CN111232185A - Wing surface folding and unfolding mechanism - Google Patents
Wing surface folding and unfolding mechanism Download PDFInfo
- Publication number
- CN111232185A CN111232185A CN201811429777.4A CN201811429777A CN111232185A CN 111232185 A CN111232185 A CN 111232185A CN 201811429777 A CN201811429777 A CN 201811429777A CN 111232185 A CN111232185 A CN 111232185A
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- Prior art keywords
- folding
- airfoil
- transmission
- pull rod
- wing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/44—Varying camber
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transmission Devices (AREA)
Abstract
The invention relates to the technical field of aerospace and discloses a wing surface folding and unfolding mechanism. The mechanism comprises a wing root rotating shaft, an actuator with a telescopic pull rod, a transmission joint and an in-place lock, wherein a folding wing surface is connected with the wing root through the wing root rotating shaft, the actuator is connected with the transmission pull rod through an opening formed in the wing root, the transmission pull rod is connected with the transmission joint, the transmission joint is arranged on the folding wing surface, the pull rod of the actuator drives the transmission pull rod to move through linear motion, the transmission pull rod drives the transmission joint to move while rotating around the wing root rotating shaft, the folding wing surface is driven to move around the rotating shaft, the folding wing surface is locked through the in-place lock after rotating in place, all wing surface unfolding actions are completed, and the transmission pull rod and the transmission joint are completely retracted into the wing root through the opening. The speed and the acceleration of the wing surface unfolding are flexibly controlled by transmitting the pulling force and the pushing force along the transmission rod and a certain moment, so that the wing surface is in place, has no impact and is stably unfolded.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to an airfoil folding and unfolding mechanism.
Background
The wing surface is an important component of the aircraft, the requirement of wing surface folding widely exists in various aircraft, the space occupied by the aircraft before takeoff \ launching can be effectively reduced through the wing surface folding, and the unfolding is completed through the folding and unfolding mechanism after the takeoff \ launching.
The existing wing surface folding and unfolding mechanism has the following defects: firstly, a spring is used as unfolding driving force, and a mechanism can only transmit small driving force and moment and cannot complete folding and unfolding actions under large wing surface load; secondly, the mechanism can not transmit the unfolding resistance, namely, the deceleration of the unfolding process can not be realized, and the wing surface is unfolded to be a pure acceleration motion process, so that the wing surface is unfolded in place and has large impact, and the flying stability and safety of the aircraft are influenced.
Disclosure of Invention
The invention aims to overcome the defects in the prior art and provides an airfoil folding and unfolding mechanism which can solve the problems in the prior art.
The technical solution of the invention is as follows: a wing surface folding and unfolding mechanism comprises a wing root rotating shaft, an actuator with a telescopic pull rod, a transmission joint and an in-place lock, wherein a folding wing surface is connected with a wing root through the wing root rotating shaft, the actuator is connected with the transmission pull rod through an opening arranged on the wing root, the transmission pull rod is connected with the transmission joint, the transmission joint is arranged on the folding airfoil surface, the pull rod of the actuator drives the transmission pull rod to move through linear motion, the transmission pull rod drives the transmission joint to move while rotating around the wing root rotating shaft, further driving the folding wing surface to move around the rotating shaft, and locking the folding wing surface through the in-place lock after the folding wing surface rotates in place to complete the unfolding action of all the wing surfaces, and the transmission pull rod and the transmission joint are completely retracted into the wing root through the opening after the folding wing surface rotates to the position.
Preferably, the mechanism further comprises an impact mass having a buffer layer disposed on the folded airfoil, the folded airfoil being in contact with the root through the impact mass.
Preferably, the material of the buffer layer is rubber.
Preferably, the mechanism further comprises a mounting seat through which the actuator is arranged on the wing root.
Preferably, the wing root rotating shaft comprises multiple fork ears hinged with each other.
