CN212448045U - Aircraft tail wing convenient to disassemble, assemble and maintain on general aircraft - Google Patents
Aircraft tail wing convenient to disassemble, assemble and maintain on general aircraft Download PDFInfo
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- CN212448045U CN212448045U CN202020592833.2U CN202020592833U CN212448045U CN 212448045 U CN212448045 U CN 212448045U CN 202020592833 U CN202020592833 U CN 202020592833U CN 212448045 U CN212448045 U CN 212448045U
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- 238000012423 maintenance Methods 0.000 claims abstract description 15
- 230000007246 mechanism Effects 0.000 claims description 40
- 230000008878 coupling Effects 0.000 claims description 7
- 238000010168 coupling process Methods 0.000 claims description 7
- 238000005859 coupling reaction Methods 0.000 claims description 7
- 230000006835 compression Effects 0.000 claims description 6
- 238000007906 compression Methods 0.000 claims description 6
- 230000000149 penetrating effect Effects 0.000 claims description 5
- 238000009434 installation Methods 0.000 abstract description 5
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
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Abstract
The utility model discloses an aircraft fin of being convenient for dismouting maintenance on general aircraft, which comprises a bod, organism top one side is equipped with perpendicular fin, organism one side front end is equipped with horizontal fin, two respectively with the rear end horizontal fin one side is equipped with the elevator, two the horizontal fin rear end is equipped with fixed establishment respectively, fixed establishment is equipped with the fixed block respectively in two horizontal fin one sides, threaded hole has still been seted up respectively in both sides in the recess of organism one side front end and rear end to fixed establishment. A universal aircraft on be convenient for dismouting maintenance's aircraft fin, pass through the horizontal fin with traditional small-size private aircraft and pass through fixed establishment and set up to detachable structure, can carry out quick pulling down when maintaining its horizontal fin, it is more convenient to also be called traditional mode to its installation simultaneously, can improve the efficiency of the dismantlement and the installation of its horizontal fin and reduce its maintenance work volume.
Description
Technical Field
The utility model relates to a flight equipment technical field, in particular to be convenient for dismouting maintenance's aircraft fin on general aircraft.
Background
The empennage is a device arranged at the tail of the airplane, and can enhance the stability of the flight. Most of the tail wings include a horizontal tail wing and a vertical tail wing, and a few of them adopt a V-shaped tail wing, which can be used to control the pitch, yaw and tilt of the aircraft to change the flight attitude, and the tail wing is an important component of the flight control system, but compared with some small-sized private aircraft, the horizontal tail wing is troublesome to detach and install when it needs to be repaired or replaced, and the horizontal tail wing is inconvenient to maintain when it is still on the body.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide an aircraft fin of being convenient for dismouting maintenance on the general aircraft can effectively solve the problem in the background art.
In order to achieve the above purpose, the utility model adopts the following technical scheme:
the utility model provides an aircraft tail wing convenient to dismouting is maintained on general aircraft, includes the organism, organism top one side is equipped with perpendicular fin, organism one side front end is equipped with horizontal tail wing, two respectively with the rear end horizontal tail wing one side is equipped with the elevator, two the horizontal tail wing rear end is equipped with fixed establishment respectively.
Preferably, the fixing mechanism is provided with fixing blocks on one side of each of the two horizontal rear wings, the fixing mechanism is further provided with threaded holes in the grooves at the front end and the rear end of one side of the machine body, and the horizontal rear wings are fixedly installed in the grooves in the machine body through the two locking mechanisms in the fixing blocks.
Preferably, the locking mechanism is symmetrically provided with two worms in the cavity of the fixed block, one side of each worm is arranged in the fixed bearing at one side in the fixed block in an inserting way through the rotating shaft, the other side of each worm is provided with a connecting shaft, the connecting shaft is arranged in the fixed block in an inserting way, and the connecting shaft extends into the cavity of the horizontal tail wing, one side of the connecting shaft is provided with a first bevel gear, and the first bevel gears are positioned in the inner cavity of the horizontal tail wing, a driving mechanism is arranged between the two first bevel gears, a turbine is arranged at the bottom of the first bevel gear, a screw rod is arranged in the turbine, the screw rod is inserted and installed in the turbine, a limiting block is arranged on the other side of the screw rod, and the limiting blocks are arranged in the limiting grooves in the fixing blocks in an inserting mode, the horizontal tail wing can be fixedly arranged in the machine body through the fixing blocks through the arrangement of the two locking mechanisms, and the functions of convenience in detachment and installation can be achieved.
