Foldable undercarriage, unmanned aerial vehicle and unmanned aerial vehicle launching system

Abstract

The invention provides a foldable undercarriage, an unmanned aerial vehicle and an unmanned aerial vehicle launching system.The undercarriage comprises a fixing base and a supporting leg assembly, the supporting leg assembly comprises a main leg and two auxiliary legs, the first end of the main leg is connected with the fixing base, and the main leg can turn over around the first end of the main leg relative to the fixing base; the second end of the main leg is connected with the respective connecting ends of the two auxiliary legs, and the auxiliary legs can rotate around the connecting ends of the auxiliary legs relative to the main leg; the unmanned aerial vehicle comprises a fuselage and the two foldable undercarriages, and the two foldable undercarriages are rotationally connected to the two sides of the fuselage correspondingly; the unmanned aerial vehicle launching system comprises a launcher and the unmanned aerial vehicle, the launcher is provided with a launching cavity and a base sliding block, the unmanned aerial vehicle is arranged in the launching cavity and arranged on the base sliding block, a foldable undercarriage and foldable paddles of the unmanned aerial vehicle can be contained in the launching cavity, and the base sliding block can push the unmanned aerial vehicle to be launched outwards; the folding table is good in supporting stability and small in occupied space after being folded.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of unmanned aerial vehicles, in particular to a foldable landing gear, an unmanned aerial vehicle and an unmanned aerial vehicle launching system. BACKGROUND

[0002] The landing gear of the coaxial dual-rotor unmanned aerial vehicle mainly plays a role in supporting the body stability of the unmanned aerial vehicle during take-off and landing, and can also protect the gimbal device located at the lower part of the fuselage. In some specific application scenarios, the landing gear needs to have a folding function because the unmanned aerial vehicle needs to be stored or deployed in a limited space, and it must be quickly unfolded to a preset angle to meet the demand of immediate take-off when preparing for flight.

[0003] The common landing gears at present mainly have two types of "I" shape and "T" shape. The "I" shape landing gear is relatively simple in folding storage and unfolding operation, but its supporting stability is relatively weak; while the "T" shape landing gear has better supporting stability, but it is not easy to fold and store, and even after folding, it still occupies a large space.

[0004] In addition, the existing foldable landing gear usually remains in an unfolded state during flight, but due to the lack of reliable limiting structure, it is easy to shake or vibrate during flight, thereby affecting the flight stability of the whole machine. SUMMARY

[0005] The first object of the present application is to provide a foldable landing gear with good supporting stability and small space occupation after folding.

[0006] The second object of the present application is to provide an unmanned aerial vehicle comprising the above foldable landing gear.

[0007] The third object of the present application is to provide an unmanned aerial vehicle launching system comprising the above unmanned aerial vehicle.

[0008] In order to achieve the above-mentioned first object, the present application provides a foldable landing gear, which comprises a fixed seat and a support leg assembly, the support leg assembly comprising a main leg and two auxiliary legs, the first end of the main leg being connected with the fixed seat, the main leg being able to rotate relative to the fixed seat at the first end thereof, the second end of the main leg being connected with the respective connecting end of each of the two auxiliary legs, and the auxiliary leg being able to rotate relative to the main leg at the connecting end thereof.

[0009] As can be seen from the above scheme, by arranging that the main leg is able to rotate relative to the fixed seat at the first end thereof, the landing gear is conveniently flipped up and down to realize its folding and unfolding functions; by arranging that the two auxiliary legs are both able to rotate relative to the main leg at the respective connecting end thereof, the whole landing gear can play a role in stable support when the auxiliary legs are unfolded, and can also minimize the occupied space when the auxiliary legs are folded. The present application also has the advantages of simple structure, convenient operation, reliable connection and relatively low cost. Further, the auxiliary leg can be switched between the first state and the second state; in the first state, the auxiliary leg is perpendicular to the main leg; in the second state, the auxiliary leg is parallel to the main leg.

[0010] Further, the second end of the main leg is connected with a tee joint, the tee joint is provided with two auxiliary insertion holes; the connecting end of the auxiliary leg is rotatably connected to one side of the tee joint, the connecting end of the auxiliary leg is provided with a locking tongue, the locking tongue can protrude from the end of the auxiliary leg and be inserted into the auxiliary insertion hole.

[0011] From the above scheme, by setting the locking tongue to protrude from the end of the auxiliary leg and be inserted into the auxiliary insertion hole, the auxiliary leg and the main leg can be kept in a vertical locking state for a long time, preventing accidental failure caused by external force.

