Rotor wing unmanned aerial vehicle with retractable unmanned aerial vehicle structure

Abstract

The invention discloses a rotor unmanned aerial vehicle with a retractable unmanned aerial vehicle structure, and relates to the technical field of unmanned aerial vehicles, the rotor unmanned aerial vehicle comprises a fuselage, a bent frame is fixedly mounted on the outer surface of the fuselage, and a protective frame is fixedly mounted at the top of the bent frame; the retractable undercarriage is used for stably supporting the unmanned aerial vehicle; and a balance driving member. According to the rotor unmanned aerial vehicle with the retractable unmanned aerial vehicle structure, when the unmanned aerial vehicle lands, the supporting blocks make contact with the ground, and when the unmanned aerial vehicle lands, the supporting blocks are affected by the weight of the unmanned aerial vehicle and extrude the ground, so that when the obliquely-arranged supporting blocks make contact with the ground, the supporting blocks make contact with the ground; damping rods connected to the surfaces of positioning blocks are driven to rotate in clamping blocks through rotating rings according to the terrain influence, so that the contact angle between supporting blocks and the ground is adjusted when the unmanned aerial vehicle is parked, the supporting blocks arranged in multiple directions are attached to and matched with the ground at the moment, the unmanned aerial vehicle is parked stably, and the phenomenon that the unmanned aerial vehicle shakes during landing is avoided.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, in particular to a rotary-wing unmanned aerial vehicle with a retractable unmanned aerial vehicle structure. Background Art

[0002] In recent years, with the gradual maturity of drone research and development technology and the reduction of manufacturing costs, drones have been widely used in various fields. In addition to military uses, they also include civilian fields such as agricultural plant protection, power inspection, geological exploration, environmental monitoring, forest fire prevention, and film and television aerial photography, and their applicable fields are still expanding rapidly.

[0003] At present, there are various types of drones on the market with increasingly rich functions. The rotors of drones cannot be retracted or folded when not in operation, and their structure makes them bulky, inconvenient to carry and easy to cause damage to the rotors during transportation. In addition, existing rotor drones often face the problem of large size during storage and transportation, occupying more space and being inconvenient to carry and store. Summary of the invention

[0004] To achieve the above objectives, the present invention is implemented through the following technical solutions: A rotary wing drone with a retractable drone structure, comprising a fuselage, a curved frame is fixedly installed on the outer surface of the fuselage, and a protective frame is fixedly installed on the top of the curved frame;

[0005] A retractable landing gear is used to stably support the UAV;

[0006] A balancing drive component, which is used for balancing the rotor of the UAV;

[0007] The retractable landing gears are provided with four, and the four retractable landing gears are fixedly installed below the outer surface of the fuselage. The balance drive member is rotatably installed at the top axis of the fuselage, and the balance drive member is rotatably adapted inside the protective frame. When the staff starts the UAV to control the flight of the UAV, the motor provided in the fuselage drives the balance drive member to rotate as a drive, thereby controlling the flight of the UAV. When the UAV completes the flight and lands, the staff controls the extension and retraction of the retractable landing gear, so that the retractable landing gear extends to contact the ground, and the retractable landing gear is provided with a flexible structure. When the UAV collides with the ground when landing, the retractable landing gear provides buffering support for the UAV, thereby avoiding collision damage to the UAV caused by the stable landing of the UAV.

[0008] The retractable landing gear includes a bottom support block, which is fixedly mounted below the outer surface of the fuselage, a stabilizing frame is fixedly mounted on the outer surface of the bottom support block, a fixed shaft is fixedly mounted on the bottom of the stabilizing frame, a round rod is rotatably mounted on the surface of the fixed shaft, and the round rod is fixedly connected to the stabilizing frame. The staff starts the drone, so that the motor in the fuselage drives the balance drive to rotate. When the drone lands, the stabilizing frame contacts the ground, so that the stabilizing frame rotates in the bottom support block and drives the round rod to rotate in the fixed shaft, so as to adjust the support angle of the stabilizing frame according to the landing terrain of the drone, so as to avoid the drone from tipping over when landing.

