CN220199576U - Stabilizing device of coaxial double-oar aircraft - Google Patents
Stabilizing device of coaxial double-oar aircraft Download PDFInfo
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- CN220199576U CN220199576U CN202322002184.2U CN202322002184U CN220199576U CN 220199576 U CN220199576 U CN 220199576U CN 202322002184 U CN202322002184 U CN 202322002184U CN 220199576 U CN220199576 U CN 220199576U
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- side wall
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- oar
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- aircraft body
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- 230000000087 stabilizing effect Effects 0.000 title claims abstract description 26
- 238000013016 damping Methods 0.000 claims abstract description 17
- 238000000034 method Methods 0.000 claims abstract description 5
- 230000005540 biological transmission Effects 0.000 claims abstract description 4
- 238000001125 extrusion Methods 0.000 claims description 16
- 230000001105 regulatory effect Effects 0.000 claims description 5
- 230000007306 turnover Effects 0.000 abstract description 2
- 241000282414 Homo sapiens Species 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
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Abstract
The utility model relates to the technical field of double-oar aircrafts and discloses a stabilizing device of a coaxial double-oar aircrafts, which comprises an aircrafts body, supporting legs fixedly installed at the bottom of the aircrafts body, and a stabilizing component arranged at the side wall of the aircrafts body, wherein the stabilizing component comprises a damping mechanism installed at the side wall of the aircrafts body, the damping mechanism is positioned at the bottom of the aircrafts body, an auxiliary mechanism is installed at the bottom of the aircrafts body, one end of the auxiliary mechanism is connected with the side wall of the damping mechanism, and a rotating shaft is installed at the top of the aircrafts body in a transmission way. The utility model solves the problems that the supporting legs of the existing double-oar aircraft are single in structure, but the supporting legs are not stable, and the unmanned aircraft cannot be effectively slowed down by the force received in the ground contact process when landing, so that the unmanned aircraft is easy to turn over due to instability during landing.
Description
Technical Field
The utility model relates to the technical field of double-oar aircrafts, in particular to a stabilizing device of a coaxial double-oar aircrafts.
Background
The aircraft is an appliance flying object which is manufactured by human beings, can fly off the ground, flies in space and is controlled by the human beings to fly in the atmosphere or outside the atmosphere (space), is called an aircraft which flies in the atmosphere, and is called a spacecraft which flies in space, so that the aircraft is conveniently used by the human beings, and a stabilizing device of the coaxial double-oar aircraft is used;
most of the supporting legs of the existing double-oar aircraft are single in structure, but the supporting legs are not stable, and when the unmanned aircraft falls, the force applied in the ground contact process cannot be effectively slowed down, so that the problem that the unmanned aircraft is prone to side turning due to instability during falling is solved.
Disclosure of Invention
The utility model aims to provide a stabilizing device of a coaxial double-oar aircraft, which achieves the aim of solving the problems in the background technology.
In order to achieve the above purpose, the present utility model provides the following technical solutions: a stabilizing device of a coaxial double-oar aircraft comprises an aircraft body,
the support legs are fixedly arranged at the bottom of the aircraft body;
and a stabilizing assembly disposed at a sidewall location of the aircraft body;
the stabilizing assembly comprises a damping mechanism arranged at the side wall of the aircraft body, and the damping mechanism is positioned at the bottom of the aircraft body;
the auxiliary mechanism is installed at the bottom position of the aircraft body, and one end of the auxiliary mechanism is connected with the side wall of the damping mechanism.
Preferably, the number of the supporting legs is two, the shapes and the sizes of the two supporting legs are equal, the two supporting legs are symmetrically arranged on the front and rear middle surfaces of the aircraft body respectively, and the positions of the device are supported through the supporting legs.
Preferably, a rotating shaft is arranged on the top of the aircraft body in a transmission way, and a propeller is fixedly arranged on the surface of the rotating shaft.
Preferably, the auxiliary mechanism comprises a rectangular frame, the rectangular frame is fixedly arranged at the bottom of the supporting leg, a U-shaped plate is fixedly arranged at the bottom of the rectangular frame, a sliding rod is slidably arranged on the inner wall of the U-shaped plate, a bottom plate is fixedly arranged at the bottom of the sliding rod, an auxiliary spring is fixedly arranged on the side wall of the bottom plate, and the other end of the auxiliary spring is fixedly connected with the side wall of the U-shaped plate.