[0012] Further, the connecting end of the auxiliary leg is further provided with a flat push piece and a first elastic piece, the first elastic piece elastically abuts between the auxiliary leg and the locking tongue, the flat push piece is arranged on the outer side of the auxiliary leg and connected with the locking tongue, and the flat push piece can drive the locking tongue to retract into the auxiliary leg.

[0013] From the above scheme, by setting the first elastic piece, the locking tongue always maintains a protruding state in normal state; by setting the flat push piece, when folding is needed, the locking tongue is retracted into the auxiliary leg and withdrawn from the auxiliary insertion hole by controlling the flat push piece, so that the auxiliary leg can be switched to the second state, having the advantages of simple structure and convenient operation.

[0014] Further, the connecting end of the auxiliary leg is provided with a sleeve part, the sleeve part is rotatably connected to the tee joint through a first rotating shaft, and a second elastic piece is further connected between the main leg and the auxiliary leg, the second elastic piece applies an elastic force to the auxiliary leg to force the auxiliary leg to rotate around the first rotating shaft to the side where the auxiliary insertion hole is located.

[0015] From the above scheme, by setting the second elastic piece, the auxiliary leg can be automatically switched from the second state to the first state without external force, which is beneficial to the automatic unfolding of the landing gear when the unmanned aerial vehicle takes off.

[0016] Further, a limiting structure is arranged between the fixed seat and the first end of the main leg; after the main leg is turned down in place, the limiting structure can inhibit the shaking of the main leg.

[0017] From the above scheme, by the above arrangement, it is ensured that the landing gear is in an unfolded state and is always fixed at a certain preset angle during the flight of the unmanned aerial vehicle, avoiding shaking of the landing gear.

[0018] Further, a first limiting protrusion is arranged on the fixed seat; a protruding part is arranged on the first end of the main leg; a plate buckle is connected between the fixed seat and the first end of the main leg, the plate buckle is rotatably connected to the fixed seat, one end of the plate buckle is provided with a limiting part, and the protruding part can be embedded between the first limiting protrusion and the limiting part.

[0019] From the above scheme, it can be seen that the first limiting protrusion and the clamping fixed protrusion of the limiting portion are used to prevent the landing gear from shaking.

[0020] Further, the fixing base comprises a mounting plate and two ear plates, the two ear plates are oppositely connected to the mounting plate, the plate buckle is connected between the two ear plates through the second rotating shaft, and the third elastic member is connected between the mounting plate and the plate buckle, and the third elastic member can force the limiting portion to rotate away from the mounting plate.

[0021] Further, the second limiting protrusion is arranged on the ear plate and is arranged on the side of the limiting portion away from the mounting plate, and the second limiting protrusion can abut against the limiting portion.

[0022] Further, the fourth elastic member is connected between the fixing base and the main leg, and the fourth elastic member can force the main leg to rotate downward.

[0023] Further, the locking member is arranged on the auxiliary leg and is provided with a locking portion protruding from the surface of the auxiliary leg.

[0024] In order to achieve the second purpose, the unmanned aerial vehicle provided by the present application comprises a fuselage and two foldable landing gears, the two foldable landing gears are rotatably connected to the two sides of the fuselage respectively, the fuselage is provided with a locking device for locking connection with the locking member of the foldable landing gear, and the locking device can be unlocked and separated from the locking member.

[0025] From the above scheme, it can be seen that during the flight of the unmanned aerial vehicle, the supporting foot assembly can be automatically turned downward and automatically unfolded; when it is necessary to be stored, the supporting foot assembly can be manually turned upward to be close to the fuselage, and the auxiliary leg is manually switched to the second state, so as to reduce the occupied space.

[0026] In order to achieve the third purpose, the unmanned aerial vehicle launching system provided by the present application comprises a launcher and the unmanned aerial vehicle, the launcher is provided with a launching cavity and a base sliding block, the base sliding block is slidingly arranged in the launching cavity; the unmanned aerial vehicle is arranged in the launching cavity and on the base sliding block, and the foldable landing gear and the foldable paddle of the unmanned aerial vehicle can be stored in the launching cavity, and the base sliding block can push the unmanned aerial vehicle to be launched outward. BRIEF DESCRIPTION OF DRAWINGS

[0027] Figure 1 is a structure diagram of the first perspective view of the folded state of the foldable landing gear of the present application.

[0028] Figure 2 is a structure diagram of the second perspective view of the folded state of the foldable landing gear of the present application.

[0029] Figure 3 is a structure diagram of the unfolded state of the foldable landing gear of the present application, and two locking members are omitted.

[0030] Figure 4 is an exploded view of the main leg and the auxiliary leg in an embodiment of the foldable landing gear of the present application.