[0009] Preferably, the stabilizing support frame includes a clamping block, a swivel is rotatably mounted on the surface of the clamping block, a damping rod is fixedly mounted on the surface of the swivel, and a cartridge is sleeved on the outer surface of the damping rod. When the drone lands, the support block contacts the ground. When the drone lands, the support block is squeezed against the ground by the weight of the drone, so that when the tilted support block contacts the ground, the damping rod connected to the surface of the positioning block is driven to rotate in the clamping block through the swivel according to the terrain, so as to adjust the contact angle between the support block and the ground when the drone is parked. At this time, the support blocks arranged in multiple directions are all in close fit with the ground, so as to facilitate the stable parking of the drone and avoid shaking when the drone lands.

[0010] Preferably, a positioning block is fixedly installed at the bottom of the damping rod, and a supporting block is fixedly installed at the bottom of the positioning block, and the supporting block is fixedly connected to the round rod. When the supporting block rotates due to the influence of the terrain, the bomb bag is squeezed by the weight of the fuselage and deforms, so that the bomb bag can cushion the fuselage when the drone lands, so as to reduce the vibration frequency of the fuselage when landing. When the damping rod changes its inclination angle as the supporting block rotates, multiple groups of damping rods extend outwards to improve the stability of the drone when it is supported at the bottom.

[0011] Preferably, the balancing drive member includes a round seat, which is rotatably mounted at the top axis of the fuselage, a shaft is fixedly mounted at the axis of the round seat, a rotating shaft is rotatably mounted on the top of the shaft, and a limit plate is rotatably mounted on the outer surface of the rotating shaft. The staff starts the motor in the fuselage, so that the output end of the motor drives the round seat to rotate. At this time, the shaft arranged in the round seat drives the balance frame and the wing to rotate. The balance frame is a double-layer arrangement, so that the two layers of wings are spirally staggered. The double-layer wings increase the flight speed of the drone. The wings are arranged inside the protective frame, and the wings are protected by the protective frame to avoid collision when the wings rotate.

[0012] Preferably, a balancing frame is fixedly mounted on the outer surface of the shaft rod, a wing is fixedly mounted on the outer surface of the balancing frame, four groups of balancing frames are provided, the sides of the four groups of balancing frames are all provided with side connecting blocks, and the balancing frames are movably adapted to the side connecting blocks.

[0013] Preferably, the round seat comprises a positioning plate, a positioning ring is fixedly mounted at the axis of the positioning plate, a round shaft is fixedly mounted inside the positioning ring, and the round shaft is fixedly connected to the shaft rod.

[0014] Preferably, a hinge plate is rotatably mounted on the outer surface of the positioning plate, a connecting line is fixedly mounted on the surface of the positioning plate close to the hinge plate, a frame plate is fixedly mounted on the surface of the hinge plate, and the frame plate is fixedly mounted on the top of the positioning ring. The positioning plate clamps and positions the circular shaft through the hinge plate, thereby maintaining the stability of the circular shaft during rotation and preventing the circular shaft from shaking due to excessive rotation, which affects the stability of the wing during rotation.

[0015] Preferably, the balancing frame includes a positioning rod, a support rod is fixedly installed on the top of the positioning rod, the positioning rod is fixedly installed on the outer surface of the shaft rod, a center axis is fixedly installed on the outer surface of the positioning rod, a connecting ring is sleeved on the surface of the center axis, and the connecting ring is fixedly connected to the connecting line.

[0016] Preferably, an external block is fixedly mounted on the outer surface of the connecting ring, a collar is sleeved on the outer surface of the external block, a connecting rod is fixedly mounted on the surface of the collar, and the connecting rod is rotationally adapted to the positioning block.

[0017] Preferably, a clamp block is fixedly installed on the surface of the external block, a segment block is fixedly installed on the surface of the clamp block, the segment block is fixedly connected to the wing, and the outer side of the wing is fixedly connected to the support rod. The staff starts the drone, so that the shaft rod drives the positioning rod to rotate. At this time, the clamp block connected to the outer side of the positioning rod positions and clamps the wing through the segment block. When the wing rotates at high speed, it is affected by the impact of high-altitude airflow and the surface of the wing will vibrate. At this time, the external block connected to the outer side of the clamp block is connected to the connecting rod through a collar to reinforce and support the external block. When the drone is stored, the segment block is set to a flexible rubber material. The staff removes the nut installed in the segment block and presses the rubber segment block downward during storage to fold and shrink the wing to reduce the storage space. When the drone is stored, the segment block is set to a flexible rubber material. The staff removes the nut installed in the segment block and presses the rubber segment block downward during storage to fold and shrink the wing to reduce the storage space.

