CN212074400U - Tilting rotor aircraft horizontal tail and horizontal tail tilting mechanism - Google Patents
Tilting rotor aircraft horizontal tail and horizontal tail tilting mechanism Download PDFInfo
- Publication number
- CN212074400U CN212074400U CN202020560978.4U CN202020560978U CN212074400U CN 212074400 U CN212074400 U CN 212074400U CN 202020560978 U CN202020560978 U CN 202020560978U CN 212074400 U CN212074400 U CN 212074400U
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- horizontal tail
- tilting
- steering wheel
- rocker arm
- rocking arm
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Abstract
The utility model discloses a rotor aircraft horizontal tail and horizontal tail mechanism of verting relates to the aircraft, specifically including the steering wheel that verts, the positive output shaft of the steering wheel that verts is fixed to be cup jointed the steering wheel rocking arm, and the steering wheel rocking arm is kept away from the one end of verting the steering wheel output shaft and is rotated and be connected with the connecting rod, and the one end that the steering wheel rocking arm was kept away from to the connecting rod is rotated and is connected with the rocking arm that verts, and the right side of the rocking arm that verts is provided with the horizontal tail girder, and the surface of horizontal tail girder is provided with horizontal tail wing rib, and the quantity of horizontal tail wing rib is a plurality of, fixedly connected with elevator steering wheel between two shortest horizontal tail wing ribs of interval, and. Through setting up steering wheel rocking arm, connecting rod, the rocking arm that verts and elevator, reached simple structure, reliable, the convenient effect of dismouting vert, solved because of verting the wing angle of verting not enough, lead to speed slow, inefficiency, and the problem of the complicated difficult dismouting of fixed wing aircraft and gyroplane aircraft inner connecting piece structure.
Description
Technical Field
The utility model relates to an aircraft specifically is a mechanism verts of rotor craft horizontal tail and horizontal tail that verts.
Background
With the development of aviation technology, unmanned vehicles are widely applied to military and civil fields, and among various types of vehicles, rotorcraft can be rapidly developed due to excellent takeoff and landing performance and hovering performance, and especially, a tilt rotorcraft combines the advantages of a fixed-wing vehicle and a rotorcraft, so that the unmanned aircraft has a good application prospect.
Some aircrafts on the market are mostly fixed-wing aircrafts and rotorcraft aircrafts, and the fixed-wing aircrafts and the rotorcraft aircrafts are not enough in front due to the tilting angle of the tilting wings, so that the speed is low, the efficiency is low, and the structures of some fixed-wing aircrafts and rotorcraft internal connecting pieces are complex and difficult to disassemble and assemble at present, thereby influencing the further development of the fixed-wing aircrafts and the rotorcraft.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a rotor craft that verts horizontal tail and horizontal tail mechanism of verting to solve the problem that proposes among the above-mentioned background art.
In order to achieve the above object, the utility model provides a following technical scheme:
the utility model provides a mechanism that verts is changeed to rotor craft horizontal tail and horizontal tail, including the steering wheel that verts, the fixed cover that has connect the steering wheel rocking arm on the positive output shaft of the steering wheel that verts, the steering wheel rocking arm is kept away from the one end rotation of the steering wheel output shaft that verts and is connected with the connecting rod, the one end rotation that the steering wheel rocking arm was kept away from to the connecting rod is connected with the rocking arm that verts, the right side of the rocking arm that verts is provided with the horizontal tail girder, the surface of horizontal tail girder is provided with horizontal tail wing rib, the quantity of horizontal tail wing rib is a plurality of, fixedly connected with elevator steering wheel between two shortest horizontal tail wing ribs of interval, one side of the horizontal tail girder of horizontal tail wing rib is provided with the elevator, the output shaft fixed connection of elevator steering wheel is in elevator.
As a further aspect of the present invention: the quantity of elevator steering wheel is two, and two elevator steering wheels use the axis of verting the rocking arm as the axisymmetrical distribution of axle.
As a further aspect of the present invention: the steering engine rocker arm, the connecting rod, the tilting rocker arm and the tilting hinge form a parallelogram.