Preferably, the multi-prong ears are hinged by bolts, and the bolt heads are provided with groove-shaped nuts and split pins.
Preferably, the transmission pull rod is hinged to both the actuator and the transmission joint.
Preferably, the lock that targets in place includes lock body, torsional spring, locking plate and spring bolt, lock body, torsional spring with the locking plate is installed on the wing root, and the spring bolt is installed on folding airfoil.
Preferably, the actuator is an electric motor actuator or a hydraulic actuator.
Through above-mentioned technical scheme, can set up wing root pivot, have actuator, transmission pull rod, the transmission of scalable pull rod and connect and lock that targets in place, the pull rod of actuator can drive through linear motion the transmission pull rod produces the motion, the transmission pull rod is winding wing root pivot pivoted simultaneously can drive the motion is connected in the transmission, and then can drive folding airfoil revolutes the rotation of axes and moves, just folding airfoil rotates the back of targetting in place and locks through the lock that targets in place. Therefore, the speed and the acceleration of the wing surface unfolding can be flexibly controlled by transmitting the pulling force and the pushing force along the transmission rod and a certain moment, so that the wing surface is in place, has no impact and is stably unfolded. And, reliable locking can be achieved by in-place lock locking.
Drawings
The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
FIG. 1 is a schematic structural diagram of an airfoil folding and unfolding mechanism according to an embodiment of the present invention;
FIG. 2 is a schematic illustration of an airfoil deployment according to an embodiment of the present invention;
FIG. 3 is a schematic illustration of a fully deployed airfoil according to an embodiment of the present invention;
fig. 4 is an exploded view of the lock according to the embodiment of the present invention.
Description of the reference numerals
1, a wing root rotating shaft; 2, an actuator; 3, driving a pull rod; 4, a transmission joint; 5, a collision block;
6 locking in place; 7 a lock body; 8 a torsion spring; 9 locking plate; 10 a bolt; 11 folding the airfoil; 12 wing roots.
Detailed Description
Specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings. In the following description, for purposes of explanation and not limitation, specific details are set forth in order to provide a thorough understanding of the present invention. However, it will be apparent to one skilled in the art that the present invention may be practiced in other embodiments that depart from these specific details.
It should be noted that, in order to avoid obscuring the present invention with unnecessary details, only the device structures and/or processing steps that are closely related to the scheme according to the present invention are shown in the drawings, and other details that are not so relevant to the present invention are omitted.
FIG. 1 is a schematic structural diagram of an airfoil folding and unfolding mechanism according to an embodiment of the present invention. FIG. 1 corresponds to an airfoil folded condition.
FIG. 2 is a schematic illustration of an airfoil deployment according to an embodiment of the present invention.
FIG. 3 is a schematic illustration of a fully deployed airfoil according to an embodiment of the present invention.
The wing surface folding and unfolding mechanism can be used for various aircrafts including unmanned planes and light aircrafts
As shown in fig. 1-3, an embodiment of the present invention provides an airfoil folding and unfolding mechanism, where the mechanism includes a wing root rotating shaft 1, an actuator 2 having a retractable pull rod, a transmission pull rod 3, a transmission joint 4 and a position lock 6, a folding airfoil (i.e., an airfoil to be unfolded) 11 and a wing root 12 are connected through the wing root rotating shaft 1 (i.e., in an initial airfoil folding state), the actuator 2 is connected with the transmission pull rod 3 through an opening provided on the wing root 12, the transmission pull rod 3 is connected with the transmission joint 4, the transmission joint 4 is provided on the folding airfoil 11, the pull rod of the actuator 2 drives the transmission pull rod 3 to move through a linear motion (i.e., outputting a driving force), the transmission pull rod 3 drives the transmission joint 4 to move while rotating around the wing root rotating shaft 1, and further drives the folding airfoil 11 connected with the transmission joint 4 to move around a rotating shaft (wing root rotating shaft) And the folding airfoil 11 is locked by the in-place lock 6 after rotating in place to complete the unfolding action of all airfoils, and the transmission pull rod 3 and the transmission joint 4 are completely retracted into the airfoil root 12 through the opening after the folding airfoil 11 rotates in place.