[0018] The present invention provides a rotary wing UAV with a retractable UAV structure, which has the following beneficial effects:

[0019] 1. The rotor UAV with a retractable UAV structure has a support block that contacts the ground when the UAV lands. When the UAV lands, the support block is squeezed against the ground by the weight of the UAV, so that when the inclined support block contacts the ground, the damping rod connected to the surface of the positioning block is driven to rotate in the clamping block through the swivel according to the terrain, so as to adjust the contact angle between the support block and the ground when the UAV is parked. At this time, the support blocks arranged in various directions are all in close contact with the ground, so as to facilitate the stable parking of the UAV and avoid shaking when the UAV lands.

[0020] 2. The rotor UAV with a retractable UAV structure, when the support block is affected by the terrain and rotates, the bomb bag is squeezed by the weight of the fuselage and deformed, so that the fuselage is cushioned by the bomb bag when the UAV lands, so as to reduce the vibration frequency of the fuselage when landing, and the damping rod changes its inclination angle as the support block rotates. At this time, multiple groups of damping rods extend outwardly to improve the stability of the bottom support of the UAV.

[0021] 3. The rotor UAV with a retractable UAV structure starts the motor in the fuselage through the staff, so that the output end of the motor drives the round seat to rotate. At this time, the shaft rod arranged in the round seat drives the balance frame and the wing to rotate. The balance frame is double-layered, so that the two layers of wings are spirally staggered. The double-layered wings increase the flight speed of the UAV. The wings are arranged inside the protective frame, and the wings are protected by the protective frame to avoid collision when the wings rotate.

[0022] Fourth, the rotary wing UAV with a retractable UAV structure uses a positioning disk to clamp and position the circular shaft through a hinge plate, thereby maintaining the stability of the circular shaft during rotation and preventing the circular shaft from shaking due to excessive rotation, which affects the stability of the wing during rotation.

[0023] 5. The rotor UAV with a retractable UAV structure is started by a staff member, so that the shaft rod drives the positioning rod to rotate. At this time, the clamping block connected to the outside of the positioning rod positions and clamps the wing through the segmented block. When the wing rotates at high speed, it is affected by the impact of high-altitude airflow and the wing surface vibrates. At this time, the external block connected to the outside of the clamping block is connected to the connecting rod through a collar to reinforce and support the external block. When the UAV is stored, the segmented block is set to a flexible rubber material. The staff removes the nut installed in the segmented block and presses the rubber segmented block downward during storage to fold and shrink the wing to reduce the storage space. When the UAV is stored, the segmented block is set to a flexible rubber material. The staff removes the nut installed in the segmented block and presses the rubber segmented block downward during storage to fold and shrink the wing to reduce the storage space. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1This is a schematic diagram of the external structure of a rotary-wing UAV with a retractable UAV structure according to the present invention;

[0025] Figure 2 This is a schematic diagram of the external structure of a rotary-wing UAV with a retractable UAV structure from another angle of the present invention;

[0026] Figure 3 This is a schematic diagram of the retractable landing gear structure of the present invention;

[0027] Figure 4 This is a schematic diagram of the structure of the stabilizing support frame of the present invention;

[0028] Figure 5 It is a schematic diagram of the enlarged structure of the balance driving member of the present invention;

[0029] Figure 6 This is a schematic diagram of the structure of the balance frame of the present invention;

[0030] Figure 7 It is a schematic diagram of the round seat structure of the present invention;

[0031] Figure 8 This is a schematic diagram of the disassembled structure of the gimbal of the present invention;

[0032] Fig. 9 This is a schematic structural diagram of the balance frame of the present invention from another angle.