Preferably, the number of the bottom plates is two, the shapes and the sizes of the two bottom plates are equal, and the two bottom plates are symmetrically arranged on the front and rear middle surfaces of the rectangular frame respectively.
Preferably, the damping mechanism comprises a long rod, the long rod is fixedly arranged on the inner wall of the rectangular frame, a turntable is fixedly arranged on the surface of the long rod, a squeezing block is arranged on the side wall of the turntable, an adjusting plate is fixedly arranged at the bottom of the squeezing block, the bottom of the adjusting plate is in contact with the inner wall of the U-shaped plate, the bottom of the adjusting plate is fixedly connected with the top of the sliding rod, a moving block is arranged on the side wall of the turntable, an inserting block is fixedly arranged at the bottom of the moving block, an extruding spring is fixedly arranged at the other end of the inserting block, a sleeve is fixedly arranged at the other end of the extruding spring, the side wall of the sleeve is in sliding connection with the inner wall of the adjusting plate, the bottom of the sleeve is fixedly connected with the inner wall of the U-shaped plate, and the inner wall of the sleeve is in sliding connection with the side wall of the inserting block.
Preferably, the side wall of carousel meshes with the lateral wall of extrusion piece through the tooth piece, the lateral wall of carousel meshes with the lateral wall of movable block through the tooth piece, and the rotation of carousel can effectually drive the position of extrusion piece and remove, can also drive the position of movable block simultaneously and remove.
The utility model provides a stabilizing device of a coaxial double-oar aircraft. The beneficial effects are as follows:
(1) According to the utility model, when the sliding rod slides in the U-shaped plate, the position of the adjusting plate can be effectively driven to be lifted, the adjusting plate further slows down vibration under the combined action of the extrusion block, the rotary table, the moving block, the inserting block, the sleeve and the extrusion spring, the overall stability of the device is effectively improved, and the problem that most of supporting legs of the existing double-oar aircraft are single in structure, but the supporting is not stable, and the unmanned aircraft cannot be effectively slowed down due to the force received in the ground contact process when falling, so that the unmanned aircraft is easy to turn on one's side due to instability when falling is solved.
(2) According to the utility model, an operator adjusts the position of the aircraft body through the controller, and when the aircraft body is under the combined action of the bottom plate, the sliding rod, the U-shaped plate and the auxiliary spring, the vibration is effectively and primarily slowed down, so that the aircraft body is prevented from being offset and turned over.
Drawings
FIG. 1 is a schematic view of the appearance structure of the present utility model;
FIG. 2 is a schematic diagram of the connection of the damping mechanism and the auxiliary mechanism of the present utility model;
FIG. 3 is a schematic view of the auxiliary mechanism of the present utility model;
FIG. 4 is a schematic view showing a part of the structure of the damping mechanism according to the present utility model;
fig. 5 is an enlarged view of a portion of fig. 3 a in accordance with the present utility model.
In the figure: 1. an aircraft body; 2. support legs; 3. a propeller; 4. a stabilizing assembly; 41. a damping mechanism; 411. an adjusting plate; 412. a sleeve; 413. extruding a spring; 414. inserting blocks; 415. a moving block; 416. a turntable; 417. a long rod; 418. extruding a block; 42. an auxiliary mechanism; 421. a rectangular frame; 422. a U-shaped plate; 423. a bottom plate; 424. an auxiliary spring; 425. a slide bar; 5. and (3) rotating the shaft.