In the rotating process, the driving force of the actuator can be reversed according to the acceleration and deceleration requirements of the airfoil, and the size and the direction of the bearing force on the transmission pull rod are also changed continuously. The driving force is transmitted through the rigid connecting rod, so that the pulling force and the pushing force along the rod direction can be transmitted, a certain moment can be transmitted, and the speed and the acceleration of the unfolding of the airfoil surface can be flexibly controlled. Also, as shown in FIG. 3, in the fully deployed state of the airfoil, the mechanism can be fully stowed inside the root through the root opening (e.g., a circular opening) without affecting the aerodynamic profile.
Through above-mentioned technical scheme, can set up wing root pivot, have actuator, transmission pull rod, the transmission of scalable pull rod and connect and lock that targets in place, the pull rod of actuator can drive through linear motion the transmission pull rod produces the motion, the transmission pull rod is winding wing root pivot pivoted simultaneously can drive the motion is connected in the transmission, and then can drive folding airfoil revolutes the rotation of axes and moves, just folding airfoil rotates the back of targetting in place and locks through the lock that targets in place. Therefore, the speed and the acceleration of the wing surface unfolding can be flexibly controlled by transmitting the pulling force and the pushing force along the transmission rod and a certain moment, so that the wing surface is in place, has no impact and is stably unfolded. And, reliable locking can be achieved by in-place lock locking.
According to an embodiment of the invention, the mechanism further comprises a striker 5 with a damping layer, arranged on said folded airfoil 11, said folded airfoil 11 being in contact with said root 12 through said striker 5.
Therefore, the end rib of the airfoil can be in collision contact with the airfoil root through the collision block 5, and the buffer layer on the collision block can play a role in buffering and protecting the airfoil structure.
According to an embodiment of the invention, the material of the cushioning layer may be rubber.
Alternatively, the impact mass 5 as a whole may be directly made of a rubber material.
According to an embodiment of the present invention, the wing root rotating shaft 1, the transmission pull rod 3 and the transmission joint 4 are all metal members.
According to an embodiment of the invention, the mechanism further comprises a mounting seat by means of which the actuator 2 is arranged on the wing root 12.
According to an embodiment of the present invention, the wing root rotating shaft 1 may include multi-pronged ears hinged to each other.
According to one embodiment of the invention, the multiple prongs may be hinged by means of a bolt, the bolt head being provided with a slotted nut and a cotter pin.
For example, the wing root rotating shaft 1 may be a hinge integrally formed with a wing root 11 end rib, the hinge is connected inside by a bolt, the shaft hole tolerance fit may be a small clearance fit, and the bolt end may be fixed by a groove nut and loose-proof by a split pin. Two wing root shafts 1 may be arranged at the connection of the wing root 12 and the airfoil to be deployed, as shown in fig. 1.
According to an embodiment of the invention, the drive rod 3 and the actuator 2 and the drive joint 4 may be articulated.
For example, the transmission pull rod, the actuator pull rod and the transmission joint are hinged, the joint can be matched with two lugs through a single lug, the inside of the joint is connected through a bolt, the tolerance fit of the shaft hole is small-clearance fit, and the end of the bolt is fixed through a groove-shaped nut and is loose-proof through a split pin.
The small gap may be, for example, 0.02mm to 0.072 mm.
More specifically, the actuator is hinged to two lugs of the transmission pull rod through a bolt from a single lug at the tail end of the pull rod, and two lugs on the other side of the transmission pull rod are hinged to a single lug of the transmission joint through a bolt.
The hinge joint of the transmission pull rod and the connection of the wing root rotating shaft are realized through shaft hole tolerance fit, and the selected tolerance zone can ensure that the connection is reliable and free from shaking and can realize smooth rotation and free from jamming.