As a further aspect of the present invention: the quantity of elevator is two, and two elevators rotate with one side of flat tail girder far away from the rocking arm that verts through the hinge and be connected.
Compared with the prior art, the beneficial effects of the utility model are that: through setting up the steering wheel rocking arm, the connecting rod, rocking arm and the elevator vert, rocking arm steering wheel rocking arm is 90 degrees anticlockwise rotatory under the drive of steering wheel, can realize that the aircraft changes the vertical flight mode from the flat mode that flies forward, deflect from top to bottom through two elevator steering wheels control elevators respectively, realize the pitch control of aircraft, the rotor structure that verts has combined the advantage of fixed wing aircraft and rotor craft, simple structure has been reached, it is reliable to vert, the convenient effect of dismouting, it is not enough to have solved because of the wing angle of verting, lead to speed slow, low efficiency, and the complicated difficult problem of dismouting of fixed wing aircraft and rotor aircraft inner connecting piece structure.
Drawings
Fig. 1 is an axonometric view of a horizontal tail and a horizontal tail tilting mechanism of a tilt rotor aircraft in a flat flight state.
Fig. 2 is an axonometric view of a horizontal tail and a horizontal tail tilting mechanism of a tilt rotor aircraft in a vertical state.
As shown in the figure: 1. the device comprises a tilting steering engine, 2 steering engine rocker arms, 3 connecting rods, 4 horizontal tail main beams, 5 elevators, 6 tilting rocker arms, 7 tilting hinges, 8 elevator steering engines and 9 horizontal tail wing ribs.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
In the description of the present invention, it should be noted that the terms "upper", "lower", "inner", "outer", "top/bottom", 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 referred to 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", "provided", "sleeved/connected", "connected", and the like are to be understood in a broad sense, such as "connected", which may be fixedly connected, 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.
Referring to fig. 1-2, in the embodiment of the present invention, a tilt mechanism for a horizontal tail and a horizontal tail of a tilt rotor aircraft comprises a tilt steering engine 1, wherein a steering engine rocker arm 2 is fixedly sleeved on an output shaft on the front side of the tilt steering engine 1, the shape formed by the steering engine rocker arm 2, a connecting rod 3, a tilt rocker arm 6 and a tilt hinge 7 is a parallelogram, the tilt rocker arm 6 can be effectively driven to rotate through the arrangement of the parallelogram, the purpose that the rotation angles of the steering engine rocker arm 2 and the tilt rocker arm 6 are the same is achieved, and the tilt steering engine 2 and the tilt hinge are more stable and firm, one end of the steering engine rocker arm 2, which is far away from the output shaft of the tilt steering engine 1, is rotatably connected with the connecting rod 3, one end of the connecting rod 3, which is far away from the steering engine rocker arm 2, is rotatably connected with the tilt rocker arm 6, a horizontal tail girder 4 is, the quantity of horizontal tail wing rib 9 is a plurality of, fixedly connected with elevator steering wheel 8 between two the shortest horizontal tail wing rib 9 of interval, elevator steering wheel 8's quantity is two, two elevator steering wheel 8 use the axis of verting rocking arm 6 to be the axisymmetric distribution as the axle, the symmetric distribution makes the weight on verting wing both sides equal, difficult emergence slope when flying, the atress is balanced, one side of horizontal tail girder 4 of horizontal tail wing rib 9 is provided with elevator 5, elevator 5's quantity is two, two elevator 5 are rotated with one side that horizontal tail girder 4 kept away from verting rocking arm 6 through the hinge and are connected, two elevator 5 conveniently control the wing that verts, elevator steering wheel 8's output shaft fixed connection is in elevator 5 one side, the surface of horizontal tail girder 4 is close to the position department fixedly connected with of verting rocking arm 6 and verts hinge 7.
