselage of the aircraft by bolts.

[0055] The bottom of the receiving seat 104 is provided with an enlarged hole 144 for the connecting rod 105 to penetrate through, and the diameter of the enlarged hole 144 is larger than the diameter of the connecting rod 105. A limiting block 114 with a cavity is arranged in the receiving seat 104, and a rotating body 134 received by the limiting block 114 and capable of rotating in all directions within the cavity 1140 formed by the limiting block 114. The connecting rod 105 vertically extends into the rotating body 134 and is fixedly connected to the rotating body 134. The rotating body 134 can be spherical or ellipsoidal or any other structure capable of rotating in all directions in the cavity 1140. An insertion section 115 is arranged at the top of the connecting rod 105. The rotating body 134 forms an installation channel 1341 along the central axis 500 for the insertion section 115 to longitudinally penetrate through the rotating body 134. A snap ring 124 can be arranged at the end of the insertion section 115 at its top to limit the longitudinal disengagement of the insertion section 115 from the installation channel 1341. Of course, the snap ring 124 can also be omitted, and the inner wall surface of the installation channel 1341 is provided with internal threads, while the outer wall of the insertion section 115 is provided with external threads, so that the insertion section 115 is screwed into the installation channel 1341 in a spiral manner, and the rigid connection between the connecting rod 105 and the rotating body 134 is ensured.

[0056] The mounting plate 101 is preferably axially symmetric with respect to the central axis 500. At the same time, an opening 1010 is arranged at the axial symmetry center of the top of the mounting plate 101, and the diameter of the opening 1010 is larger than the diameter of the enlarged hole 144 located below, so as to facilitate the limiting block 114 to longitudinally insert and hold on the inner wall surface of the receiving seat 104. The receiving seat 104 and the mounting plate 101 can be of an integral structure.

[0057] At the same time, in this embodiment, the thickness of the limiting block 114 formed along the central axis 500 direction is smaller than the thickness of the rotating body 134 formed along the central axis 500 direction. The diameter of the enlarged hole 144 is larger than the diameters of the rotating body 134 and the cavity 1140 in the transverse direction, so as to ensure that the connecting rod 105 can drive the rotating body 134 to swing in all directions relative to the plane where the mounting plate 101 is located in the cavity 1140. When the extending direction of the mounting plate 101 is the same as the flight direction of the aircraft, when the aircraft is accelerating or decelerating, the connecting rod 105 swings from the state of the central axis 100 formed by the uniform horizontal flight state to Figure 3 the state of the central axis 100b and the state of the central axis 100a. Figure 3 The central axis 100 in Figure 1 coincides with the central axis 500 in the vertical direction and is a typical example of the first direction.

[0058] When the aircraft is in rotary flight or affected by air currents, the connecting rod 105 will rotate and swing in any posture around the central axis 100, thus forming a range of rotary swing in the shape of a cone. At this time, the center of gravity and posture of the aircraft will be greatly disturbed. Therefore, in this embodiment, at least two torsion elastic elements arranged axially symmetrically with respect to the connecting rod 105 are introduced to counteract the rotary swing. The tension and / or torsion generated by the torsion elastic elements act on the hanging seat 103 configured below the connecting rod 105 and the cutting device 30 assembled below the telescopic device 20 (see Figure 6 shown), correcting the postures of the hanging device and the cutting device, effectively ensuring the stability and accuracy of the hanging device and the cutting device, and also effectively preventing the interference of the center of gravity and flight posture of the aircraft caused by the cutting device 30 when the aircraft accelerates, decelerates, rotates or is affected by huge air currents during the hoisting of the cutting device 30 and other actuators, effectively avoiding phenomena such as rotation, rollover or crash of the aircraft.

[0059] The reset assembly is composed of at least two torsion elastic elements arranged axially symmetrically with respect to the connecting rod 105. The two ends of the torsion elastic element are connected to the end extending along the length direction of the mounting plate 101 and the end of the hanging seat 103. The torsion elastic element is selected from a spring or an elastic rubber strip. Specifically, in this embodiment, the reset assembly is composed of two torsion elastic elements arranged axially symmetrically with respect to the connecting rod 105. Of course, the reset assembly can also be composed of three, four or more torsion elastic elements arranged axially symmetrically with respect to the connecting rod 105 to achieve the correction ability to correct the posture of the hanging seat 103 configured below the connecting rod 105 within a larger swing range. The mounting plate 101 is axially symmetric with respect to the central axis 100, and three, four or more torsion elastic elements are arranged axially symmetrically with respect to the connecting rod 105, defining the reset assembly.