According to an embodiment of the invention, the transmission joint 4 and the folded airfoil 11 (folded airfoil end rib) may be fixedly connected by means of bolts.
Fig. 4 is an exploded view of the lock according to the embodiment of the present invention.
As shown in fig. 4, the in-place lock 6 may include a lock body 7, a torsion spring 8, a locking plate 9 and a locking bolt 10, wherein the lock body 7, the torsion spring 8 and the locking plate 9 are installed on the wing root 12, and the locking bolt 10 is installed on the folding wing surface 11.
That is, the latch 10 may be installed at a position corresponding to the locking plate 9 on the folding wing 11.
For example, the lock 6 can be a torsion spring mechanism, after the spring tongue 10 impacts the torsion spring 8 and the lock plate 9, the torsion spring 8 drives the lock plate 9 to reset under the action of elastic force to complete locking (when the spring tongue is in place, the lock plate is lifted by impacting the lock plate, and then the lock plate resets under the action of the elastic force of the torsion spring to hook the lock tongue, so that locking is completed).
According to an embodiment of the invention, the actuator 2 is an electric motor actuator or a hydraulic actuator.
As can be seen from the above embodiments, the airfoil folding and unfolding mechanism of the present invention has the following advantages:
1) the folding and unfolding of the airfoil under the condition of large load can be completed.
2) The mechanism can transmit the pulling force and the pushing force along the transmission rod and a certain moment, so that the speed and the acceleration of the wing surface unfolding can be flexibly controlled, and the wing surface can be unfolded stably in place without impact.
3) Under the condition that the wing surface is completely unfolded, the mechanism is completely retracted into the wing root structure, and the aerodynamic appearance is not influenced
4) The structure is succinct, and the locking is firm, and whole has very high reliability.
5) The application range is wide, and the device can be used for various aircrafts including unmanned planes and light aircrafts.
The folding wing surface under the large load can be unfolded quickly and stably and locked reliably, the size of the folded state is effectively reduced, the structure is simple, the locking is firm, and the whole folding wing surface has very high reliability.
Features that are described and/or illustrated above with respect to one embodiment may be used in the same way or in a similar way in one or more other embodiments and/or in combination with or instead of the features of the other embodiments.
It should be emphasized that the term "comprises/comprising" when used herein, is taken to specify the presence of stated features, integers, steps or components but does not preclude the presence or addition of one or more other features, integers, steps, components or groups thereof.
The many features and advantages of these embodiments are apparent from the detailed specification, and thus, it is intended by the appended claims to cover all such features and advantages of these embodiments which fall within the true spirit and scope thereof. Further, since numerous modifications and changes will readily occur to those skilled in the art, it is not desired to limit the embodiments of the invention to the exact construction and operation illustrated and described, and accordingly, all suitable modifications and equivalents may be resorted to, falling within the scope thereof.
The invention has not been described in detail and is in part known to those of skill in the art.
Claims (9)
1. The utility model provides a folding deployment mechanism of airfoil, its characterized in that, this mechanism includes wing root pivot (1), actuator (2) that have scalable pull rod, transmission pull rod (3), transmission joint (4) and lock (6) that targets in place, and folding airfoil (11) pass through with wing root (12) wing root pivot (1) is connected, actuator (2) pass through the opening that sets up on wing root (12) with transmission pull rod (3) are connected, transmission pull rod (3) with transmission joint (4) are connected, transmission joint (4) set up on folding airfoil (11), the pull rod of actuator (2) drives through linear motion transmission pull rod (3) produce the motion, transmission pull rod (3) drive around wing root pivot (1) pivoted simultaneously transmission joint (4) move, and then drive folding airfoil (11) revolute the axle motion, and the folding wing surfaces (11) are locked by in-place locks (6) after rotating in place to complete the unfolding action of all the wing surfaces, and the transmission pull rod (3) and the transmission joint (4) are completely retracted into the wing roots (12) through the opening after the folding wing surfaces (11) rotate in place.