Preferably, two rotary troughs have been seted up to the symmetry in the fixed block, be equipped with a plurality of ball in the rotary trough, the turbine alternates through the draw-in groove of its outer wall and installs in the rotary trough, set up the round thread groove on the turbine inner wall, through the setting of rotary trough and ball, the draw-in groove of cooperation turbine outer wall simultaneously can make the turbine at the rotary trough internal fixation rotate, and then reaches and removes the screw rod in the turbine through the restriction piece.
Preferably, the driving mechanism comprises a second bevel gear, a fixing shaft is arranged at the bottom of the second bevel gear, the fixing shaft is arranged in a fixing bearing on the bottom surface of the cavity in the horizontal tail wing in a penetrating manner, a rotating mechanism is arranged below the fixing shaft, and the rotating mechanism is located on the fixing shaft in the cavity below the horizontal tail wing.
Preferably, rotary mechanism includes the handle, the handle top surface is equipped with fixed pipe, fixed pipe alternates to be installed on the fixed axle, two spacing grooves have been seted up in the fixed pipe, be equipped with a plurality of coupling mechanism in the fixed pipe wall body, through coupling mechanism's setting, can make when using, drag the handle out, when not using, with the handle automatic retraction in the cavity of horizontal fin.
Preferably, coupling mechanism is equipped with a plurality of connecting rod at horizontal fin below cavity top surface, the connecting rod alternates to be installed in the connecting hole that corresponds on the fixed pipe, the connecting rod bottom is equipped with the dog, be equipped with compression spring on the connecting rod to compression spring is located the connecting rod between the top surface in dog and the fixed pipe connecting hole.
Compared with the prior art, the utility model discloses following beneficial effect has:
a universal aircraft on be convenient for dismouting maintenance's aircraft fin, pass through the horizontal fin with traditional small-size private aircraft and pass through fixed establishment and set up to detachable structure, can carry out quick pulling down when maintaining its horizontal fin, it is more convenient to also be called traditional mode to its installation simultaneously, can improve the efficiency of the dismantlement and the installation of its horizontal fin and reduce its maintenance work volume.
Drawings
FIG. 1 is a schematic view of the main structure of the present invention;
fig. 2 is a schematic structural view of the locking mechanism of the present invention;
FIG. 3 is an enlarged view taken at A in FIG. 2;
FIG. 4 is a schematic view of a turbine mounting structure of the present invention;
fig. 5 is a schematic structural view of the driving mechanism of the present invention;
fig. 6 is an enlarged view at B in fig. 5.
In the figure: 1. a body; 2. a vertical tail; 3. a horizontal rear wing; 4. an elevator; 5. a fixing mechanism; 6. A fixed block; 7. a threaded hole; 8. a locking mechanism; 9. a worm; 10. a connecting shaft; 11. a first bevel gear; 12. a turbine; 13. a screw; 14. a limiting block; 15. an active mechanism; 16. rotating the groove; 17. a ball bearing; 18. a card slot; 19. a screw groove; 20. a second bevel gear; 21. a fixed shaft; 22. a rotation mechanism; 23. A handle; 24. a fixed tube; 25. a limiting groove; 26. a connecting mechanism; 27. a connecting rod; 28. a stopper; 29. compressing the spring.
Detailed Description
In order to make the technical means, creation features, achievement purposes and functions of the present invention easy to understand, the present invention is further described below with reference to the following embodiments.
In the description of the present invention, it should be noted that the terms "upper", "lower", "inner", "outer", "front end", "rear end", "both ends", "one end", "the other end" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element to which the reference is made must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "disposed," "connected," and the like are to be construed broadly, and for example, "connected" may be either fixedly connected or detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
As shown in fig. 1-6, the utility model provides a pair of aircraft fin of being convenient for dismouting maintenance on general aircraft, including organism 1, 1 top one side of organism is equipped with vertical tail 2, and 1 one side front end of organism is equipped with horizontal tail 3 respectively with the rear end, and 3 one sides of two horizontal tail are equipped with elevator 4, and 3 rear ends of two horizontal tail are equipped with fixed establishment 5 respectively.