[0033] In the figure: 1, protective frame; 2, bending frame; 3, fuselage; 4, retractable landing gear; 41, bottom support block; 42, stabilizing support frame; 421, clamping block; 422, swivel; 423, damping rod; 424, bomb bag; 425, positioning block; 426, supporting block; 43, round rod; 44, fixed shaft; 5, balance drive; 51, wing; 52, rotating shaft; 53, limit plate; 54, shaft rod; 5 5. Round seat; 551. Positioning plate; 552. Hinge plate; 553. Round shaft; 554. Connecting line; 555. Positioning ring; 556. Frame plate; 56. Side block; 57. Balancing frame; 571. Positioning rod; 572. Connecting ring; 573. External block; 574. Support rod; 575. Connecting rod; 576. Ring; 577. Clamp block; 578. Segment block; 579. Center axis. DETAILED DESCRIPTION

[0034] The present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments. The embodiments of the present invention are provided for the purpose of illustration and description, and are not intended to be exhaustive or to limit the present invention to the disclosed forms. Many modifications and variations will be apparent to those of ordinary skill in the art. The embodiments are selected and described in order to better illustrate the principles and practical applications of the present invention, and to enable those of ordinary skill in the art to understand the present invention and thereby design various embodiments with various modifications suitable for specific uses.

[0035] The first embodiment, as Figure 1 to Figure 2 As shown, the present invention provides a technical solution: a rotary wing UAV with a retractable UAV structure, comprising a fuselage 3, a curved frame 2 is fixedly installed on the outer surface of the fuselage 3, and a protective frame 1 is fixedly installed on the top of the curved frame 2;

[0036] Retracting the landing gear 4, the retracting landing gear 4 is used for stably supporting the UAV;

[0037] A balancing drive 5, which is used for balancing the rotor of the UAV;

[0038] There are four retractable landing gears 4, which are all fixedly installed below the outer surface of the fuselage 3. The balance drive member 5 is rotatably installed at the top axis of the fuselage 3, and the balance drive member 5 is rotatably adapted inside the protective frame 1; when the staff starts the UAV to control the flight of the UAV, the motor arranged in the fuselage 3 drives the balance drive member 5 to rotate as a drive, thereby controlling the flight of the UAV. When the UAV completes the flight and lands, the staff controls the retractable landing gear 4 to extend and retract, so that the retractable landing gear 4 extends to contact the ground, and the retractable landing gear 4 is arranged as a flexible structure. When the UAV collides with the ground when landing, the retractable landing gear 4 provides buffering support for the UAV, thereby avoiding collision damage to the UAV caused by the stable landing of the UAV.

[0039] The second embodiment is based on the first embodiment. Figure 3 to Figure 4 As shown, the retractable landing gear 4 includes a bottom support block 41, which is fixedly mounted below the outer surface of the fuselage 3, a stabilizing frame 42 is fixedly mounted on the outer surface of the bottom support block 41, a fixed shaft 44 is fixedly mounted at the bottom of the stabilizing frame 42, a round rod 43 is rotatably mounted on the surface of the fixed shaft 44, and the round rod 43 is fixedly connected to the stabilizing frame 42. The staff starts the UAV, so that the motor in the fuselage 3 drives the balance drive 5 to rotate. When the UAV lands, the stabilizing frame 42 contacts the ground, so that the stabilizing frame 42 rotates in the bottom support block 41, and drives the round rod 43 to rotate in the fixed shaft 44, so as to adjust the support angle of the stabilizing frame 42 according to the landing terrain of the UAV, so as to avoid the UAV from tipping over when landing.

[0040] The stabilizing frame 42 includes a clamping block 421, a swivel 422 is rotatably mounted on the surface of the clamping block 421, a damping rod 423 is fixedly mounted on the surface of the swivel 422, and a cartridge 424 is sleeved on the outer surface of the damping rod 423. When the drone lands, the support block 426 contacts the ground. When the drone lands, the support block 426 is squeezed with the ground by the weight of the drone, so that when the inclined support block 426 contacts the ground, the damping rod 423 connected to the surface of the positioning block 425 is driven to rotate in the clamping block 421 through the swivel 422 according to the terrain, so as to adjust the contact angle between the support block 426 and the ground when the drone is parked. At this time, the support blocks 426 arranged in multiple directions are all in close contact with the ground, so as to facilitate the stable parking of the drone and avoid shaking when the drone lands.

[0041] A positioning block 425 is fixedly installed at the bottom of the damping rod 423, and a support block 426 is fixedly installed at the bottom of the positioning block 425, and the support block 426 is fixedly connected to the round rod 43. When the support block 426 rotates due to the influence of the terrain, the bomb 424 is squeezed by the weight of the fuselage 3 to deform, so that the bomb 424 can buffer the fuselage 3 when the drone lands, so as to reduce the vibration frequency of the fuselage 3 when landing. When the damping rod 423 changes its tilt angle as the support block 426 rotates, multiple groups of damping rods 423 extend outwardly to improve the stability of the drone when it is supported at the bottom.