[0060] See Figure 2 and Figure 3 shown. In this embodiment, the torsion elastic element is specifically a spring 102. The hanging seat 103 is provided with a hook seat 1030 at the end in the transverse direction for hooking one end of the spring 102, and the mounting plate 101 is provided with a hook seat 1012 at the end extending along its length direction for hooking the other end of the spring 102. Combining Figure 10 shown, when the hanging device is vertically arranged, the hanging seat 103 and the mounting plate 101 coincide with each other in the top view angle, and the spring 102 extends along Figure 10The direction shown by the central axis 200 is symmetrically inclined with respect to the connecting rod 105, thereby defining the so-called initial state formed by the hanging seat 103 and the mounting plate 101. Of course, this initial state does not specifically limit that the hanging seat 103 and the mounting plate 101 must coincide with each other from a top-down perspective. For example, the hanging seat 103 and the mounting plate 101 can also be in a cross-shaped intersection posture from a top-down perspective.

[0061] In this embodiment, when the two springs 102 (a lower concept of the torsion elastic element) for restoring the initial state formed by the hanging seat 103 and the mounting plate 101 are twisted, the two springs 102 elongate. At this time, the springs 102 will generate a contraction force and a torsion restoring force, so as to Figure 10 restore to the initial state in the direction shown by the arrow K and restore from the state of the spring 102a to the state of the spring 102, thereby adjusting the state between the hanging seat 103 and the mounting plate 101 and restoring to the initial state. At the same time, the torsion elastic element can also be a rod-shaped damper (not shown), and the ends of the rod-shaped damper are respectively connected to the hook seat 1012 and the hook seat 1030 through universal joints (not shown).

[0062] Refer Figure 1 、 Figure 5 、 Figure 8 and Figure 9 As shown in, the telescopic device 20 includes a first mounting seat 201 for accommodating the first driving device 21, a driving plate 26 driven by the first driving device 21 and moving up and down along the first direction, two guiding plates 27 having guiding grooves 271 and arranged parallel to the first direction, a telescopic link mechanism clamped by the two guiding plates 27, and a driving rod 22. The driving rod 22 is hinged to the driving plate 26 and the telescopic link mechanism, and drives the telescopic link mechanism to expand or contract under the drive of the first driving device 21, so as to drive the guiding plates 27 to move up and down along the first direction as a whole. The telescopic link mechanism and the guiding plates 27 form a fixed hinge point 284 and a moving hinge point 244. When the telescopic device 20 makes an elongation movement along the first direction, the fixed hinge point 284 and the moving hinge point 244 move away from each other (refer Figure 8 shown), and at this time, the moving hinge point 244 is located at the upper limit point of the guiding groove 271. When the telescopic device 20 makes a shortening movement along the vertical direction, the fixed hinge point 284 and the moving hinge point 244 move closer to each other (refer Figure 9As shown in the figure, at this time, the moving hinge point 244 is located at the lower limit point of the guiding groove 271. Among them, the first direction can be the vertical direction (or perpendicular direction), or any direction at an angle to the vertical direction, and there is no limitation here. When the first direction is any direction at an angle to the vertical direction, the connecting device and the suspension device remain rigidly connected to the aircraft, so that the suspension device can be automatically and precisely controlled to expand and contract. Thus, the cutting device 30 connected to the bottom of the suspension device in the first embodiment can trim and cut objects such as crops, trees, shrubs, or lawns at any angle, improving the adaptability of the mobile cutting device disclosed in the third embodiment and being able to adapt to various complex usage environments.

[0063] The first driving device 21 forms a first driving shaft 212 that extends partially along the first direction across the driving plate 26 and is provided with external threads, and the driving plate 26 is provided with internal threads that mesh with the external threads of the first driving shaft 212. As Figure 4 and Figure 5 shown, the first mounting seat 201 is composed of a top plate 210, a side plate 217 rigidly connected to the top plate 210, and a bottom plate 215. The side plate 217 and the bottom plate 215 can be an integral structure. The top plate 210 is provided with a mounting hole 213 for the first driving device 21 to penetrate through on the central axis 500, and a mounting hole 214 coaxial with the mounting hole 213 in the first direction is opened on the bottom plate 215, and a plurality of through holes 2150 for fixing the first driving device 21 are arranged on the radial outer side of the mounting hole 214. Preferably, in this embodiment, the driving plate 26 is provided with a flange nut 25 with internal threads along the central axis 500, and the first driving shaft 212 extends downward through the flange nut 25.

[0064] The first driving shaft 212 of the first driving device 21 extends downward through the mounting hole 214. A positioning hole (not shown) that coincides with the through hole 2150 is opened on the circular end surface of the first driving device 21 configured with the first driving shaft 212, so that bolts pass through the through hole 2150 from bottom to top and extend into the positioning hole of the first driving device 21, so as to reliably fix the first driving device 21 in the open mounting space 216 formed by enclosing the top plate 210, the side plate 217, and the bottom plate 215, improving the space utilization rate of the first mounting seat 201 in the connecting device 10.

[0065] At the same time, in order to reduce the weight of the suspension device, a plurality of hollow holes 2121 can be opened on the side plate 217, and the specific shape does not need to be specifically defined. At the same time, through holes 2101 are opened on the lateral sides of the top plate 210 located on both sides of the mounting hole 213, Figure 2 and Figure 3In the connecting device 10, the two bolts 106 at the bottom are longitudinally inserted into the aforementioned through holes 2101 and locked, so as to realize a reliable longitudinal connection between the connecting device 10 and the telescopic device 20. In particular, it should be noted that in the embodiments of the present application, the aforementioned " Horizontal sides " in " Horizontal " refers to the direction formed by the telescopic link mechanism in the telescopic device 20 at the vertical projection angle. " Vertical " refers to the direction formed by coinciding with or being parallel to the central axis 500. Hinge seats 218 are provided on the transverse two sides of the top plate 210, and hinge holes 2180 are provided in the hinge seats 218.