The fixing mechanism 5 is provided with a fixing block 6 on one side of two horizontal tail wings 3, the fixing mechanism 5 is also provided with threaded holes 7 on two sides in grooves at the front end and the rear end of one side of the machine body 1, the horizontal tail wings 3 are fixedly arranged in the grooves in the machine body 1 through two locking mechanisms 8 in the fixing block 6, the locking mechanisms 8 are symmetrically provided with two worms 9 in a cavity in the fixing block 6, one side of each worm 9 is inserted and arranged in a fixing bearing on one side in the fixing block 6 through a rotating shaft, the other side of each worm 9 is provided with a connecting shaft 10, the connecting shaft 10 is inserted and arranged in the fixing block 6, the connecting shaft 10 extends into the cavity in the horizontal tail wing 3, one side of the connecting shaft 10 is provided with a first bevel gear 11, the first bevel gear 11 is positioned in the cavity in the horizontal tail wing 3, a driving mechanism, a screw 13 is arranged in the turbine 12, the screw 13 is installed in the turbine 12 in an inserting manner, a limiting block 14 is arranged on the other side of the screw 13, the limiting block 14 is installed in a limiting groove in the fixed block 6 in an inserting manner, two rotating grooves 16 are symmetrically formed in the fixed block 6, a plurality of balls 17 are arranged in the rotating grooves 16, the turbine 12 is installed in the rotating grooves 16 in an inserting manner through a clamping groove 18 on the outer wall of the turbine 12, a circle of spiral groove 19 is formed in the inner wall of the turbine 12, the driving mechanism 15 comprises a second bevel gear 20, a fixed shaft 21 is arranged at the bottom of the second bevel gear 20, the fixed shaft 21 is installed in a fixed bearing on the bottom surface of the inner cavity of the horizontal tail fin 3 in an inserting manner, a rotating mechanism 22 is arranged below the fixed shaft 21, the rotating mechanism 22 is positioned on the fixed shaft 21 in the cavity below the horizontal tail fin, be equipped with a plurality of coupling mechanism 26 in the fixed pipe 24 wall body, coupling mechanism 26 is equipped with a plurality of connecting rod 27 at horizontal fin 3 below cavity top surface, and connecting rod 27 alternates to be installed in the connecting hole that corresponds on fixed pipe 24, and connecting rod 27 bottom is equipped with dog 28, is equipped with compression spring 29 on the connecting rod 27 to compression spring 29 is located dog 28 and fixed pipe 24 and goes up the connecting rod 27 between the interior top surface of connecting hole.
It should be noted that, when the horizontal tail fin 3 is to be disassembled to maintain it, the protective cover at the bottom of the horizontal tail fin 3 is opened and the handle 23 is pulled downward, so that the handle 23 moves downward through the connecting rod 27 in the fixed tube 24, and the two limiting grooves 25 in the fixed tube 24 are simultaneously clamped onto the two limiting blocks at the outer side of the fixed shaft 21, then the handle 23 is rotated, the fixed tube 24 is further driven to rotate through the handle 23, the two limiting grooves 25 in the fixed tube 24 are further driven to rotate the limiting blocks at the outer walls of the two fixed shafts 21, and further the fixed shaft 21 is driven to rotate, and further the second bevel gear 20 is driven to rotate, and further the two first bevel gears 11 are driven to rotate in the same direction, and further the corresponding worm 9 is driven to rotate through the connecting shaft 10, and then the two worms 9 drive the corresponding turbines 12 to rotate in the rotary grooves 16 in the fixed block 6, and because the screw 13 is prevented from rotating together with the turbines 12 in the limiting grooves in the fixed block 6 through the limiting blocks 14, the screw 13 is driven to rotate through the screw grooves 19 in the turbines 12, and then the screw 13 is screwed out of the threaded hole 7 in the machine body 1, so that the horizontal tail wing 3 is integrally taken down to be maintained.
The basic principles and the main features of the invention and the advantages of the invention have been shown and described above. It will be understood by those skilled in the art that the present invention is not limited to the above embodiments, and that the foregoing embodiments and descriptions are provided only to illustrate the principles of the present invention without departing from the spirit and scope of the present invention. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (7)
1. The utility model provides an aircraft tail wing of being convenient for dismouting maintenance on general aircraft which characterized in that: including organism (1), organism (1) top one side is equipped with vertical tail (2), organism (1) one side front end is equipped with horizontal tail (3) respectively with the rear end, two horizontal tail (3) one side is equipped with elevator (4), two horizontal tail (3) rear end is equipped with fixed establishment (5) respectively.