[0031] Figure 5 is a sectional view of the main leg and the auxiliary leg in an embodiment of the foldable landing gear of the present application.

[0032] Figure 6 is an exploded view of the fixed seat, the plate buckle, the sleeve and the main leg in an embodiment of the foldable landing gear of the present application.

[0033] Figure 7 is a sectional view of the main leg when folded in an embodiment of the foldable landing gear of the present application.

[0034] Figure 8 is a sectional view of the main leg when unfolded in an embodiment of the foldable landing gear of the present application.

[0035] Figure 9 is a structural view of the sleeve in an embodiment of the foldable landing gear of the present application.

[0036] Figure 10 is a structural view of the unmanned aerial vehicle in an embodiment of the present application in an unfolded state.

[0037] Figure 11 is a structural view of the unmanned aerial vehicle in an embodiment of the present application in a folded state.

[0038] Figure 12 is an exploded view of the unmanned aerial vehicle, the base slider and the launcher in an embodiment of the unmanned aerial vehicle launching system of the present application.

[0039] Explanation of reference numerals: 1 - fixed seat, 11 - mounting plate, 111 - first perforation, 112 - second perforation, 12 - ear plate, 121 - first limiting protrusion, 122 - second limiting protrusion; 2 - main leg, 21 - sleeve, 211 - protruding part, 2111 - abutting surface, 2112 - avoiding position, 212 - recess, 22 - locking member; 3 - auxiliary leg, 31 - sleeve part, 311 - second protruding plate, 312 - step part, 313 - flat surface, 314 - sliding hole; 4 - three-way piece, 41 - main insertion hole, 42 - auxiliary insertion hole, 43 - first protruding plate; 5 - locking tongue, 51 - guiding surface; 6 - first rotating shaft; 7 - second elastic member; 8 - flat pushing piece; 9 - connecting piece; 10 - first elastic member; 20 - plate buckle, 201 - limiting part, 202 - pushing part; 30 - second rotating shaft; 40 - third elastic member; 50 - third rotating shaft; 60 - fourth elastic member; 70 - locking member; 100 - body, 1001 - support seat; 200 - launcher; 300 - base slider, 3001 - mounting groove; 400 - launching frame.

[0040] The application will be further described below in conjunction with the accompanying drawings and embodiments. DETAILED DESCRIPTION

[0041] Foldable landing gear embodiment: Referring to Figures 1 to 3 , and in conjunction with Figure 12 , the foldable landing gear provided by the embodiment comprises a fixed seat 1 and a support leg assembly.

[0042] The support leg assembly comprises a main leg 2 and two auxiliary legs 3. The first end of the main leg 2 is rotatably connected to the fixed seat 1, and the main leg 2 can be flipped up and down relative to the fixed seat 1 about the first end thereof. The second end of the main leg 2 is rotatably connected to the respective connecting end of each of the two auxiliary legs 3, and the auxiliary leg 3 can rotate relative to the main leg 2 about the connecting end thereof, and the rotation direction of the main leg 2 is different from that of the auxiliary leg 3. The main leg 2 rotates up and down, and the auxiliary leg 3 rotates along an axis perpendicular to the main leg 2.

[0043] The auxiliary leg 3 can be switched back and forth between a first state and a second state. The first state is the unfolded state of the auxiliary leg 3, at which time the auxiliary leg 3 is perpendicular to the main leg 2 to provide stable support; the second state is the folded state of the auxiliary leg 3, at which time the auxiliary leg 3 is parallel to the main leg 2 to reduce the occupied space and facilitate the overall landing gear to be accommodated in the launching cavity of the launcher 200.

[0044] Referring to Figure 4 and Figure 5 , the second end of the main leg 2 is connected to a three-way piece 4, and the three ends of the three-way piece 4 are respectively provided with a main insertion hole 41 and two auxiliary insertion holes 42. The two auxiliary insertion holes 42 are coaxially arranged, and the main insertion hole 41 is perpendicular to the auxiliary insertion holes 42. The second end of the main leg 2 is fixedly connected in the main insertion hole 41.

[0045] The connecting end of the auxiliary leg 3 is rotatably connected to one side of the tee piece 4, and preferably, the rotation angle of the auxiliary leg 3 is about 90°. A retractable locking tongue 5 is arranged in the connecting end of the auxiliary leg 3. In the normal state, the locking tongue 5 protrudes from the end of the connecting end of the auxiliary leg 3 and is inserted into the auxiliary insertion hole 42. The outer diameter of the locking tongue 5 is equal to or slightly smaller than the inner diameter of the auxiliary insertion hole 42, so that the outer peripheral wall of the locking tongue 5 can be adjacent to or abut against the inner wall of the auxiliary insertion hole 42, which can limit the rotation of the auxiliary leg 3 relative to the tee piece 4, avoid support failure, and avoid the locking tongue 5 from shaking in the auxiliary insertion hole 42, thereby reducing noise.