[0042] The third embodiment is based on the first and second embodiments. Figures 5 to 9 As shown, the balancing drive member 5 includes a round seat 55, which is rotatably mounted at the top axis of the fuselage 3, a shaft 54 ​​is fixedly mounted at the axis of the round seat 55, a rotating shaft 52 is rotatably mounted on the top of the shaft 54, and a limit plate 53 is rotatably mounted on the outer surface of the rotating shaft 52. The staff starts the motor in the fuselage 3, so that the output end of the motor drives the round seat 55 to rotate. At this time, the shaft 54 ​​set in the round seat 55 drives the balance frame 57 and the wing 51 to rotate. The balance frame 57 is a double-layer setting, so that the two-layer wing 51 is spirally staggered. The double-layer wing 51 increases the flight speed of the drone. The wing 51 is set inside the protective frame 1, and the wing 51 is protected by the protective frame 1 to avoid collision when the wing 51 rotates.

[0043] A balancing frame 57 is fixedly mounted on the outer surface of the shaft 54 ​​, and a wing 51 is fixedly mounted on the outer surface of the balancing frame 57 . There are four groups of balancing frames 57 , and side connecting blocks 56 are arranged on the sides of the four groups of balancing frames 57 , and the balancing frames 57 are movably adapted to the side connecting blocks 56 .

[0044] The round seat 55 includes a positioning plate 551 , a positioning ring 555 is fixedly installed at the axis of the positioning plate 551 , a round shaft 553 is fixedly installed inside the positioning ring 555 , and the round shaft 553 is fixedly connected to the shaft rod 54 .

[0045] The outer surface of the positioning plate 551 is rotatably mounted with a hinge plate 552, the surface of the positioning plate 551 close to the hinge plate 552 is fixedly mounted with a connecting line 554, the surface of the hinge plate 552 is fixedly mounted with a frame plate 556, and the frame plate 556 is fixedly mounted on the top of the positioning ring 555. The positioning plate 551 clamps and positions the circular shaft 553 through the hinge plate 552, thereby maintaining the stability of the circular shaft 553 during rotation, and preventing the circular shaft 553 from shaking due to excessive rotation, which affects the stability of the wing 51 during rotation.

[0046] The balancing frame 57 includes a positioning rod 571, a support rod 574 is fixedly installed on the top of the positioning rod 571, the positioning rod 571 is fixedly installed on the outer surface of the shaft rod 54, a center axis 579 is fixedly installed on the outer surface of the positioning rod 571, and a connecting ring 572 is sleeved on the surface of the center axis 579, and the connecting ring 572 is fixedly connected to the connecting line 554.

[0047] An external block 573 is fixedly mounted on the outer surface of the connecting ring 572 . A collar 576 is sleeved on the outer surface of the external block 573 . A connecting rod 575 is fixedly mounted on the surface of the collar 576 . The connecting rod 575 is rotatably adapted to the positioning block 425 .

[0048] A clamping block 577 is fixedly installed on the surface of the external block 573 , and a segmented block 578 is fixedly installed on the surface of the clamping block 577 . The segmented block 578 is fixedly connected to the wing 51 , and the outer side of the wing 51 is fixedly connected to the support rod 574 . The staff starts the drone, so that the shaft 54 ​​drives the positioning rod 571 to rotate. At this time, the clamping block 577 connected to the outside of the positioning rod 571 positions and clamps the wing 51 through the segmented block 578. When the wing 51 rotates at high speed, it is affected by the impact of high-altitude airflow and the surface of the wing 51 will vibrate. At this time, the external block 573 connected to the outside of the clamping block 577 is connected to the connecting rod 575 through the ring 576 to reinforce and support the external block 573. When the drone is stored, the segmented block 578 is set to a flexible rubber material. The staff removes the nut installed in the segmented block 578 and presses the rubber segmented block downward during storage to fold and shrink the wing 51 to reduce the storage space. When the drone is stored, the segmented block 578 is set to a flexible rubber material. The staff removes the nut installed in the segmented block 578 and presses the rubber segmented block downward during storage to fold and shrink the wing 51 to reduce the storage space.