[0066] The guiding plates 27 arranged in parallel with the first direction are separated from each other on the side close to the connecting device 10 and connected to each other on the side far from the connecting device 10. Guiding grooves 271 extending in the first direction are respectively provided on the two guiding plates 27, and the guiding grooves 271 penetrate through the guiding plates 27 (see Figure 5 and Figure 6 ) or the guiding grooves 271a are oppositely arranged on the opposite inner sides of the two guiding plates 27a (see Figure 11 ).

[0067] Specifically, as shown in Figure 5 and Figure 6 , in the embodiment, the two guiding grooves 271 formed by penetrating the guiding plates 27 are parallel to each other. The two ends of the shaft portion 246 of the second folding rods 24 that are arranged in a crossed and hinged manner are embedded in the guiding grooves 271, and move along the first direction in the guiding grooves 271 as the driving plate 26 reciprocates back and forth along the first direction in the guiding grooves 271. In particular, during the process of the telescopic link mechanism expanding or folding, the connection line between the fixed hinge point 284 and the moving hinge point 244 can always be kept in the same direction as the extension direction of the guiding grooves 271, thereby preventing the cutting device 30 assembled at the bottom of the telescopic device 20 from rotating relative to the shaft portion 282 of the third folding rods 28 that are arranged in a crossed and hinged manner, thus improving the stability of the telescopic device 20 during the elongation or shortening operation process and the overall structural strength of the telescopic device 20.

[0068] With reference to Figure 6 shown, the two ends of the shaft portion 282 penetrate through two pin holes 272 opened at the bottom of the guiding plates 27, and nuts are provided at the two ends of the shaft portion 282. During the process of the telescopic link mechanism expanding or folding, the shaft portion 246 and the shaft portion 282 always maintain a parallel posture and move closer to or away from each other. See Figure 11As shown, the guiding groove 271a is disposed oppositely on the inner sides of the two guiding plates 27a facing each other. Guide blocks that are movably inserted into the guiding groove 271a are provided at both end portions of the shaft portion 282. The guide blocks can be nuts or sliders screwed onto both end portions of the shaft portion 282. The shaft portion 282 passes through a strip-shaped opening 272a that is opened on the inner side of the guiding plates 27a facing each other and is arranged parallel to and along the first direction. During the expansion or contraction of the telescopic link mechanism, the moving hinge point 244 reciprocates back and forth along the first direction in a horizontal posture relative to the first direction along the guiding groove 271a and the strip-shaped opening 272a.

[0069] As shown in Figure 5 In this embodiment, the telescopic link mechanism is composed of two sets of symmetrically arranged and mutually articulated first folding rods 23, second folding rods 24, and third folding rods 28. The first folding rod 23 is articulated with the first mounting seat 201, and the driving rod 22 is articulated with the driving plate 26 and the first folding rod 23. The distance between the hinge point formed by the driving rod 22 and the first folding rod 23 and the hinge point formed by the first folding rod 23 and the first mounting seat 201 is less than the distance between the hinge point formed by the driving rod 22 and the first folding rod 23 and the hinge point formed by the first folding rod 23 and the second folding rod 24. The length of the first folding rod 23 is greater than the length of the third folding rod 28. Thereby, the telescopic distance formed by the telescopic link mechanism along the first direction can be increased, and at the same time, the overall stability of the suspension device can be ensured.