[0046] The connecting end of the auxiliary leg 3 is provided with a sleeve part 31, which is rotatably connected to one side of the tee piece 4 through a first rotation shaft 6, and the axial direction of the first rotation shaft 6 is perpendicular to the axial direction of the auxiliary insertion hole 42. When the sleeve part 31 is rotated to the state that the axial line thereof is parallel to the axial line of the auxiliary insertion hole 42, the end face of the sleeve part 31 abuts or abuts against the corresponding end face of the tee piece 4. Specifically: The tee piece 4 is provided with two first protruding plates 43 on the left and right outer sides of the main insertion hole 41, and the two first protruding plates 43 are oppositely arranged and spaced by a first preset distance.

[0047] One side of the sleeve part 31 is provided with two second protruding plates 311, which are oppositely arranged and spaced by a second preset distance, and the second preset distance is smaller than the first preset distance, so that the two second protruding plates 311 can be embedded between the two first protruding plates 43. The first rotation shaft 6 is connected with the two first protruding plates 43 and the two second protruding plates 311 respectively, and the sleeve part 31 can rotate around the first rotation shaft 6. The sleeve part 31 is integrally formed with the auxiliary leg 3, or the sleeve part 31 is fixedly connected with the auxiliary leg 3 through glue or screws, which is not limited herein.

[0048] The second elastic member 7, which is preferably a torsion spring, is further connected between the main leg 2 and each auxiliary leg 3, the middle part of the second elastic member 7 is sleeved on the middle part of the first rotation shaft 6, one end of the second elastic member 7 abuts against the sleeve part 31, and the other end of the second elastic member 7 abuts against the outer side wall of the main leg 2 or the main insertion hole 41. The second elastic member 7 can exert a elastic force on the auxiliary leg 3 to force the auxiliary leg 3 to rotate around the first rotation shaft 6 to the side where the auxiliary insertion hole 42 is located, so that the auxiliary leg 3 can automatically expand without external force control, and ensure that the auxiliary leg 3 can automatically expand when the unmanned aerial vehicle takes off.

[0049] In order to facilitate the locking tongue 5 to smoothly insert into the auxiliary insertion hole 42 when it automatically expands, the locking tongue 5 of the present embodiment is provided with a guide surface 51 on the end thereof protruding from the sleeve part 31, the guide surface 51 is arranged on the side of the locking tongue 5 close to the rotation axis of the auxiliary leg 3, and the guide surface 51 can be in guiding contact with the edge of the auxiliary insertion hole 42. The guide surface 51 can be an arc surface or an inclined surface, which is not limited herein.

[0050] The connecting end of the auxiliary leg 3 is further provided with a flat pushing piece 8, a connecting piece 9 and a first elastic piece 10. The inner side of the connecting end of the auxiliary leg 3 is provided with a stepped portion 312, and the first elastic piece 10 elastically abuts between the stepped portion 312 and the lock tongue 5. The first elastic piece 10 is preferably a compression spring, so that the lock tongue 5 can protrude out of the end of the sleeve portion 31 in a normal state. One side of the sleeve portion 31 is provided with a flat surface 313, and a sliding hole 314 is formed in the flat surface 313 and communicates with the inside of the sleeve portion 31. The length direction of the sliding hole 314 is parallel to the axial direction of the sleeve portion 31. The flat pushing piece 8 is arranged on the outside of the sleeve portion 31 and is slidingly arranged on the flat surface 313. The flat pushing piece 8 is connected with the lock tongue 5 through the connecting piece 9, and the middle part of the connecting piece 9 is inserted into the sliding hole 314 and can move back and forth in the length direction of the sliding hole 314. The flat pushing piece 8 can drive the lock tongue 5 to retract into the auxiliary leg 3, so that the lock tongue 5 exits the auxiliary insertion hole 42, thereby realizing the folding function of the auxiliary leg 3. The surface of the flat pushing piece 8 is provided with anti-skid lines, which facilitates the operation of the user.

[0051] Referring to Figure 1 and Figure 2 , the end of the auxiliary leg 3 away from the three-way piece 4 is provided with a foot cover made of nylon or rubber material, which can not only protect the auxiliary leg 3, but also enhance the ground friction and provide a cushioning effect, thereby further improving the operation safety and overall stability of the unmanned aerial vehicle.

