CN221114350U - Vertical tail folding mechanism for airplane - Google Patents
Vertical tail folding mechanism for airplane Download PDFInfo
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- CN221114350U CN221114350U CN202323132201.0U CN202323132201U CN221114350U CN 221114350 U CN221114350 U CN 221114350U CN 202323132201 U CN202323132201 U CN 202323132201U CN 221114350 U CN221114350 U CN 221114350U
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- 239000003381 stabilizer Substances 0.000 description 2
- 230000007306 turnover Effects 0.000 description 2
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- 230000009286 beneficial effect Effects 0.000 description 1
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- 238000012986 modification Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Abstract
The utility model discloses a vertical fin folding mechanism for an aircraft, which comprises a fixed structure and a folding structure, wherein the folding structure is fixedly connected to the top outer side surface of the fixed structure, the fixed structure comprises a tail unit and an air flow plate unit, the air flow plate unit is movably connected to the outer side surface of the tail unit, the folding structure comprises a folding unit, a vertical tail unit and a plug-in unit, the folding unit is fixedly connected to the top surface of the tail unit, the vertical tail unit is movably connected to the outer side surface of the folding unit, and the plug-in unit is fixedly connected to the outer side surface of the vertical tail unit. This a vertical fin folding mechanism for aircraft, when vertical fin carries out decurrent upset through folding connecting rod, through pegging graft the dead lever in the inboard of pegging graft the dead bolt for fixed vertical fin can pack up the vertical fin when aircraft straight line flies like this, thereby reduces the shielding of air current, lets the aircraft can fly more rapidly.
Description
Technical Field
The utility model relates to the technical field of aircrafts, in particular to a vertical fin folding mechanism for an aircraft.
Background
The aircraft tail fin comprises a horizontal tail fin and a vertical tail fin, wherein the horizontal tail fin consists of a fixed horizontal stabilizer and a movable elevator, the vertical tail fin comprises a fixed vertical stabilizer and a movable rudder, and the main function of the tail fin is to control the aircraft to lift and deflect and ensure the aircraft to fly stably.
The utility model discloses a vertical fin folding unfolding and limiting locking mechanism, which comprises a right vertical fin, a left vertical fin, a vertical fin rotating shaft and a shell, wherein shaft holes are symmetrically formed in the upper sides of the left end face and the right end face of the shell, the vertical fin rotating shaft is rotationally connected between the shaft holes, a driving torsion spring is sleeved in the middle position of the vertical fin rotating shaft, rubber stop blocks are symmetrically arranged on the rear upper sides of the left end face and the right end face of the shell, the right vertical fin and the left vertical fin are symmetrically and fixedly connected to the two ends of the vertical fin rotating shaft, an arc-shaped notch is formed in the rear side of the lower end of the right vertical fin, a mounting hole is formed in the right end face of the shell, the mounting hole is arranged corresponding to the arc-shaped notch, a spring pin is arranged at the mounting hole, and the telescopic end of the spring pin protrudes out of the shell.
This vertical fin is folded and is expanded and spacing locking mechanism can't let the vertical fin fold, leads to the aircraft when straight line flight, and the vertical fin receives the windage, can't let the aircraft carry out full speed's flight, seriously influences the speed of flight.
Disclosure of utility model
The utility model aims to provide a vertical fin folding mechanism for an aircraft, which is used for solving the problems in the background art.
In order to achieve the above purpose, the present utility model provides the following technical solutions: a vertical fin folding mechanism for aircraft includes fixed knot and beta structure, beta structure fixed connection is in fixed knot's top outside surface.
The fixed knot constructs including fin unit and air current board unit, air current board unit swing joint is in the outside surface of fin unit, the beta structure includes folding unit, vertical fin unit and grafting unit, folding unit fixed connection is in the top surface of fin unit, vertical fin unit swing joint is in the outside surface of folding unit, grafting unit fixed connection is in the outside surface of vertical fin unit.
Preferably, the tail unit comprises an aircraft tail end and a horizontal tail, the aircraft tail end is arranged on the inner side of the folding structure, the horizontal tail is fixedly connected to the outer side surface of the aircraft tail end, and the tail unit is used for enabling the aircraft to fly horizontally.
Preferably, the air flow plate unit comprises a horizontal air flow plate and a horizontal connecting rod, wherein the horizontal air flow plate is movably connected to the outer side surface of the horizontal connecting rod, the horizontal connecting rod is movably connected to the rear side surface of the horizontal tail wing, and the air flow plate unit is used for changing the height position of the aircraft.
Preferably, the folding unit comprises a bottom connecting plate, a rotating shaft supporting plate and a folding connecting rod, wherein the bottom connecting plate is fixedly connected to the top surface of the horizontal tail wing, the rotating shaft supporting plate is fixedly connected to the top surface of the bottom connecting plate, the folding connecting rod is movably connected to the inner side panel of the rotating shaft supporting plate, and the folding unit is permanently connected with the vertical tail wing unit.