[0070] As shown in Figures 4 to 6 , Figure 8 and Figure 9 As shown in, the two sets of first folding rods 23, second folding rods 24, and third folding rods 28 are symmetrically arranged and are sequentially articulated, that is, the first folding rod 23 is articulated with the second folding rod 24, and the second folding rod 24 is articulated with the third folding rod 28. At the same time, the first folding rods 23, second folding rods 24, and third folding rods 28 are each articulated, that is, the first folding rods 23 are symmetrically arranged and articulated to the first mounting seat 201, the second folding rods 24 are symmetrically arranged and articulated to the moving hinge point 244, and the third folding rods 28 are symmetrically arranged and articulated to the fixed hinge point 284. The telescopic link mechanism always makes a telescopic movement between the planes formed by the two guiding plates 27 arranged parallel to and along the first direction. An end portion of the first folding rod 23 close to the hinge seat 218 is provided with a shaft portion 235 articulated to the hinge seat 218. Both ends of the shaft portion 235 pass through the hinge holes 2180, and nuts 236 are screwed onto both end portions of the shaft portion 235. The shaft portion 235 coincides with shaft b. The first folding rod 23 rotates around Figure 5The central axis b rotates. The two driving rods 22 are arranged in an inclined and outward-expanded shape and are symmetrically arranged with respect to the first mounting seat 201, and are supported against the lower part of the two first folding rods 23 close to the first mounting seat 201. A shaft portion 221 is provided at the bottom of the driving rod 22, and the shaft portion 221 is hinged to the hinge seats 222 at the transverse two ends of the driving plate 26, and the hinge seat 222 coincides with the axis c. When the first driving shaft 212 rotates clockwise, it pushes the flange nut 25 and the driving plate 26 to move downward along the central axis 500 in a horizontal posture. When the first driving shaft 212 rotates counterclockwise, it pulls the flange nut 25 and the driving plate 26 to move upward along the central axis 500 in a horizontal posture, and by means of the two driving rods 22 located in the same plane and axially symmetric with respect to the central axis 500, the first folding rod 23 is propped up or pulled to realize driving the first folding rod 23 to rotate around the axis b. The driving rod 22 is hinged to the driving plate 26 and rotates along Figure 5 the central axis c. The end of the driving rod 22 far from the shaft portion 221 is hinged to the first folding rod 23 to form a hinge point 223. During the process of the first folding rod 23 rotating around the axis b, the top of the driving rod 22 rotates around the axis a, and the hinge point 223 coincides with the axis a. The distance between the axis a and the axis b is greater than the distance between the axis a and the axis c, so that when the first driving shaft 212 rotates to drive the driving plate 26 to move along the central axis 500, that is, along the first direction (when the first direction is the vertical direction, the driving plate 26 moves up and down in a horizontal posture), it can move within a relatively small range to realize a larger range of expansion (refer to Figure 9 shown) or folding (refer to Figure 8 shown) of the two first folding rods 23. Thus, on the premise of shortening the length of the first driving shaft 212, the telescopic link mechanism can achieve a larger telescopic range. At the same time, since the axes a, b, and c are arranged in a triangle in the same plane, the whole telescopic link mechanism is more stable.

[0071] A sleeve 231 is provided at the end of the first folding rod 23 close to the first mounting seat 201, and a sleeve 232 is provided at the other end far from the first mounting seat 201. A hinge seat 233 is provided at the end of the sleeve 232. One end of the second folding rod 24 is provided with a shaft portion 240 that is movably hinged to the hinge seat 233. Both ends of the shaft portion 240 pass through the hinge seat 233 and nuts are screwed at both ends of the shaft portion 233 to lock. The first folding rod 23 and the second folding rod 24 form a hinge point 234, and the first folding rod 23 and the second folding rod 24 rotate relative to each other around the axis d, and the hinge point 234 coincides with the axis d. When the two first folding rods 23 perform the expansion action, the included angle between the first folding rod 23 and the second folding rod 24 decreases. When the two first folding rods 23 perform the folding action, the included angle between the first folding rod 23 and the second folding rod 24 increases. During the above-mentioned actuation process, the first folding rod 23 and the second folding rod 24 rotate around the axis d through the hinge point 234.

[0072] A sleeve 241 is provided at one end of the second folding rod 24 close to the hinge point 234, and the shaft portion 240 is provided at the end of the sleeve 241. The shaft portions 246 are formed by two second folding rods 24 arranged in a cross configuration, and nuts are arranged at both ends of the shaft portion 246 and located outside the guiding groove 271. A sleeve 245 is provided at the second folding rod 24 close to the guiding plate 27, and the sleeve 245 is coaxially provided with a hinge seat 247, and the hinge seat 247 is held in the air by two guiding plates 27. The other second folding rod 24 is arranged in a cross configuration with the hinge seat 247 and is provided with a shaft portion 246 that continuously penetrates through the two second folding rods 24. Both ends of the shaft portion 246 extend through the two guiding plates 27, so as to form a movable hinge point 244 at the intersection of the two second folding rods 24 arranged in a cross configuration and hinged to each other. The movable hinge point 244 coincides with the shaft e, and the fixed hinge point 284 coincides with the shaft g.

[0073] During the process that the movable hinge point 244 reciprocates back and forth in the guiding groove 271 in the first direction, the shaft e formed by the shaft portion 246 always remains perpendicular to the plane formed by the first folding rod 23 and the second folding rod 24. A shaft portion 242 is provided at the end of the second folding rod 24 extending through the guiding plate 27 and is hinged to a hinge seat 281 formed at the end of the third folding rod 28 close to the second folding rod 24. Both ends of the shaft portion 242 penetrate through the hinge seat 281 and are fixed by nuts 243, and the shaft portion 242 coincides with the shaft f. The second folding rod 24 and the third folding rod 28 rotate around the shaft f. The bottoms of the two third folding rods 28 cross and are hinged, and a structure similar to that at the intersection of the two second folding rods 24 described above is provided at the intersection of the two third folding rods 28. A shaft portion 282 is provided at the bottom end of one of the third folding rods 28, and the shaft portion 282 passes through the two guiding plates 27 and is fixed by nuts. The two third folding rods 28 rotate around the shaft g during the process of the telescopic link mechanism extending or shortening, and the position of the shaft g relative to the guiding plate 27 always remains unchanged.