[0052] The auxiliary leg 3 is further provided with a lock catch 70, which can be arranged between the two ends of the auxiliary leg 3, and is preferably arranged on the end away from the three-way piece 4. The lock catch 70 includes a connecting ring portion and a locking portion, the connecting ring portion is sleeved on the outside of the auxiliary leg 3, and the locking portion protrudes outward along the radial direction of the connecting ring portion, and is used to extend into the unmanned aerial vehicle body 100 and be locked and connected with the locking device inside the unmanned aerial vehicle body 100, as shown in Figure 11 When it is needed to be unfolded, the locking device can also be unlocked and separated from the locking portion.

[0053] Referring to Figures 6 to 9 , the fixed seat 1 and the first end of the main leg 2 are provided with a limiting structure.

[0054] When the main leg 2 is turned down to the position, the limiting structure can inhibit the main leg 2 from shaking up and down, and the limiting structure includes a buckle 20, a first limiting protrusion 121 and a second limiting protrusion 122. Specifically: The fixed seat 1 includes a mounting plate 11 and two ear plates 12, the mounting plate 11 is provided with a plurality of mounting holes for being fixedly connected with the unmanned aerial vehicle body 100, the two ear plates 12 are oppositely connected on the same side of the mounting plate 11, and the middle part of the mounting plate 11 is provided with a first through hole 111, and the first through hole 111 is located at the position between the two ear plates 12. The mounting plate 11 and the ear plates 12 are both provided with a plurality of weight reduction holes to reduce the weight of the fixed seat 1 and realize light weight.

[0055] The fixed seat 1 is connected with the first end of the main leg 2, and a plate buckle 20 is connected between the lower parts of the two ear plates 12 through a second rotating shaft 30. The plate buckle 20 can rotate forward and backward around the second rotating shaft 30. The second rotating shaft 30 is arranged on the middle part of the plate buckle 20, the upper part of the plate buckle 20 is provided with a limiting part 201 for limiting the main leg 2 from continuing to rotate downward, and the lower part of the plate buckle 20 is provided with a pushing part 202. The included angle between the limiting part 201 and the pushing part 202 is less than 180° and greater than 90°. When the limiting part 201 abuts against the second limiting protrusion 122, the pushing part 202 is inclined to protrude outward downward, at this time, only a vertical upward pushing force is needed to force the plate buckle 20 to rotate counterclockwise, so that the limiting part 201 is separated from the main leg 2.

[0056] A third elastic member 40 is connected between the mounting plate 11 and the plate buckle 20, and the third elastic member 40 can force the plate buckle 20 to have an elastic potential energy of clockwise rotation, that is, force the limiting part 201 to rotate away from the mounting plate 11, so that the limiting part 201 is close to the main leg 2. The third elastic member 40 is preferably a torsional spring, the middle part of the third elastic member 40 is connected to the second rotating shaft 30, one end of the third elastic member 40 abuts against the plate buckle 20, and the other end of the third elastic member 40 is inserted into the first perforation 111 and abuts against the lower hole wall of the first perforation 111.

[0057] The inner side wall of one of the ear plates 12 is provided with a first limiting protrusion 121 and a second limiting protrusion 122. The second limiting protrusion 122 is arranged below the first limiting protrusion 121, and the first limiting protrusion 121 and the second limiting protrusion 122 are spaced apart in the vertical direction and the horizontal direction. The first limiting protrusion 121 is used to limit the maximum rotation angle of the main leg 2 when it is flipped downward. The second limiting protrusion 122 is arranged on the side of the limiting part 201 away from the mounting plate 11, and the second limiting protrusion 122 can abut against the limiting part 201 to limit the maximum rotation angle of the plate buckle 20 when it rotates clockwise.

[0058] The first end of the main leg 2 is provided with a pipe sleeve 21, and the pipe sleeve 21 is fixedly connected with the main leg 2 through a locking member 22. The pipe sleeve 21 is rotatably connected between the upper parts of the two ear plates 12 through a third rotating shaft 50, and the third rotating shaft 50 is arranged on the end of the pipe sleeve 21 away from the main leg 2 and above the second rotating shaft 30. The pipe sleeve 21 is provided with a protruding part 211 extending in the radial direction of the third rotating shaft 50. One side of the protruding part 211 is provided with an abutting surface 2111 which is a curved surface or an inclined surface recessed from the lower side wall of the protruding part 211 to the inner side of the protruding part 211. The abutting surface 2111 can abut against the top wall of the limiting part 201.