[0049] During use, when the staff starts the drone to control the flight of the drone, the motor arranged in the fuselage 3 drives the balance drive member 5 to rotate, thereby controlling the flight of the drone. When the drone completes the flight and lands, the staff controls the extension and retraction of the retractable landing gear 4, so that the retractable landing gear 4 extends to contact the ground, and the retractable landing gear 4 is set to a flexible structure. When the drone collides with the ground during landing, the retracted landing gear 4 provides cushioning support for the drone, thereby avoiding collision damage to the drone caused by the stable landing of the drone.

[0050] The staff starts the drone, so that the motor in the fuselage 3 drives the balance drive 5 to rotate. When the drone lands, the stabilizing frame 42 contacts the ground, so that the stabilizing frame 42 rotates in the bottom support block 41, and drives the round rod 43 to rotate in the fixed shaft 44, so as to adjust the support angle of the stabilizing frame 42 according to the landing terrain of the drone, so as to avoid the drone from tipping over when landing.

[0051] When the drone lands, the support block 426 contacts the ground. When the drone lands, the support block 426 is squeezed against the ground by the weight of the drone, so that when the tilted support block 426 contacts the ground, it drives the damping rod 423 connected to the surface of the positioning block 425 to rotate in the clamping block 421 through the swivel 422 according to the influence of the terrain, so as to adjust the contact angle of the support block 426 with the ground when the drone is parked. At this time, the support blocks 426 set in multiple directions are all in close fit with the ground, so that the drone can be parked stably and shaking of the drone can be avoided when it lands.

[0052] When the support block 426 rotates due to the influence of the terrain, the bomb bag 424 is squeezed by the weight of the fuselage 3 and deformed, so that the fuselage 3 is cushioned by the bomb bag 424 when the UAV lands, so as to reduce the vibration frequency of the fuselage 3 when landing. When the damping rod 423 changes its inclination angle as the support block 426 rotates, multiple groups of damping rods 423 extend outward to improve the stability of the bottom support of the UAV.

[0053] The staff starts the motor in the fuselage 3, so that the output end of the motor drives the round seat 55 to rotate. At this time, the shaft 54 ​​set in the round seat 55 drives the balance frame 57 and the wing 51 to rotate. The balance frame 57 is a double-layer setting, so that the two layers of wings 51 are spirally staggered. The double-layer wings 51 increase the flight speed of the drone. The wings 51 are set inside the protective frame 1, and the protective frame 1 protects the wings 51 to avoid collision when the wings 51 rotate.

[0054] The positioning plate 551 clamps and positions the circular shaft 553 through the hinge plate 552, so as to maintain the stability of the circular shaft 553 during rotation, and prevent the circular shaft 553 from shaking due to excessive rotation, which affects the stability of the wing 51 during rotation.

[0055] The staff starts the drone, so that the shaft 54 ​​drives the positioning rod 571 to rotate. At this time, the clamping block 577 connected to the outside of the positioning rod 571 positions and clamps the wing 51 through the segmented block 578. When the wing 51 rotates at high speed, it is affected by the impact of high-altitude airflow and the surface of the wing 51 will vibrate. At this time, the external block 573 connected to the outside of the clamping block 577 is connected to the connecting rod 575 through the ring 576 to reinforce and support the external block 573. When the drone is stored, the segmented block 578 is set to a flexible rubber material. The staff removes the nut installed in the segmented block 578 and presses the rubber segmented block downward during storage to fold and shrink the wing 51 to reduce the storage space. When the drone is stored, the segmented block 578 is set to a flexible rubber material. The staff removes the nut installed in the segmented block 578 and presses the rubber segmented block downward during storage to fold and shrink the wing 51 to reduce the storage space.

[0056] Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field and related fields without creative work should fall within the scope of protection of the present invention. The structures, devices and operating methods not specifically described and explained in the present invention are implemented according to the conventional means in the field unless otherwise specified and limited.