2. An aircraft tail for easy removal and maintenance of a general purpose aircraft as claimed in claim 1, wherein: fixed block (6) are respectively arranged on one side of each of the two horizontal tail wings (3) of the fixed mechanism (5), threaded holes (7) are respectively formed in the front end of one side of the machine body (1) and the grooves in the rear end of the machine body (5), and the horizontal tail wings (3) are fixedly installed in the grooves in the machine body (1) through two locking mechanisms (8) in the fixed blocks (6).
3. An aircraft tail for easy removal and maintenance of a general purpose aircraft as claimed in claim 2, wherein: the locking mechanism (8) is symmetrically provided with two worms (9) in a cavity of the fixed block (6), one side of each worm (9) is arranged in a fixed bearing on one side in the fixed block (6) in a penetrating manner through a rotating shaft, the other side of each worm (9) is provided with a connecting shaft (10), each connecting shaft (10) is arranged in the fixed block (6) in a penetrating manner, each connecting shaft (10) extends to the cavity in the horizontal tail wing (3), one side of each connecting shaft (10) is provided with a first bevel gear (11), each first bevel gear (11) is arranged in the cavity in the horizontal tail wing (3), a driving mechanism (15) is arranged between the two first bevel gears (11) below, the bottom of each first bevel gear (11) is provided with a turbine (12), a screw (13) is arranged in the turbine (12), the screw (13) is arranged in the turbine (12) in a penetrating manner, and the other side of the, and the limiting block (14) is inserted and installed in the limiting groove in the fixing block (6).
4. An aircraft tail for easy removal and maintenance of a general purpose aircraft as defined in claim 3, wherein: two rotary grooves (16) are symmetrically formed in the fixed block (6), a plurality of balls (17) are arranged in the rotary grooves (16), the turbine (12) is installed in the rotary grooves (16) in a penetrating mode through clamping grooves (18) in the outer wall of the turbine (12), and a circle of spiral groove (19) is formed in the inner wall of the turbine (12).
5. An aircraft tail for easy removal and maintenance of a general purpose aircraft as defined in claim 4, wherein: initiative mechanism (15) include second bevel gear (20), second bevel gear (20) bottom is equipped with fixed axle (21), fixed axle (21) alternate and install in the fixing bearing of cavity bottom surface in horizontal fin (3), fixed axle (21) below is equipped with rotary mechanism (22), rotary mechanism (22) are located fixed axle (21) in horizontal fin (3) below cavity.
6. An aircraft tail for easy removal and maintenance of a general purpose aircraft as defined in claim 5, wherein: rotary mechanism (22) include handle (23), handle (23) top surface is equipped with fixed pipe (24), fixed pipe (24) alternate and install on fixed axle (21), set up two spacing grooves (25) in fixed pipe (24), be equipped with a plurality of coupling mechanism (26) in fixed pipe (24) wall body.
7. An aircraft tail for easy removal and maintenance of a general purpose aircraft as defined in claim 6, wherein: coupling mechanism (26) are equipped with a plurality of connecting rod (27) at horizontal tail wing (3) below cavity top surface, connecting rod (27) alternate and install in the connecting hole that corresponds on fixed pipe (24), connecting rod (27) bottom is equipped with dog (28), be equipped with compression spring (29) on connecting rod (27) to compression spring (29) are located dog (28) and fixed pipe (24) and go up connecting rod (27) between the top surface in the connecting hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020592833.2U CN212448045U (en) | 2020-04-20 | 2020-04-20 | Aircraft tail wing convenient to disassemble, assemble and maintain on general aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020592833.2U CN212448045U (en) | 2020-04-20 | 2020-04-20 | Aircraft tail wing convenient to disassemble, assemble and maintain on general aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212448045U true CN212448045U (en) | 2021-02-02 |
Family
ID=74467451
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020592833.2U Active CN212448045U (en) | 2020-04-20 | 2020-04-20 | Aircraft tail wing convenient to disassemble, assemble and maintain on general aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN212448045U (en) |
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2020
- 2020-04-20 CN CN202020592833.2U patent/CN212448045U/en active Active
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| PP01 | Preservation of patent right |
Effective date of registration: 20240624 Granted publication date: 20210202 |
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| PP01 | Preservation of patent right | ||
| PD01 | Discharge of preservation of patent |
Date of cancellation: 20240805 Granted publication date: 20210202 |
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