[0059] When the main leg 2 is flipped upward to the vertical direction, the protruding part 211 protrudes outward away from the mounting plate 11, as shown in Figure 7 ​

[0060] When the main leg 2 is being flipped down, the protrusion 211 first abuts against the upper part of the plate buckle 20 and pushes the plate buckle 20 to rotate counterclockwise, so that the protrusion 211 can rotate above the plate buckle 20; and at the moment when the protrusion 211 rotates past the plate buckle 20 and separates from the plate buckle 20, the plate buckle 20 immediately rotates clockwise under the elastic force of the third elastic member 40, so that the limiting part 201 rotates below the protrusion 211; at this time, the protrusion 211 is embedded between the first limiting protrusion 121 and the limiting part 201, so as to limit the rotation of the protrusion 211 and reduce the amplitude of the up-and-down swinging of the main leg 2.

[0061] Preferably, the first limiting protrusion 121 and the limiting part 201 abut against both sides of the protrusion 211, respectively, so as to clamp and fix the protrusion 211 by the first limiting protrusion 121 and the limiting part 201, thereby fixing the sleeve 21 and the main leg 2 and avoiding the up-and-down swinging of the main leg 2.

[0062] In combination with Figure 6 and Figure 9 , in order to facilitate the smooth passing of the protrusion 211 through the second limiting protrusion 122 when the main leg 2 is being rotated downward, the side of the protrusion 211 close to the second limiting protrusion 122 is provided with an avoiding position 2112, which is preferably a bevel recessed from the corner of the protrusion 211 to the inner side thereof, so that the protrusion 211 does not collide with the second limiting protrusion 122 during the flipping-down process of the sleeve 21, thereby avoiding the collision and avoiding the structural interference.

[0063] The fourth elastic member 60 is connected between the fixed seat 1 and the main leg 3, and can force the main leg 3 to rotate downward, so that the main leg 3 automatically expands downward under the combined action of the gravity and the elastic force of the fourth elastic member 60. Specifically: The sleeve 21 is provided with a groove 212 at the end close to the third rotating shaft 50, and the middle part of the third rotating shaft 50 is arranged in the groove 212. The fourth elastic member 60 is arranged in the groove 212. The fourth elastic member 60 is preferably a torsion spring, the middle part of the fourth elastic member 60 is sleeved on the third rotating shaft 50, the first end of the fourth elastic member 60 elastically abuts against the bottom of the groove 212, and the second end of the fourth elastic member 60 elastically abuts against the mounting plate 11 of the fixed seat 1. The mounting plate 11 is provided with a second through hole 112 above the first through hole 111; the second end of the fourth elastic member 60 is provided with a hook part, the hook part passes through the second through hole 112 and is hooked on the hole wall of the second through hole 112, as shown in Figure 2 The fourth elastic member 60 can exert a downward rotating elastic force on the sleeve 21.

[0064] The working principle of the embodiment is as follows: When the landing gear is expanded, the main leg 2 is inclined to extend downward, and the auxiliary leg 3 is in the first state, i.e., both of the auxiliary legs 3 are perpendicular to the main leg 2, as shown in Figure 3 .

[0065] When folding is needed, first, the auxiliary leg 3 is forced to switch from the first state to the second state by a first external force, that is, the auxiliary leg 3 rotates about 90° around the first rotating shaft 6, so that the auxiliary leg 3 is parallel to the main leg 2; then the main leg 2 is forced to turn upward by a second external force until the main leg 2 is tightly attached to the unmanned aerial vehicle body 100, and the angle of upward turning of the main leg 2 is about 135°. The first external force and the second external force are both manually applied forces.

[0066] In other embodiments, the main leg 2 can first turn upward, and then the auxiliary leg 3 rotates around the first rotating shaft 6, which is not limited here.

[0067] When unfolding the landing gear, the landing gear automatically turns downward under the combined action of its gravity and the elastic force of the fourth elastic member 60, the protruding part 211 pushes the plate buckle 20 to rotate counterclockwise, the third elastic member 40 is compressed, and the main leg 2 rotates to collide with the first limiting protrusion 121 and then returns. At this time, due to the arrangement of the abutting surface 2111, the protruding part 211 is separated from the plate buckle 20, the force acting on the plate buckle 20 disappears, and under the elastic action of the third elastic member 40, the plate buckle 20 rotates clockwise until it abuts against the second limiting protrusion 122. At this time, the limiting part 201 abuts against the abutting surface 2111, so that the main leg 2 can maintain the unfolded state for a long time.

[0068] In the process of downward rotation of the main leg 2, the auxiliary leg 3 rotates relative to the main leg 2 under the elastic action of the second elastic member 7, the locking tongue 5 is first compressed and retracted into the auxiliary leg 3, and the first elastic member 10 is compressed. When the auxiliary leg 3 rotates about 90° and stops, the locking tongue 5 extends into the corresponding auxiliary insertion hole 42 under the elastic action of the first elastic member 10, so that the auxiliary leg 3 can maintain the unfolded state for a long time.