Preferably, the vertical tail unit comprises a vertical tail, a vertical connecting rod and a vertical airflow plate, wherein the vertical tail is movably connected to the outer side surface of the folding connecting rod, the vertical connecting rod is movably connected to the outer side surface of the vertical tail, the vertical airflow plate is movably connected to the outer side surface of the vertical connecting rod, and the vertical tail unit is used for enabling the aircraft to fly straight.
Preferably, the plug-in unit comprises a plug-in fixing rod and a plug-in fixing bolt, wherein the plug-in fixing rod is fixedly connected to the outer side surface of the vertical tail wing, the plug-in fixing bolt is fixedly connected to the top surface of the horizontal tail wing, and the plug-in unit is used for fixing the folding mode of the vertical tail wing.
Preferably, the number of the horizontal tails is two, the two horizontal tails are arranged at the left side and the right side of the tail end of the airplane in a mirror image mode, the number of the folding structures is consistent with that of the horizontal tails, and the folding structures are arranged at the top of the horizontal tails, so that the airplane can fly horizontally.
Compared with the prior art, the utility model has the beneficial effects that: this a vertical fin folding mechanism for aircraft, when vertical fin carries out decurrent upset through folding connecting rod, through pegging graft the dead lever in the inboard of pegging graft the dead bolt for fixed vertical fin can pack up the vertical fin when aircraft straight line flies like this, thereby reduces the shielding of air current, lets the aircraft can fly more rapidly.
Drawings
FIG. 1 is a schematic view of the outside structure of the present utility model;
FIG. 2 is a schematic view of the inside structure of the present utility model;
FIG. 3 is an enlarged schematic view of the structure of FIG. 2A according to the present utility model;
Fig. 4 is a schematic view of a folded structure of the present utility model.
In the figure: 1. a fixed structure; 101. an aircraft tail end; 102. a horizontal tail; 103. a horizontal air flow plate; 104. a horizontal connecting rod; 2. a folding structure; 201. a bottom connecting plate; 202. a rotating shaft support plate; 203. folding the connecting rod; 204. a vertical tail; 205. a vertical connecting rod; 206. a vertical air flow plate; 207. inserting a fixing rod; 208. and (5) inserting a fixing bolt.
Detailed Description
The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
Referring to fig. 1-4, the present utility model provides a technical solution: a vertical fin folding mechanism for an aircraft comprises a fixed structure 1 and a folding structure 2, wherein the folding structure 2 is fixedly connected to the top outer side surface of the fixed structure 1.
The fixed structure 1 comprises a tail unit and an air flow plate unit, the air flow plate unit is movably connected to the outer side surface of the tail unit, the folding structure 2 comprises a folding unit, a vertical tail unit and a plug-in unit, the folding unit is fixedly connected to the top surface of the tail unit, the vertical tail unit is movably connected to the outer side surface of the folding unit, and the plug-in unit is fixedly connected to the outer side surface of the vertical tail unit.
The tail unit includes aircraft tail end 101 and tailplane 102, and aircraft tail end 101 is settled in the inboard of beta structure 2, and tailplane 102 fixed connection is in the outside surface of aircraft tail end 101, and the quantity of tailplane 102 is two, and two tailplanes 102 are the mirror image and settle in the left and right sides of aircraft tail end 101, and the quantity of beta structure 2 is unanimous with tailplane 102's quantity, settles at tailplane 102's the top, can let the aircraft keep the horizontal flight like this, and the tail unit is used for letting the aircraft keep the horizontal flight, and tailplane 102 is used for letting aircraft tail end 101 keep the horizontal flight in the time of the flight.
The air current board unit includes horizontal air current board 103 and horizontal connecting rod 104, and horizontal air current board 103 swing joint is in the outside surface of horizontal connecting rod 104, and horizontal connecting rod 104 swing joint is in the rear side surface of tailplane 102, and the air current board unit is used for changing the high low position that the aircraft was flown, and horizontal air current board 103 can overturn through horizontal connecting rod 104, can change the upper and lower flight height of aircraft tailplane 101.
The folding unit includes bottom connecting plate 201, pivot backup pad 202 and folding connecting rod 203, bottom connecting plate 201 fixed connection is in the top surface of tailplane 102, pivot backup pad 202 fixed connection is in the top surface of bottom connecting plate 201, folding connecting rod 203 swing joint is in the inboard panel of pivot backup pad 202, the vertical tail unit is connected forever to the folding unit, bottom connecting plate 201 is used for carrying out fixed connection with pivot backup pad 202 and tailplane 102, pivot backup pad 202 is used for bearing folding connecting rod 203, folding connecting rod 203 can drive vertical tail 204 and overturn.
The vertical tail unit includes vertical fin 204, vertical connecting rod 205 and vertical air current board 206, vertical fin 204 swing joint is in the outside surface of folding connecting rod 203, vertical connecting rod 205 swing joint is in the outside surface of vertical fin 204, vertical air current board 206 swing joint is in the outside surface of vertical connecting rod 205, vertical tail unit is used for letting the aircraft carry out straight flight, vertical fin 204 is used for keeping the straight line flight of aircraft tail end 101, vertical connecting rod 205 is used for driving vertical air current board 206 and overturns, vertical air current board 206 upset can change the direction of flight of aircraft tail end 101.