Detailed Description
Example 1
As shown in fig. 1-5, the present utility model provides a technical solution: the stabilizing device of the coaxial double-propeller aircraft comprises an aircraft body 1, a rotating shaft 5 is arranged on the top of the aircraft body 1 in a transmission way, a propeller 3 is fixedly arranged on the surface of the rotating shaft 5,
the two support legs 2 are fixedly arranged at the bottom of the aircraft body 1, the number of the support legs 2 is two, the shape and the size of the two support legs 2 are equal, the two support legs 2 are symmetrically arranged on the front and the rear middle surfaces of the aircraft body 1 respectively, and the positions of the device are supported through the support legs 2;
the stabilizing component 4 is arranged at the side wall position of the aircraft body 1, and the stabilizing component 4 does not influence the flight of the aircraft body 1;
the stabilizing assembly 4 comprises a damping mechanism 41 arranged at the side wall of the aircraft body 1, the damping mechanism 41 is arranged at the bottom of the aircraft body 1, the damping mechanism 41 comprises a long rod 417, the long rod 417 is fixedly arranged on the inner wall of a rectangular frame 421, a turntable 416 is fixedly arranged on the surface of the long rod 417, a squeezing block 418 is arranged on the side wall of the turntable 416, an adjusting plate 411 is fixedly arranged at the bottom of the squeezing block 418, the bottom of the adjusting plate 411 is in contact with the inner wall of a U-shaped plate 422, the bottom of the adjusting plate 411 is fixedly connected with the top of a sliding rod 425, a moving block 415 is arranged on the side wall of the turntable 416, an inserting block 414 is fixedly arranged at the bottom of the moving block 415, a squeezing spring 413 is fixedly arranged at the other end of the inserting block 414, a sleeve 412 is fixedly arranged at the other end of the squeezing spring 413, the side wall of the sleeve 412 is in sliding connection with the inner wall of the adjusting plate 411, the bottom of the sleeve 412 is fixedly connected with the inner wall of the U-shaped plate 422, the inner wall of the sleeve 412 is slidably connected with the side wall of the insert block 414, the side wall of the rotary table 416 is meshed with the side wall of the extrusion block 418 through the tooth block, the side wall of the rotary table 416 is meshed with the side wall of the moving block 415 through the tooth block, the rotary table 416 can effectively drive the extrusion block 418 to move, and simultaneously can drive the moving block 415 to move, when the sliding rod 425 slides in the U-shaped plate 422, the position of the adjusting plate 411 can be effectively driven to lift, the adjusting plate 411 further slows down vibration under the combined action of the extrusion block 418, the rotary table 416, the moving block 415, the insert block 414, the sleeve 412 and the extrusion spring 413, the integral stability of the device is effectively improved, the problem that most of supporting legs of the existing double-propeller aircraft are single in structure, but the support is not stable, and the unmanned aircraft falls down, the problem that the unmanned aerial vehicle is easy to turn over due to instability when falling because the force applied in the process of being in contact with the ground cannot be effectively slowed down;
when the sliding rod 425 slides in the U-shaped plate 422, the position of the adjusting plate 411 can be effectively driven to be lifted, the adjusting plate 411 effectively drives the position of the extrusion block 418 to be lifted, the extrusion block 418 effectively drives the position of the rotary table 416 to rotate when moving, the rotary table 416 further drives the position of the moving block 415 to descend, the moving block 415 drives the position of the inserting block 414 to descend, the inserting block 414 effectively slides in the sleeve 412, the inserting block 414 further extrudes one end of the extrusion spring 413, vibration is further relieved, and the integral stability of the device is effectively improved;
example 2
On the basis of embodiment 1, an auxiliary mechanism 42 is installed at the bottom of the aircraft body 1, one end of the auxiliary mechanism 42 is connected with the side wall of the shock absorbing mechanism 41, the auxiliary mechanism 42 comprises a rectangular frame 421, the rectangular frame 421 is fixedly installed at the bottom of the supporting leg 2, a U-shaped plate 422 is fixedly installed at the bottom of the rectangular frame 421, a sliding rod 425 is slidably installed on the inner wall of the U-shaped plate 422, a bottom plate 423 is fixedly installed at the bottom of the sliding rod 425, auxiliary springs 424 are fixedly installed on the side wall of the bottom plate 423, the other ends of the auxiliary springs 424 are fixedly connected with the side wall of the U-shaped plate 422, the number of the bottom plates 423 is two, the shapes and the sizes of the two bottom plates 423 are equal, the two bottom plates 423 are symmetrically arranged on the front and rear middle surfaces of the rectangular frame 421 respectively, the position of the aircraft body 1 is adjusted by an operator through a controller, and when the aircraft body 1 is preliminarily slowed down under the combined action of the bottom plates 423, the sliding rods 425, the U422 and the auxiliary springs 424, and the condition that the aircraft body 1 is prevented from side turning on one side;
when the position of the aircraft body 1 is regulated by an operator through the controller and the aircraft body 1 falls, the bottom of the bottom plate 423 is contacted with the ground, the sliding rod 425 is caused to slide in the U-shaped plate 422 due to the gravity of the aircraft body 1, one end of the auxiliary spring 424 is extruded, and the sliding rod 425 and the auxiliary spring 424 form a simple damper, so that the vibration is effectively and primarily relieved.
