Convenient mini aircraft convenient to overhaul

Abstract

The utility model discloses a convenient mini aircraft convenient to overhaul, and relates to the technical field of aircrafts. The aircraft comprises an aircraft body, a camera is detachably arranged at the lower end of one side of the aircraft body, a fixing mechanism used in cooperation with the camera is arranged at the end of the aircraft body, and a supporting foot mechanism used in cooperation with the camera is arranged at the bottom end of the aircraft body. The fixing mechanism comprises a cross rod and a rotating rod; an inner groove and an inserting groove which are matched for use are formed in the end part of the aircraft body; by arranging and using a fixing mechanism, the two clamping plates can be conveniently pushed to move back to back, so that the two inserting rods can be conveniently pushed to move back to back, the two clamping plates can drive the two inserting rods to reset conveniently when pushing force is removed, the opposite sides of the clamping plates can be tightly attached to the outer walls of the inserting blocks, and the inserting rods are inserted into the corresponding inserting holes; and therefore, the camera can be conveniently mounted, and the later disassembly is facilitated, so that convenience is provided for the later convenient maintenance of the camera.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft, in particular to a convenient mini aircraft which is easy to repair. Background Art

[0002] An aircraft is a flying object made by humans that can take off from the ground, fly within the atmosphere or outside the atmosphere (space), and is controlled by humans. There are many types of aircraft, including convenient mini aircraft.

[0003] However, the cameras in existing portable mini aircraft are complicated to disassemble and assemble, making them inconvenient to inspect and repair. In addition, most of the existing portable mini aircraft lack a sudden drop buffer structure, resulting in a short service life.

[0004] In response to the above problems, the inventors propose a convenient mini aircraft that is easy to maintain to solve the above problems. Utility Model Content

[0005] In order to solve the problems that the cameras in the existing portable mini aircraft are complicated to disassemble and assemble and inconvenient to repair, and lack of a sudden drop buffer structure; the purpose of the utility model is to provide a portable mini aircraft that is easy to repair.

[0006] To solve the above technical problems, the present invention adopts the following technical solutions: a convenient mini aircraft that is easy to maintain, comprising an aircraft body, a camera detachably provided at the lower end of one side of the aircraft body, a fixing mechanism for use with the camera provided at the end of the aircraft body, and a supporting leg mechanism for use with the camera provided at the bottom end of the aircraft body;

[0007] The fixing mechanism includes a cross bar and a rotating rod. The end of the aircraft body is provided with an inner groove and a slot for use with each other, and the cross bar is fixedly inserted in the inner groove. The end of the aircraft body is penetrated by a through hole connected to the inner groove, and the cross bar is fixedly inserted in the through hole. A symmetrically arranged splint is slidably sleeved on the cross bar, and the splint is slidably inserted in the inner groove. A symmetrically distributed guide cylinder is fixedly installed on the inner wall of the inner groove, and a guide rod is slidably inserted in the guide cylinder. The end of the guide rod is fixedly inserted on the splint, and a through hole is penetrated by the splint, and the guide rod is fixedly inserted in the through hole. A spring 1 is fixedly installed on the opposite sides of the splint, and the spring 1 is movably sleeved on the cross bar. The opposite ends of the spring 1 are fixedly connected to the inner wall of the inner groove, and the splint is close to the insertion The opposite sides of the groove are fixedly installed with plug rods, the top of the camera is fixedly installed with a plug block, and the plug block is provided with symmetrically distributed plug holes, the plug block can be slidably inserted in the slot, and the plug rod can be slidably inserted in the plug hole, the outer diameter of the plug block is the same as the inner diameter of the slot, the outer diameter of the plug rod is the same as the inner diameter of the plug hole, the rotating rod is rotatably inserted in the bottom end of the inner groove, and the top of the rotating rod is fixedly sleeved with a ring, the bottom end of the rotating rod is fixedly sleeved with a rotating ring, and the outer wall of the rotating ring is provided with an array of grooves, symmetrically arranged push rods are fixedly installed on the ring, and the opposite ends of the push rods can movably contact the opposite sides of the splint, a torsion spring is movably sleeved on the rotating rod, and the two ends of the torsion spring are respectively fixedly connected to the inner wall of the inner groove and the ring.