[0074] Refer Figure 9 As shown, when the angle between the first folding rod 23 and the second folding rod 24 decreases, the movable hinge point 244 gradually moves downward and reaches the lower limit point of the guiding groove 271. At this time, the first folding rod 23 is in the state of the first folding rod 23b, the second folding rod 24 is in the state of the second folding rod 24b, and the third folding rod 28 is in the state of the third folding rod 28b.

[0075] Refer Figure 8 As shown, when the angle between the first folding rod 23 and the second folding rod 24 increases, the movable hinge point 244 gradually moves upward and reaches the upper limit point of the guiding groove 271. At this time, the first folding rod 23 is in the state of the first folding rod 23a, the second folding rod 24 is in the state of the second folding rod 24a, and the third folding rod 28 is in the state of the third folding rod 28a.

[0076] During the extension or contraction of the telescopic link mechanism, the aforementioned axis a, axis b, axis c, axis d, axis e, axis f and axis g are all kept parallel and perpendicular to the plane formed by the first folding rod 23, the second folding rod 24 and the third folding rod 28. During the up and down movement of the driving plate 26 along the central axis 500 driven by the first driving device 21, the axis a, the axis b and the axis c always form a triangular hinged assembly relationship together, thereby making the overall structure of the telescopic link mechanism more stable. The two groups of axis a, the axis b and the axis c on the lateral sides of the first driving device 21 always maintain synchronous deformation.

[0077] Since an aircraft may perform acceleration, deceleration, constant speed level flight, turns, pull-ups and other maneuvers during flight, the suspension device installed on the aircraft cannot maintain a stable posture due to inertia. Therefore, the suspension device in this embodiment can restore its posture through a connecting device 10 that is directly or indirectly connected to the aircraft. The recovery process is achieved through one or more torsion elastic elements in this embodiment, so as to avoid the center of gravity of the overall device formed by the connecting rod 105 rigidly and universally connected to the receiving seat 104 and the telescopic device 20 hoisted under the connecting rod 105 from fluctuating up and down, left and right, thereby improving the stability and safety of the aircraft flight; at the same time, the stability of the suspension device is improved, ensuring that the telescopic connecting rod mechanism contained in the hoisted telescopic device 20 always maintains a vertical posture during the operation of expanding or contracting, reducing the lateral pressure of the shaft 282 forming the moving intersection 244 on the two guide plates 27 (or guide plates 27a), so that the shaft 282 moves as much as possible in the area defined by the two guide plates 27 (or guide plates 27a), and improving the telescopic operation accuracy of the telescopic connecting rod mechanism.

[0078] Preferably, Figure 17 As shown, in this embodiment, at least one power supply mounting seat is configured to protrude laterally from the top of the first mounting seat 201, namely, the power supply mounting seat 251 and the power supply mounting seat 252. The power supply mounting seat is used to accommodate an energy storage device (not shown), and an electrical connection is established between the energy storage device and the first driving device 21 and the second driving device 31 by a channel wire to provide power. The energy storage device can be any device / module that can provide power, such as a rechargeable battery, an energy storage capacitor, etc.

[0079] In this embodiment, restoring the attitude of the connecting device 10 means restoring the attitude after the mounting plate 101 and the hanging seat 103 are twisted in the plane perpendicular to the first direction, or restoring the attitude after the mounting plate 101 and the hanging seat 103 are inclined in the transverse direction, or simultaneously restoring the attitude that has undergone torsion and inclination. Finally, in this embodiment, the first driving device 21 is vertically downward configured, and the first driving shaft 212, the cross point formed by the connecting rod 105, the driving plate 26, the two second folding rods 24, the cross point formed by the two third folding rods 28, and even the second driving device 31 disclosed in the second embodiment, the second driving shaft 311 and the center point of the cutting device 30 are all vertically coaxially arranged with the central axis 500 (or the central axis 100). Therefore, the telescopic link mechanism is more stable and synchronous during the actuation process of expanding or retracting, and significantly improves the overall structural strength and stability of the suspension device and the mobile cutting device in the third embodiment.

[0080] Example 2:

[0081] This embodiment shows another specific implementation of the aircraft suspension device.

[0082] Refer Figures 12 to 14 The main difference between the suspension device shown and the suspension device in the first embodiment is that, in this embodiment, the end of the mounting plate 101 forms two bent portions 111, 121 with through holes, and the reset assembly is composed of at least one torsion spring 107. The torsion spring 107 forms two free ends 1071 and 1072 extending through the bent portions 111, 121, and the torsion spring is vertically penetrated and fixed by the connecting rod 105.

[0083] Specifically, one end of the mounting plate 101 forms a bent portion 111, and a through hole 1111 for the free end 1071 to penetrate is opened in the bent portion 111; the other end of the mounting plate 101 forms a bent portion 121, and a through hole 1211 for the free end 1072 to penetrate is opened in the bent portion 121. Similar to the bent portion 111 or the bent portion 121, two groups arranged in a cross shape can also be provided, and two torsion springs 107 are respectively arranged in the first direction. The two torsion springs 107 are both sleeved outside the connecting rod 105 to provide a greater torsion recovery effect.