Claims (7)
1. A stabilizing device for a coaxial double-oar aircraft comprises an aircraft body (1),
support legs (2) fixedly mounted at the bottom of the aircraft body (1);
and a stabilizing assembly (4) arranged at a side wall position of the aircraft body (1); the method is characterized in that:
the stabilizing assembly (4) comprises a damping mechanism (41) arranged at the side wall position of the aircraft body (1), and the damping mechanism (41) is positioned at the bottom position of the aircraft body (1);
an auxiliary mechanism (42) is arranged at the bottom of the aircraft body (1), and one end of the auxiliary mechanism (42) is connected with the side wall of the damping mechanism (41).
2. A stabilizing device for a coaxial double-oar aircraft according to claim 1, wherein: the number of the supporting legs (2) is two, the shapes and the sizes of the two supporting legs (2) are equal, and the two supporting legs (2) are symmetrically arranged on the front and rear middle surfaces of the aircraft body (1) respectively.
3. A stabilizing device for a coaxial double-oar aircraft according to claim 1, wherein: the top transmission of aircraft body (1) is installed rotation axis (5), the surface fixed mounting of rotation axis (5) has screw (3).
4. A stabilizing device for a coaxial double-oar aircraft according to claim 1, wherein: the auxiliary mechanism (42) comprises a rectangular frame (421), the rectangular frame (421) is fixedly arranged at the bottom of the supporting leg (2), a U-shaped plate (422) is fixedly arranged at the bottom of the rectangular frame (421), a sliding rod (425) is slidably arranged on the inner wall of the U-shaped plate (422), a bottom plate (423) is fixedly arranged at the bottom of the sliding rod (425), an auxiliary spring (424) is fixedly arranged on the side wall of the bottom plate (423), and the other end of the auxiliary spring (424) is fixedly connected with the side wall of the U-shaped plate (422).
5. A stabilizing device for a coaxial double-oar aircraft according to claim 4, wherein: the number of the bottom plates (423) is two, the shapes and the sizes of the two bottom plates (423) are equal, and the two bottom plates (423) are symmetrically arranged on the front middle surface and the rear middle surface of the rectangular frame (421) respectively.
6. A stabilizing device for a coaxial double-oar aircraft according to claim 1, wherein: the utility model provides a damping mechanism (41) is including stock (417), stock (417) fixed mounting is at the inner wall of rectangle frame (421), the fixed surface of stock (417) installs carousel (416), extrusion piece (418) are installed to the lateral wall of carousel (416), the bottom fixed mounting of extrusion piece (418) has regulating plate (411), the bottom of regulating plate (411) and the inner wall contact setting of U template (422), the bottom of regulating plate (411) and the top fixed connection of slide bar (425), movable block (415) are installed to the lateral wall of carousel (416), the bottom fixed mounting of movable block (415) has inserted block (414), the other end fixed mounting of inserted block (414) has extrusion spring (413), the other end fixed mounting of extrusion spring (413) has sleeve (412), the lateral wall of sleeve (412) and the inner wall sliding connection of regulating plate (411), the bottom of sleeve (412) and the inner wall fixed connection of U template (422), the lateral wall of sleeve (412) and inserted block (414) sliding connection.
7. A stabilizing device for a coaxial double-oar aircraft according to claim 6, wherein: the side wall of the rotary table (416) is meshed with the side wall of the extrusion block (418) through the tooth block, and the side wall of the rotary table (416) is meshed with the side wall of the moving block (415) through the tooth block.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322002184.2U CN220199576U (en) | 2023-07-27 | 2023-07-27 | Stabilizing device of coaxial double-oar aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322002184.2U CN220199576U (en) | 2023-07-27 | 2023-07-27 | Stabilizing device of coaxial double-oar aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220199576U true CN220199576U (en) | 2023-12-19 |
Family
ID=89144469
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322002184.2U Active CN220199576U (en) | 2023-07-27 | 2023-07-27 | Stabilizing device of coaxial double-oar aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220199576U (en) |
-
2023
- 2023-07-27 CN CN202322002184.2U patent/CN220199576U/en active Active
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