The plug-in unit includes a plug-in fixing rod 207 and a plug-in fixing bolt 208, the plug-in fixing rod 207 is fixedly connected to the outer side surface of the vertical tail 204, the plug-in fixing bolt 208 is fixedly connected to the top surface of the horizontal tail 102, and the plug-in unit is used for fixing the folding manner of the vertical tail 204, and when the vertical tail 204 is turned down through the folding connecting rod 203, the plug-in fixing rod 207 is plugged in the inner side of the plug-in fixing bolt 208 to fix the vertical tail 204.
When the vertical tail folding mechanism for the aircraft is used, the horizontal tail wing 102 is utilized to enable the aircraft tail end 101 to fly horizontally, the horizontal air flow plate 103 can turn over through the horizontal connecting rod 104, the up-down flying height of the aircraft tail end 101 can be changed, the vertical tail wing 204 keeps the straight line of the aircraft tail end 101 to fly, the vertical connecting rod 205 drives the vertical air flow plate 206 to turn over, the vertical air flow plate 206 turns over to change the flying direction of the aircraft tail end 101, and when the vertical tail wing 204 turns downwards through the folding connecting rod 203, the plug-in fixing rod 207 is plugged into the inner side of the plug-in fixing bolt 208 for fixing the vertical tail wing 204.
Although embodiments of the present utility model have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein without departing from the principles and spirit of the utility model, the scope of which is defined in the appended claims and their equivalents.
Claims (7)
1. A vertical fin folding mechanism for aircraft, includes fixed knot structure (1) and beta structure (2), its characterized in that: the folding structure (2) is fixedly connected to the outer side surface of the top of the fixing structure (1);
The fixed structure (1) comprises a tail unit and an air flow plate unit, the air flow plate unit is movably connected to the outer side surface of the tail unit, the folding structure (2) comprises a folding unit, a vertical tail unit and a plug-in unit, the folding unit is fixedly connected to the top surface of the tail unit, the vertical tail unit is movably connected to the outer side surface of the folding unit, and the plug-in unit is fixedly connected to the outer side surface of the vertical tail unit.
2. A vertical fin folding mechanism for an aircraft according to claim 1, wherein: the tail unit comprises an aircraft tail end (101) and a horizontal tail (102), wherein the aircraft tail end (101) is arranged on the inner side of the folding structure (2), and the horizontal tail (102) is fixedly connected to the outer side surface of the aircraft tail end (101).
3. A vertical fin folding mechanism for an aircraft according to claim 1, wherein: the air flow plate unit comprises a horizontal air flow plate (103) and a horizontal connecting rod (104), wherein the horizontal air flow plate (103) is movably connected to the outer side surface of the horizontal connecting rod (104), and the horizontal connecting rod (104) is movably connected to the rear side surface of the horizontal tail wing (102).
4. A vertical fin folding mechanism for an aircraft according to claim 1, wherein: the folding unit comprises a bottom connecting plate (201), a rotating shaft supporting plate (202) and a folding connecting rod (203), wherein the bottom connecting plate (201) is fixedly connected to the top surface of the horizontal tail wing (102), the rotating shaft supporting plate (202) is fixedly connected to the top surface of the bottom connecting plate (201), and the folding connecting rod (203) is movably connected to the inner side panel of the rotating shaft supporting plate (202).
5. A vertical fin folding mechanism for an aircraft according to claim 1, wherein: the vertical tail unit comprises a vertical tail (204), a vertical connecting rod (205) and a vertical airflow plate (206), wherein the vertical tail (204) is movably connected to the outer side surface of the folding connecting rod (203), the vertical connecting rod (205) is movably connected to the outer side surface of the vertical tail (204), and the vertical airflow plate (206) is movably connected to the outer side surface of the vertical connecting rod (205).
6. A vertical fin folding mechanism for an aircraft according to claim 1, wherein: the plug-in unit comprises a plug-in fixing rod (207) and a plug-in fixing bolt (208), wherein the plug-in fixing rod (207) is fixedly connected to the outer side surface of the vertical tail wing (204), and the plug-in fixing bolt (208) is fixedly connected to the top surface of the horizontal tail wing (102).
7. A vertical fin folding mechanism for an aircraft according to claim 2, wherein: the number of the horizontal tails (102) is two, the two horizontal tails (102) are arranged at the left side and the right side of the tail end (101) of the airplane in a mirror image mode, the number of the folding structures (2) is identical to that of the horizontal tails (102), and the folding structures are arranged at the top of the horizontal tails (102).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202323132201.0U CN221114350U (en) | 2023-11-21 | 2023-11-21 | Vertical tail folding mechanism for airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202323132201.0U CN221114350U (en) | 2023-11-21 | 2023-11-21 | Vertical tail folding mechanism for airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN221114350U true CN221114350U (en) | 2024-06-11 |
Family
ID=91345481
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202323132201.0U Active CN221114350U (en) | 2023-11-21 | 2023-11-21 | Vertical tail folding mechanism for airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN221114350U (en) |
-
2023
- 2023-11-21 CN CN202323132201.0U patent/CN221114350U/en active Active
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