[0084] The connecting rod 105 is provided with a positioning hole 125. The torsion spring 107 is composed of a helical section 1070 and two free ends connected to the helical section 1070. The positioning member 1073 passes through the helical section 1070 and is placed into the positioning hole 125 to limit the rotation of the torsion spring 107 and at the same time limit the displacement of the torsion spring 107 in the first direction. The positioning hole 125 can be a blind hole with internal threads, and the positioning member 1073 is configured as a bolt with external threads. The positioning member 1073 is screwed and fixed with the positioning hole 125. The positioning hole 125 can also be a through hole that laterally penetrates the connecting rod 105. The positioning member 1073 is configured as a pin, or a bolt with external threads and is screwed with a nut at the end of the bolt, so as to laterally lock the helical section 1070.

[0085] To further improve the stability of the torsion spring 107 after being installed in the connecting rod 105a in the first direction, refer Figure 15 to Figure 16 As shown, the connecting rod 105a radially forms an inwardly contracting section 1050 that restricts the longitudinal movement of the helical section 1070, and the helical section 1070 is embedded in the contracting section 1050. The positioning member 1073 laterally passes through the helical section 1070 and is placed into the positioning hole 125. The connecting rod 105a is composed of an upper connecting rod section 1051 and a lower connecting rod section 1053 that are vertically screwed together. A blind hole 1054 with internal threads is recessed at the top of the lower connecting rod section 1053, and a screwed section 1052 with external threads is provided at the bottom of the upper connecting rod section 1051. The diameter of the screwed section 1052 is smaller than the diameter of the lower connecting rod section 1053. The upper connecting rod section 1051 is circumferentially provided with a protruding ring 1151, and the diameter of the protruding ring 1151 is larger than the diameter of the contracting section 1050, so as to clamp the helical section 1070 up and down with the lower connecting rod section 1053 through the protruding ring 1151. Thus, in the same way that the positioning member 1073 passes through the helical section 1070 and is placed into the positioning hole 125, the rotation of the torsion spring 107 is jointly restricted and at the same time the displacement of the torsion spring 107 in the vertical direction is restricted.

[0086] For the technical solutions of the same parts in the suspension device in this embodiment and those in Embodiment 1, refer to those shown in Embodiment 1 and will not be elaborated here.

[0087] Example 3:

[0088] Refer Figure 1 , Figure 6 and Figure 7 As shown, based on the technical solutions of the suspension device disclosed in Embodiment 1 and / or Embodiment 2, this embodiment also discloses a mobile cutting device, which performs mobile cutting operations on objects such as crops, trees, shrubs, and lawns by mobile operation devices such as aircraft. The mobile cutting device includes: an aircraft suspension device such as those in Embodiment 1 and / or Embodiment 2, and a cutting device 30 assembled below the guiding plate 27 in the first direction. The cutting device 30 can be integrally disc-shaped. The guiding plate 27 is used to hoist and connect the cutting device 30 in the first direction.

[0089] Specifically, in this embodiment, the cutting device 30 includes a second driving device 31 disposed at the bottoms of two guiding plates 27, a protective cover 32, a cutting tool holder 34, and a plurality of blades 35 that are horizontally assembled with the cutting tool holder 34 and rotate in the area enclosed by the protective cover 32. The cutting device 30 is controlled by the aircraft suspension device and performs a telescopic movement along the longitudinal extension direction of the guiding plate 27 (i.e., the direction parallel to the central axis 500) as the telescopic link mechanism expands or contracts. An area 270 for the movement of the telescopic link mechanism is formed between two guiding plates 27 arranged in parallel along the first direction. The protective cover 32 blocks the fragments formed by the cutting of the blades 35.

[0090] Preferably, the mobile cutting device further includes: a protective housing 33 that horizontally partially shields the cutting tool holder 34. By providing the protective housing 33, it can effectively prevent the debris (such as branches, etc.) generated by the high-speed rotating blades 35 when cutting trees or lawns from winding around the second driving shaft 311 of the second driving device 31 and the cutting tool holder rotating shaft 343 that houses the second driving shaft 311, preventing the second driving device 31 from jamming. At the same time, a gap is formed between the bottom of the protective housing 33 and the cutting tool holder 34.

[0091] Refer Figure 7 As shown, the bottoms of the guiding plates 27 are connected to form a base 276. The protective housing 33 is assembled to the bottom of the base 276. The protective cover 32 is formed by movably splicing two semi-circular covers 321 and 322. The base 276 is used to connect and assemble the second driving device 31. An annular limiting ring 275 for clamping the second driving device 31 is protruded upward inside the base 276. A circle of blind holes is provided on the end face of the second driving device 31 facing the base 276. Bolts 274 penetrate upward through the base 276 and extend into the blind holes to reliably lock the second driving device 31 in the limiting ring 275. The protective cover 32 blocks the flying debris or the fragments that may be generated by the breakage of the blades from flying out to avoid safety accidents.