When the tilting steering engine is used, the tilting steering engine 1 and the tilting hinge 7 are fixedly installed on the aircraft body, the other half of the tilting hinge 7 is fixed on a wing beam of the aircraft, the connecting rod 3 is connected with the steering engine rocker arm 2 and the tilting rocker arm 6, so that a parallelogram structure is formed among the steering engine rocker arm 2, the connecting rod 3, the tilting rocker arm 6 and the tilting hinge 7, the tilting steering engine 1 drives the steering engine rocker arm 2 to rotate 90 degrees anticlockwise, the steering engine rocker arm 2 rotates 90 degrees anticlockwise, the connecting rod 3 rotates 90 degrees anticlockwise, the horizontal tail tilts from a horizontal state to a vertical state, namely, the aircraft rotates from a forward horizontal flight mode to a vertical flight mode, and then the two lifting rudder steering engines 8 respectively control the vertical deflection of the lifting rudder 5, so that the pitching control of the aircraft is realized, the design structure is simple and easy to operate, and the tilting hinge 7 is fixedly connected, the disassembly and the assembly are more convenient.
Although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments or portions thereof without departing from the spirit and scope of the invention, and the following claims are therefore to be read in this light of the appended claims.
Claims (4)
1. A tilt-rotor aircraft horizontal tail and horizontal tail tilting mechanism comprises a tilting steering engine (1) and is characterized in that a steering engine rocker arm (2) is fixedly sleeved on an output shaft on the front side of the tilting steering engine (1), one end, far away from the output shaft of the tilting steering engine (1), of the steering engine rocker arm (2) is rotatably connected with a connecting rod (3), one end, far away from the steering engine rocker arm (2), of the connecting rod (3) is rotatably connected with a tilting rocker arm (6), a horizontal tail main beam (4) is arranged on the right side of the tilting rocker arm (6), horizontal tail wing ribs (9) are arranged on the surface of the horizontal tail main beam (4), the number of the horizontal tail wing ribs (9) is multiple, a lifting rudder steering engine (8) is fixedly connected between two horizontal tail wing ribs (9) with the shortest interval, a lifting rudder (5) is arranged on one side of the horizontal tail main beam (4) of each horizontal tail wing rib (9), the output shaft of the lifting steering engine, the surface of the horizontal tail main beam (4) is fixedly connected with a tilting hinge (7) at a position close to the tilting rocker arm (6).
2. The horizontal tail and horizontal tail tilting mechanism of the tilt rotor aircraft according to claim 1, wherein the number of the elevator steering engines (8) is two, and the two elevator steering engines (8) are distributed in axial symmetry by taking the axis of the tilting rocker arm (6) as an axis.
3. The tilt rotor aircraft horizontal tail and horizontal tail tilt mechanism according to claim 1, wherein the shape formed by the steering engine rocker arm (2), the connecting rod (3), the tilt rocker arm (6) and the tilt hinge (7) is a parallelogram.
4. The tilt rotor aircraft horizontal tail and horizontal tail tilting mechanism according to claim 1, characterized in that the number of the elevators (5) is two, and the two elevators (5) are rotatably connected with one side of the horizontal tail main beam (4) away from the tilting rocker arm (6) through a hinge.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020560978.4U CN212074400U (en) | 2020-04-15 | 2020-04-15 | Tilting rotor aircraft horizontal tail and horizontal tail tilting mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020560978.4U CN212074400U (en) | 2020-04-15 | 2020-04-15 | Tilting rotor aircraft horizontal tail and horizontal tail tilting mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212074400U true CN212074400U (en) | 2020-12-04 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020560978.4U Expired - Fee Related CN212074400U (en) | 2020-04-15 | 2020-04-15 | Tilting rotor aircraft horizontal tail and horizontal tail tilting mechanism |
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| Country | Link |
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| CN (1) | CN212074400U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115123535A (en) * | 2022-08-11 | 2022-09-30 | 北京北航天宇长鹰无人机科技有限公司 | Tilt wing unmanned aerial vehicle |
-
2020
- 2020-04-15 CN CN202020560978.4U patent/CN212074400U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115123535A (en) * | 2022-08-11 | 2022-09-30 | 北京北航天宇长鹰无人机科技有限公司 | Tilt wing unmanned aerial vehicle |
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| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20201204 |