[0008] Preferably, the support leg mechanism includes a base, which is fixedly mounted on the bottom end of the aircraft body, and a U-shaped rod is fixedly inserted on the base, the bottom end of the U-shaped rod is fixedly connected to a symmetrically arranged chassis one, and a damping sleeve is fixedly mounted on the bottom end of chassis one, chassis two is fixedly mounted on the bottom end of the damping sleeve, and a spring two is movably sleeved on the damping sleeve, the two ends of spring two are respectively fixedly connected to chassis one and chassis two, and the bottom ends of the two chassis twos are fixedly mounted with support rods.

[0009] Compared with the prior art, the beneficial effects of the present invention are:

[0010] 1. By setting up and using the fixing mechanism, the two splints can be easily pushed to move in opposite directions, thereby easily pushing the two insertion rods to move in opposite directions. When the thrust is removed, the two splints can drive the two insertion rods to reset conveniently, so that the opposite sides of the splints can be tightly fitted with the outer wall of the insertion block and the insertion rods can be inserted into the corresponding insertion holes, thereby realizing convenient installation of the camera and facilitating subsequent disassembly, thereby providing convenience for convenient maintenance of the camera in the later stage.

[0011] 2. Through the setting and use of the support leg mechanism, when the aircraft body suddenly fails and cannot maintain stable flight and makes a sudden landing, the use of the damping sleeve and the spring 2 can play a buffering and shock-absorbing role, thereby effectively reducing the reaction force generated by the sudden landing on the aircraft body, thereby extending the service life of the aircraft body. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0013] Figure 1 This is a schematic diagram of the structure of the utility model.

[0014] Figure 2 This is a schematic diagram of the installation of the fixing mechanism in the present utility model.

[0015] Figure 3 For this utility model Figure 2 A magnified schematic diagram of the structure in the middle.

[0016] Figure 4 For this utility model Figure 2 A magnified schematic diagram of the structure at point B in the middle.

[0017] In the figure: 1. Aircraft body; 11. Inner groove; 12. Slot; 13. Through hole; 2. Camera; 21. Insert block; 22. Socket; 3. Fixing mechanism; 31. Cross bar; 32. Turn bar; 33. Clamp; 34. Spring 1; 35. Insert rod; 36. Ring; 37. Push rod; 38. Torsion spring; 39. Guide cylinder; 310. Guide rod; 311. Through hole; 312. Turn ring; 313. Groove; 4. Support leg mechanism; 41. Base; 42. U-shaped rod; 43. Chassis 1; 44. Damping sleeve; 45. Chassis 2; 46. Spring 2; 47. Support rod. DETAILED DESCRIPTION

[0018] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0019] Example: Figures 1-4 As shown, the present invention provides a convenient mini aircraft that is easy to maintain, including an aircraft body 1, a camera 2 is detachably provided at the lower end of one side of the aircraft body 1, and a fixing mechanism 3 for use with the camera 2 is provided at the end of the aircraft body 1, and a supporting leg mechanism 4 is provided at the bottom end of the aircraft body 1 for use with the camera 2;