Claims

1. A rotary wing drone with a retractable drone structure, characterized in that: include: A fuselage (3), a curved frame (2) being fixedly mounted on the outer surface of the fuselage (3), and a protective frame (1) being fixedly mounted on the top of the curved frame (2); A retractable landing gear (4), wherein the retractable landing gear (4) is used for stably supporting the UAV; A balancing drive component (5), the balancing drive component (5) is used for adjusting the balance of the unmanned aerial vehicle rotor; The retractable landing gear (4) is provided with four, and the four retractable landing gears (4) are fixedly mounted below the outer surface of the fuselage (3); the balancing drive member (5) is rotatably mounted at the top axis of the fuselage (3), and the balancing drive member (5) is rotatably adapted inside the protective frame (1); The retractable landing gear (4) comprises a bottom support block (41), wherein the bottom support block (41) is fixedly mounted below the outer surface of the fuselage (3), a stabilizing frame (42) is fixedly mounted on the outer surface of the bottom support block (41), a fixed shaft (44) is fixedly mounted at the bottom of the stabilizing frame (42), a round rod (43) is rotatably mounted on the surface of the fixed shaft (44), and the round rod (43) is fixedly connected to the stabilizing frame (42).

2. The rotary-wing UAV with a retractable UAV structure according to claim 1, characterized in that: The stabilizing support frame (42) comprises a clamping block (421), a rotating ring (422) is rotatably mounted on the surface of the clamping block (421), a damping rod (423) is fixedly mounted on the surface of the rotating ring (422), and an elastic bag (424) is sleeved on the outer surface of the damping rod (423).

3. The rotary wing UAV with a retractable UAV structure according to claim 2, characterized in that: A positioning block (425) is fixedly installed at the bottom of the damping rod (423), a supporting block (426) is fixedly installed at the bottom of the positioning block (425), and the supporting block (426) is fixedly connected to the round rod (43).

4. The rotary-wing UAV with a retractable UAV structure according to claim 1, characterized in that: The balancing driving member (5) comprises a round seat (55), the round seat (55) is rotatably mounted at the top axis of the fuselage (3), a shaft (54) is fixedly mounted at the axis of the round seat (55), a rotating shaft (52) is rotatably mounted at the top of the shaft (54), and a limit plate (53) is rotatably mounted on the outer surface of the rotating shaft (52).

5. The rotary wing UAV with a retractable UAV structure according to claim 4, characterized in that: A balancing frame (57) is fixedly mounted on the outer surface of the shaft rod (54), and a wing (51) is fixedly mounted on the outer surface of the balancing frame (57). Four groups of balancing frames (57) are provided, and side connecting blocks (56) are provided on the sides of the four groups of balancing frames (57), and the balancing frames (57) are movably matched with the side connecting blocks (56).

6. The rotary wing UAV with a retractable UAV structure according to claim 5, characterized in that: The round seat (55) comprises a positioning plate (551), a positioning ring (555) is fixedly mounted at the axis of the positioning plate (551), a round shaft (553) is fixedly mounted inside the positioning ring (555), and the round shaft (553) is fixedly connected to the shaft rod (54).

7. The rotary-wing UAV with a retractable UAV structure according to claim 6, characterized in that: A hinge plate (552) is rotatably mounted on the outer surface of the positioning plate (551), a connecting line (554) is fixedly mounted on the surface of the positioning plate (551) close to the hinge plate (552), a frame plate (556) is fixedly mounted on the surface of the hinge plate (552), and the frame plate (556) is fixedly mounted on the top of the positioning ring (555).

8. The rotary-wing UAV with a retractable UAV structure according to claim 5, characterized in that: The balancing frame (57) comprises a positioning rod (571), a support rod (574) is fixedly mounted on the top of the positioning rod (571), the positioning rod (571) is fixedly mounted on the outer surface of the shaft rod (54), a center shaft (579) is fixedly mounted on the outer surface of the positioning rod (571), a connecting ring (572) is sleeved on the surface of the center shaft (579), and the connecting ring (572) is fixedly connected to the connecting line (554).

9. The rotary-wing UAV with a retractable UAV structure according to claim 8, characterized in that: An external block (573) is fixedly mounted on the outer surface of the connecting ring (572), a collar (576) is sleeved on the outer surface of the external block (573), a connecting rod (575) is fixedly mounted on the surface of the collar (576), and the connecting rod (575) is rotationally adapted to the positioning block (425).

10. The rotary-wing UAV with a retractable UAV structure according to claim 9, characterized in that: A clamping block (577) is fixedly mounted on the surface of the external block (573), a segmented block (578) is fixedly mounted on the surface of the clamping block (577), the segmented block (578) is fixedly connected to the wing (51), and the outer side of the wing (51) is fixedly connected to the support rod (574).

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