[0092] Specifically, the second driving device 31 can be a DC brushless motor or any other form of driving device. The second driving device 31 forms a second driving shaft 311 along the first direction. The cutting tool holder 34 protrudes upward to form a cutting tool holder rotating shaft 343 for housing the second driving shaft 311. The cutting tool holder 34 laterally forms a plurality of clamping portions 341 for clamping the blades 35 relative to the central axis 500. The blades 35 are vertically penetrated through the clamping portions 341 and the blades 35 by bolts 342 to reliably assemble the blades 35 with the clamping portions 341.

[0093] The guiding plate 27 extends transversely to form two mounting pieces 292, and two mounting pieces 291 perpendicular to the mounting pieces 292 are provided at the bottom of the base 276. The mounting pieces 291 are used for vertically assembling the protective shell 33 located below the base 276. The top of the protective shell 33 extends transversely to form a mounting piece 325, so as to screw and install the mounting piece 325 and the mounting piece 291 through a bolt 326, thereby fixedly installing the protective shell 33 below the base 276. The mounting piece 292 straddles the joint of the two semi-circular covers 321 and 322, and the bolt 273 is used to penetrate downward through the mounting piece 292 and is screwed and fixed with the protective cover 32 to enhance the structural strength of the protective cover 32. Through the above structure, it is not only beneficial to the installation of each component, but also can significantly increase the overall structural strength after the two mounting plates 27 and the cutting device 30 are assembled.

[0094] Meanwhile, in this embodiment, movable buckles 323 are correspondingly arranged at the edges of the semi-circular cover 321 and the semi-circular cover 322, and the bolt 324 is continuously used to penetrate through the buckles 323 to lock the edges of the semi-circular cover 321 and the semi-circular cover 322, so as to facilitate the assembly of the protective cover 32. The blade 35 in this embodiment can be strip-shaped or curved, and can be adjusted according to the actual needs of the object to be cut. At this time, the protective cover 32 only needs to fit the three-dimensional shape formed when the blade 35 rotates. Multiple blades 35 can rotate in the area enclosed by the protective cover 32, and the bottom of the protective cover 32 is of an open structure.

[0095] The specific technical solutions of the aircraft suspension device included in the mobile cutting device disclosed in this embodiment are as shown in Embodiment 1 and / or Embodiment 2, and will not be elaborated here.

[0096] Example 4:

[0097] Combined with Figure 18 As shown, based on the technical solutions disclosed in the mobile cutting device disclosed in Embodiment 3, this embodiment discloses a mobile working device 400.

[0098] The mobile working device 400 includes: a fuselage 41, and the fuselage 41 is assembled with the mobile cutting device disclosed in Embodiment 3. The mobile working device includes an aircraft or a ground working device or a water surface working device. The aircraft is selected from a rotary-wing aircraft, a non-powered aircraft or a fixed-wing aircraft. The aforementioned aircraft can be a manned aircraft or an unmanned aircraft. The aforementioned ground working device can be a vehicle traveling on land. The mobile cutting device is assembled on the side, front or rear of the vehicle, and the mobile cutting device is used to cut and trim roadside trees, lawns or even crops during the vehicle's travel.

[0099] Refer to Figure 18As shown, the aircraft further selects a quadrotor UAV (a subordinate concept of a rotary-wing aircraft). The quadrotor UAV includes a fuselage 41, and the fuselage 41 is connected to four power devices 43 (such as brushless DC motors) through four crossbars 42. The power devices 43 are configured with blades 431. Two landing gears 44 are provided below the fuselage 41. The mobile cutting device disclosed in the third embodiment can be installed below (or in front of or behind) the fuselage 41 through a mounting plate 101 or below other conventional auxiliary mounting devices horizontally placed between the two landing gears 44. This quadrotor UAV can lift one or more mobile cutting devices.

[0100] For the technical solutions of the mobile cutting device included in the mobile operation device in this embodiment that have the same parts as those in the third embodiment, please refer to the third embodiment shown, and details will not be repeated here.

[0101] The series of detailed descriptions listed above are only specific descriptions of the feasible implementation manners of the present invention, and they are not intended to limit the protection scope of the present invention. Any equivalent implementation manners or changes made without departing from the technical spirit of the present invention should be included in the protection scope of the present invention.

[0102] For those skilled in the art, it is obvious that the present invention is not limited to the details of the above-described exemplary embodiments, and the present invention can be implemented in other specific forms without departing from the spirit or basic characteristics of the present invention. Therefore, from any point of view, the embodiments should be regarded as exemplary and non-limiting. The scope of the present invention is defined by the appended claims rather than the above description. Therefore, all changes falling within the meaning and scope of the equivalent elements of the claims are intended to be included in the present invention. Any reference signs in the claims should not be regarded as limiting the claimed invention.