[0020] The fixing mechanism 3 includes a cross bar 31 and a rotating rod 32. The end of the aircraft body 1 is provided with an inner groove 11 and a slot 12 for use, and the cross bar 31 is fixedly inserted in the inner groove 11. The end of the aircraft body 1 is penetrated by a through hole 13 connected to the inner groove 11, and the cross bar 31 is fixedly inserted in the through hole 13. The setting and use of the through hole 13 provide a guarantee for the stable insertion of the cross bar 31. A symmetrically arranged splint 33 is slidably sleeved on the cross bar 31, and the splint 33 is slidably inserted in the inner groove 11 and fixedly installed on the inner wall of the inner groove 11. There are symmetrically distributed guide cylinders 39, and a guide rod 310 is slidably inserted in the guide cylinder 39. The end of the guide rod 310 is fixedly inserted on the splint 33. A through hole 311 is opened on the splint 33, and the guide rod 310 is fixedly inserted in the through hole 311. The coordinated use of the guide cylinder 39, the guide rod 310 and the through hole 311 plays a limiting and guiding role in the movement and adjustment of the splint 33. The opposite sides of the splint 33 are fixedly installed with a spring 34, and the spring 34 is movably sleeved on the cross bar 31. The opposite ends of the spring 34 are aligned with the inner groove 11. The wall is fixedly connected, and the opposite sides of the splint 33 near the slot 12 are fixedly installed with an insertion rod 35. The top of the camera 2 is fixedly installed with an insertion block 21, and the insertion block 21 is provided with symmetrically distributed insertion holes 22. The insertion block 21 can be slidably inserted into the slot 12, and the insertion rod 35 can be slidably inserted into the insertion hole 22. The outer diameter of the insertion block 21 is the same as the inner diameter of the slot 12, and the outer diameter of the insertion rod 35 is the same as the inner diameter of the insertion hole 22, thereby ensuring the insertion stability of the insertion block 21 and the insertion rod 35. The rotating rod 32 is rotatably inserted into the inner groove 11. The bottom end, and the top of the rotating rod 32 is fixedly sleeved with a ring 36, the bottom end of the rotating rod 32 is fixedly sleeved with a rotating ring 312, and the outer wall of the rotating ring 312 is provided with an array of grooves 313, the setting and use of the grooves 313 can increase friction and facilitate operation, and a symmetrically arranged push rod 37 is fixedly installed on the ring 36, and the opposite ends of the push rod 37 can be movably contacted with the opposite side of the splint 33, and a torsion spring 38 is movably sleeved on the rotating rod 32, and the two ends of the torsion spring 38 are respectively fixedly connected to the inner wall of the inner groove 11 and the ring 36.

[0021] When the cam 33 is in the closed position, the two levers 33 are in the closed position, and the two levers 33 are in the closed position, so that the levers 33 can be pushed in the closed position, thereby the levers 33 are pushed in the closed position, and the two levers 33 are pushed in the closed position, thereby the two levers 33 are pushed in the closed position, and the two levers 33 are pushed in the closed position, thereby the two levers 33 are pushed in the closed position, and the two levers 33 are pushed in the closed position, thereby the two levers 33 are pushed in the closed position,

[0022] The support leg mechanism 4 includes a base 41, which is fixedly mounted on the bottom end of the aircraft body 1, and a U-shaped rod 42 is fixedly inserted on the base 41, and the bottom end of the U-shaped rod 42 is fixedly connected to a symmetrically arranged chassis 1 43, and a damping sleeve 44 is fixedly mounted on the bottom end of the chassis 1 43, and a chassis 2 45 is fixedly mounted on the bottom end of the damping sleeve 44, and a spring 2 46 is movably sleeved on the damping sleeve 44, and the two ends of the spring 2 46 are respectively fixedly connected to the chassis 1 43 and the chassis 2 45. The combination of chassis 1 43, chassis 2 45, damping sleeve 44 and spring 2 46 constitutes a spring damping shock absorber, and the bottom ends of the two chassis 2 45 are fixedly mounted with a support rod 47.

[0023] By adopting the above technical solution, when the aircraft body 1 suddenly fails and cannot maintain stable flight, it will make a sudden landing, and when the support rod 47 contacts the landing support surface, the use of the damping sleeve 44 and the spring 2 46 can play a role in buffering and shock absorption, thereby effectively reducing the reaction force generated by the sudden landing on the aircraft body 1, thereby extending the service life of the aircraft body 1.

[0024] When the cam 312 is in the closed position, the two levers 33 are in the closed position, and the two levers 33 are in the closed position, so that the levers 33 can be pushed in the closed position, thereby the levers 33 are pushed in the closed position, and the two levers 33 are pushed in the closed position, thereby the two levers 33 are pushed in the closed position, and the two levers 33 are pushed in the closed position, thereby the two levers 33 are pushed in the closed position,

[0025] During this period, when the aircraft body 1 suddenly fails and cannot maintain stable flight, it will make a sudden drop, and when the support rod 47 contacts the landing support surface, the use of the damping sleeve 44 and the spring 2 46 can play a role in buffering and shock absorption, thereby effectively reducing the reaction force generated by the sudden drop on the aircraft body 1, thereby extending the service life of the aircraft body 1.