[0069] Unmanned aerial vehicle embodiment: Referring to Figure 10 and Figure 11 , and in combination with Figure 12 , the unmanned aerial vehicle provided in the embodiment can be a coaxial dual-rotor unmanned aerial vehicle, or can be other unmanned aerial vehicles, which is not limited here.

[0070] The unmanned aerial vehicle of the embodiment includes a body 100 and two foldable landing gears of the above-mentioned embodiments, and the two foldable landing gears are respectively and rotatably connected to opposite sides of the body 100. The fixing seat 1 of the foldable landing gear is fixedly connected to the body 100, and the main leg 2 and the auxiliary leg 3 of the foldable landing gear are both arranged on the outside of the body 100.

[0071] Four locking devices are arranged in the body 100, and the four locking devices are respectively and correspondingly arranged with the locking catch members 70 on the four auxiliary legs 3. The locking devices are in locking connection with the locking catch members 70 and can be unlocked and separated, so as to realize the fixing and releasing of the foldable landing gear.

[0072] The landing gear of the unmanned aerial vehicle of the embodiment does not need to be disassembled, the folding method is simple and efficient, and the space occupied after folding is very small.

[0073] The upper portion of the unmanned aerial vehicle is further provided with a plurality of foldable blades, the plurality of foldable blades are in pairs and can be folded downward, the foldable blades can be turned downward by about 90°, so that the foldable blades can be close to the unmanned aerial vehicle body 100, and the foldable blades can be conveniently stored in the launcher 200 of the unmanned aerial vehicle launching system.

[0074] When the foldable blades are stored, the foldable blades are turned downward by about 90°, the auxiliary legs 3 are switched from the first state to the second state, the main legs 2 are turned upward by about 135°, the auxiliary legs 3 are locked by the locking device, so that the foldable blades and the foldable landing gear are close to the unmanned aerial vehicle body 100, as shown in Figure 11 Then, the unmanned aerial vehicle is placed in the launching cavity of the launcher 200, and the next launching is waited.

[0075] When taking off, after the unmanned aerial vehicle gradually rises and leaves the launching cavity, the foldable blades are automatically turned upward and unfolded, and the foldable landing gear is automatically turned downward to the position under the cooperation of the gravity and the elastic force of the fourth elastic member 60; in this process, under the action of the second elastic member 7, the auxiliary legs 3 are automatically switched from the second state to the first state, so that the auxiliary legs 3 are perpendicular to the main legs 2, and the automatic unfolding of the auxiliary legs 3 is realized, without manual operation.

[0076] Embodiment of the unmanned aerial vehicle launching system: Referring to Figure 12 The unmanned aerial vehicle launching system provided by the embodiment comprises a launching frame 400, four launchers 200 and four unmanned aerial vehicles of the above-mentioned embodiment. The four launchers 200 are fixed on the launching frame 400.

[0077] The launching cavity extends along the vertical direction and is upwardly provided with an entrance, and the cross-sectional shape of the launching cavity is preferably circular, which is matched with the size of the unmanned aerial vehicle and can provide storage and guiding effects for the unmanned aerial vehicle.

[0078] The base sliding block 300 is slidingly arranged in the launching cavity in an up-down direction to provide boost force for the launching of the unmanned aerial vehicle. The base sliding block 300 is provided with two mounting grooves 3001, and the two mounting grooves 3001 are arranged in one-to-one correspondence with the two support seats 1001 at the bottom of the unmanned aerial vehicle. The shape of the mounting groove 3001 is matched with the shape of the support seat 1001, and the support seat 1001 is detachably arranged in the mounting groove 3001. One of the mounting grooves 3001 is provided with a first connector, and one of the support seats 1001 is provided with a second connector. The first connector and the second connector are electrically connected and detachably connected. When the support seat 1001 is inserted into the mounting groove 3001 to the right depth, the first connector and the second connector are automatically connected.

[0079] The unmanned aerial vehicle is arranged in the launching cavity and on the base sliding block 300, and the foldable landing gear and the foldable paddle of the unmanned aerial vehicle can be accommodated in the launching cavity. The base sliding block 300 can push the unmanned aerial vehicle to be launched outward.

[0080] As can be seen from the above, the main leg 2 can rotate relative to the fixed seat 1 at the first end, which facilitates the up-down turning of the landing gear to realize the folding and unfolding functions; the two auxiliary legs 3 can rotate relative to the main leg 2 at the respective connecting ends, when the auxiliary legs 3 are unfolded, the whole landing gear can play a role in stable support, and when the auxiliary legs 3 are folded, the occupied space can be maximally reduced.