[0103] In addition, it should be understood that although this specification is described according to embodiments, not every embodiment only includes an independent technical solution. This narrative manner of the specification is only for clarity. Those skilled in the art should regard the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. Aircraft suspension device, characterized in that, comprising: a telescopic device assembled to the aircraft through a connecting device; the telescopic device includes a first mounting seat for receiving a first driving device, a driving plate driven by the first driving device and moving up and down in a first direction, two guiding plates provided with guiding grooves and arranged parallel to the first direction, a telescopic link mechanism clamped by the two guiding plates, and a driving rod; the telescopic link mechanism includes two groups of symmetrically arranged and mutually articulated first folding rods, second folding rods and third folding rods, the first folding rods are articulated to the first mounting seat, the second folding rods are symmetrically arranged and articulated to a moving articulation point, and the third folding rods are symmetrically arranged and articulated to a fixed articulation point; the driving rod is articulated to the driving plate and the telescopic link mechanism, and drives the telescopic link mechanism to expand or contract under the drive of the first driving device, so as to integrally drive the guiding plates to move up and down in the first direction. The telescopic link mechanism and the guiding plates form a fixed articulation point and a moving articulation point. During the process of the telescopic link mechanism expanding or contracting, the connection line between the fixed articulation point and the moving articulation point always remains in the same direction as the extension direction of the guiding groove.

2. The aircraft suspension device according to claim 1, characterized in that, the distance between the articulation point formed by the driving rod and the first folding rod and the articulation point formed by the first folding rod and the first mounting seat is less than the distance between the articulation point formed by the driving rod and the first folding rod and the articulation point formed by the first folding rod and the second folding rod, and the length of the first folding rod is greater than the length of the third folding rod.

3. The aircraft suspension device according to claim 1, characterized in that, the first driving device forms a first driving shaft that partially extends in the first direction past the driving plate and is provided with an external thread, and the driving plate is provided with an internal thread that meshes with the external thread of the first driving shaft.

4. The aircraft suspension device according to any one of claims 1 to 3, characterized in that, one sides of the two guiding plates close to the connecting device are separated from each other and one sides far from the connecting device are connected to each other. The two guiding plates are respectively provided with corresponding guiding grooves. The guiding grooves extend in the first direction and penetrate through the guiding plates or are arranged oppositely on the opposite inner sides of the two guiding plates.

5. The aircraft suspension device according to claim 4, characterized in that, the connecting device includes: a mounting plate, a receiving seat formed at the center of the mounting plate, a connecting rod extending into the receiving seat and connected to the receiving seat in a universal joint manner, a hanging seat rigidly connected to the connecting rod, and a reset assembly for restoring the initial state formed by the hanging seat and the mounting plate. A connecting arm for movably hoisting the first mounting seat is provided at the bottom of the hanging seat; a reamed hole for the connecting rod to penetrate is opened at the bottom of the receiving seat, and the diameter of the reamed hole is greater than the diameter of the connecting rod.

6. The aircraft suspension device according to claim 5, characterized in that, a limiting block with a cavity is provided in the receiving seat, and a rotating body received by the limiting block and rotating in a universal joint manner within the cavity formed by the limiting block. The connecting rod vertically extends into the rotating body and is fixedly connected to the rotating body.

7. The aircraft suspension device according to claim 5, It is characterized in that the reset assembly is composed of at least two torsion elastic elements arranged axially symmetrically with respect to the connecting rod, and both ends of the torsion elastic element are connected to the end extending along the length direction of the mounting plate and the end of the hanging seat; the torsion elastic element is selected from a spring or an elastic rubber strip.

8. The aircraft suspension device according to claim 5, It is characterized in that both ends of the mounting plate form two bent parts with through holes, and the reset assembly is composed of at least one torsion spring; the torsion spring forms two free ends extending through the bent parts, and the torsion spring is vertically penetrated and fixed by the connecting rod.

9. The aircraft suspension device according to claim 8, It is characterized in that the connecting rod is provided with positioning holes, the torsion spring is composed of a spiral section and two free ends connected to the spiral section, and a positioning member penetrates through the spiral section and is placed in the positioning holes to limit the rotation of the torsion spring.

10. The aircraft suspension device according to claim 9, It is characterized in that the connecting rod radially forms an inwardly contracting section that restricts the longitudinal movement of the spiral section, and the spiral section is embedded in the contracting section.

11. A mobile cutting device, It is characterized in that comprising: the aircraft suspension device according to any one of claims 1 to 10, and a cutting device assembled below the guide plate along the first direction; the cutting device includes a second driving device arranged at the bottom of two guide plates, a protective cover, a cutting tool holder, and a plurality of blades that are horizontally assembled with the cutting tool holder and rotate in the area enclosed by the protective cover; the cutting device is controlled by the aircraft suspension device and makes a telescopic movement along the longitudinal extension direction of the guide plate as the telescopic link mechanism expands or contracts.

12. The mobile cutting device according to claim 11, It is characterized in that the mobile cutting device further includes: a protective shell that horizontally partially shields the cutting tool holder; the bottoms of the guide plates are connected to form a base, the protective shell is assembled at the bottom of the base, and the protective cover is formed by movably splicing two semi-circular covers.

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