[0026] Obviously, those skilled in the art may make various modifications and variations to the present invention without departing from the spirit and scope of the present invention. Thus, if such modifications and variations fall within the scope of the claims of the present invention and their equivalents, the present invention is intended to include such modifications and variations.

Claims

1. A convenient mini aircraft that is easy to maintain, comprising an aircraft body (1), characterized in that: A camera (2) is detachably provided at the lower end of one side of the aircraft body (1), and a fixing mechanism (3) for use with the camera (2) is provided at the end of the aircraft body (1), and a supporting leg mechanism (4) for use with the camera (2) is provided at the bottom end of the aircraft body (1); The fixing mechanism (3) includes a crossbar (31) and a rotating rod (32), the end of the aircraft body (1) is provided with an inner groove (11) and a slot (12) for use together, and the crossbar (31) is fixedly inserted in the inner groove (11), and a symmetrically arranged clamping plate (33) is slidably sleeved on the crossbar (31), and the clamping plate (33) is slidably inserted in the inner groove (11), and the opposite sides of the clamping plate (33) are fixedly installed with a spring (34), and the spring (34) is movably sleeved on the crossbar (31), and the opposite ends of the spring (34) are fixedly connected to the inner wall of the inner groove (11), and the opposite sides of the clamping plate (33) close to the slot (12) are fixedly installed with an insertion rod (35), and the camera ( 2) is fixedly installed with an insert block (21) at the top end, and the insert block (21) is provided with symmetrically distributed insert holes (22), the insert block (21) can be slidably inserted in the slot (12), and the insert rod (35) can be slidably inserted in the insert hole (22), the rotating rod (32) is rotatably inserted in the bottom end of the inner groove (11), and the top end of the rotating rod (32) is fixedly sleeved with a ring (36), a symmetrically arranged push rod (37) is fixedly installed on the ring (36), and the opposite ends of the push rod (37) can be movably contacted with the opposite side of the splint (33), the rotating rod (32) is movably sleeved with a torsion spring (38), and the two ends of the torsion spring (38) are respectively fixedly connected to the inner wall of the inner groove (11) and the ring (36).

2. A portable mini aircraft that is easy to maintain as claimed in claim 1, characterized in that: The support leg mechanism (4) includes a base (41), the base (41) is fixedly mounted on the bottom end of the aircraft body (1), and a U-shaped rod (42) is fixedly inserted on the base (41), the bottom end of the U-shaped rod (42) is fixedly connected to a symmetrically arranged chassis one (43), and the bottom end of the chassis one (43) is fixedly mounted with a damping sleeve (44), the bottom end of the damping sleeve (44) is fixedly mounted with chassis two (45), and a spring two (46) is movably sleeved on the damping sleeve (44), the two ends of the spring two (46) are respectively fixedly connected to chassis one (43) and chassis two (45), and the bottom ends of the two chassis twos (45) are fixedly mounted with support rods (47).

3. A portable mini aircraft that is easy to maintain as claimed in claim 1, characterized in that: A through hole (13) communicating with the inner groove (11) is provided through the end of the aircraft body (1), and a cross bar (31) is fixedly inserted into the through hole (13).

4. The portable mini aircraft that is easy to maintain as claimed in claim 1, characterized in that: A symmetrically distributed guide cylinder (39) is fixedly mounted on the inner wall of the inner groove (11), and a guide rod (310) is slidably inserted into the guide cylinder (39), and the end of the guide rod (310) is fixedly inserted on the clamping plate (33).

5. A convenient mini aircraft that is easy to maintain as claimed in claim 4, characterized in that: A through hole (311) is formed through the clamping plate (33), and the guide rod (310) is fixedly inserted into the through hole (311).

6. The portable mini aircraft that is easy to maintain as claimed in claim 1, characterized in that: A rotating ring (312) is fixedly sleeved on the bottom end of the rotating rod (32), and grooves (313) distributed in an array are provided on the outer wall of the rotating ring (312).

7. The portable mini aircraft that is easy to maintain as claimed in claim 1, characterized in that: The outer diameter of the insert (21) is the same as the inner diameter of the slot (12).

8. The portable mini aircraft that is easy to maintain as claimed in claim 1, characterized in that: The outer diameter of the insertion rod (35) is the same as the inner diameter of the insertion hole (22).

Images