[0081] Finally, it needs to be emphasized that the above is only the preferred embodiment of the present application and is not used to limit the present application. For those skilled in the art, the present application can have various changes and modifications, and any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A foldable landing gear comprising a fixed base and a supporting leg assembly, characterized in that: the supporting leg assembly comprises a main leg and two auxiliary legs, a first end of the main leg is connected with the fixed base, the main leg can rotate about the first end relative to the fixed base, a second end of the main leg is connected with a respective connecting end of each of the two auxiliary legs, and each of the auxiliary legs can rotate about the connecting end relative to the main leg.

2. The foldable landing gear according to claim 1, characterized in that: each of the auxiliary legs can be switched between a first state and a second state; in the first state, the auxiliary leg is perpendicular to the main leg; and in the second state, the auxiliary leg is parallel to the main leg.

3. The foldable landing gear according to claim 1, characterized in that: the second end of the main leg is connected with a tee joint, the tee joint is provided with two auxiliary insertion holes; the connecting end of each of the auxiliary legs is rotatably connected on one side of the tee joint, the connecting end of each of the auxiliary legs is provided with a locking tongue, the locking tongue can protrude from the end of the auxiliary leg and be inserted into the auxiliary insertion hole.

4. The foldable landing gear according to claim 3, characterized in that: the connecting end of each of the auxiliary legs is further provided with a flat pusher and a first elastic member, the first elastic member elastically abuts between the auxiliary leg and the locking tongue, the flat pusher is arranged on the outer side of the auxiliary leg and connected with the locking tongue, and the flat pusher can drive the locking tongue to retract into the auxiliary leg.

5. The foldable landing gear according to claim 3, characterized in that: the connecting end of each of the auxiliary legs is provided with a sleeve part, the sleeve part is rotatably connected on the tee joint through a first rotating shaft, and the main leg and the auxiliary leg are further connected with a second elastic member, the second elastic member applies an elastic force to the auxiliary leg to force the auxiliary leg to rotate about the first rotating shaft to the side where the auxiliary insertion hole is located.

6. The foldable landing gear according to claim 1, characterized in that: a limiting structure is arranged between the fixed base and the first end of the main leg; and when the main leg is turned down to the position, the limiting structure can inhibit the main leg from shaking.

7. The foldable landing gear according to claim 6, characterized in that: the fixed base is provided with a first limiting protrusion; the first end of the main leg is provided with a protruding part; the fixed base and the first end of the main leg are connected with a plate buckle, the plate buckle is rotatably connected on the fixed base, one end of the plate buckle is provided with a limiting part, and the protruding part can be embedded between the first limiting protrusion and the limiting part.

8. The foldable landing gear according to claim 7, characterized in that: the fixed base comprises a mounting plate and two ear plates, the two ear plates are oppositely connected on the mounting plate, the plate buckle is connected between the two ear plates through a second rotating shaft, and the mounting plate and the plate buckle are connected with a third elastic member, the third elastic member can force the limiting part to rotate away from the mounting plate.

9. The foldable landing gear according to claim 8, characterized in that: The second limiting protrusion is arranged on the ear plate and is arranged on the side of the limiting portion away from the mounting plate, and the second limiting protrusion can abut against the limiting portion.

10. The foldable landing gear according to claim 6, characterized in that: The fourth elastic member is connected between the fixing seat and the main leg, and the fourth elastic member can force the main leg to rotate downward.

11. The foldable landing gear according to claim 1, characterized in that: The locking member is arranged on the auxiliary leg, and the locking member is provided with a locking portion which protrudes from the surface of the auxiliary leg.

12. A drone, characterized by: The aircraft comprises a fuselage and two foldable landing gears according to any one of claims 1 to 11, and the two foldable landing gears are rotatably connected to the two sides of the fuselage respectively, the fuselage is provided with locking devices for locking connection with the locking members of the foldable landing gears, and the locking devices can be unlocked and separated from the locking members.

13. An unmanned aerial vehicle launch system characterized by: The unmanned aerial vehicle is arranged in the launching cavity and on the base sliding block, and the foldable landing gear and the foldable propeller of the unmanned aerial vehicle can be accommodated in the launching cavity, and the base sliding block can push the unmanned aerial vehicle to be launched outward. The unmanned aerial vehicle is arranged in the launching cavity and on the base sliding block, and the foldable landing gear and the foldable propeller of the unmanned aerial vehicle can be accommodated in the launching cavity, and the base sliding block can push the unmanned aerial vehicle to be launched outward.

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