2. An airfoil folding and unfolding mechanism according to claim 1, further comprising a bump (5) with a buffer layer arranged on said folded airfoil (11), said folded airfoil (11) being in contact with said root (12) through said bump (5).
3. The airfoil folding and unfolding mechanism of claim 2, wherein said snubber material is rubber.
4. An airfoil folding and unfolding mechanism according to any of claims 1-3, characterised in that the mechanism further comprises a mounting seat by means of which the actuator (2) is arranged on the root (12).
5. An airfoil folding and unfolding mechanism according to any of claims 1-3, characterized in that said airfoil root spindle (1) comprises mutually articulated multi-pronged ears.
6. The airfoil folding and unfolding mechanism according to claim 5, wherein said multi-pronged ears are hinged by bolts, the bolt ends being provided with slotted nuts and cotter pins.
7. An airfoil folding and unfolding mechanism according to any of claims 1-3, characterized in that said transmission tie rod (3) is hinged to both said actuator (2) and said transmission joint (4).
8. An airfoil folding and unfolding mechanism according to any of claims 1-3, characterized in that said in-place lock (6) comprises a lock body (7), a torsion spring (8), a locking plate (9) and a locking tongue (10), said lock body (7), torsion spring (8) and locking plate (9) being mounted on said wing root (12), and said locking tongue (10) being mounted on said folding airfoil (11).
9. An airfoil folding and unfolding mechanism according to any of claims 1-3, characterized in that said actuator (2) is an electric motor actuator or a hydraulic actuator.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811429777.4A CN111232185A (en) | 2018-11-28 | 2018-11-28 | Wing surface folding and unfolding mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811429777.4A CN111232185A (en) | 2018-11-28 | 2018-11-28 | Wing surface folding and unfolding mechanism |
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| Publication Number | Publication Date |
|---|---|
| CN111232185A true CN111232185A (en) | 2020-06-05 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811429777.4A Pending CN111232185A (en) | 2018-11-28 | 2018-11-28 | Wing surface folding and unfolding mechanism |
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| CN (1) | CN111232185A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112407241A (en) * | 2020-12-06 | 2021-02-26 | 西安长峰机电研究所 | Rotary folding mechanism |
| CN112550667A (en) * | 2020-12-29 | 2021-03-26 | 河北福莱卡航空科技有限公司 | High-reliability self-compensation dead-locking wing folding system |
| CN112918659A (en) * | 2021-03-12 | 2021-06-08 | 中航西飞民用飞机有限责任公司 | Folding structure and folding method of airplane wing |
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| CN106945820A (en) * | 2015-11-18 | 2017-07-14 | 空中客车英国运营有限责任公司 | Actuating assembly and application method and wing, Wing tip device and aircraft including it |
| CN107933881A (en) * | 2017-11-15 | 2018-04-20 | 安徽工程大学 | A kind of outer wing folding and unfolding mechanism of aircraft |
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2018
- 2018-11-28 CN CN201811429777.4A patent/CN111232185A/en active Pending
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| CN101712379A (en) * | 2009-07-14 | 2010-05-26 | 北京航空航天大学 | Folding small-sized unmanned aerial vehicle |
| CN103963958A (en) * | 2014-04-21 | 2014-08-06 | 西工大常熟研究院有限公司 | Wing folding mechanism for unmanned plane |
| CN105882938A (en) * | 2015-02-17 | 2016-08-24 | 空中客车营运有限公司 | An arrangement for effecting movement of a wing tip device between a flight configuration and a ground configuration |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112407241A (en) * | 2020-12-06 | 2021-02-26 | 西安长峰机电研究所 | Rotary folding mechanism |
| CN112407241B (en) * | 2020-12-06 | 2024-06-04 | 西安长峰机电研究所 | Rotary folding mechanism |
| CN112550667A (en) * | 2020-12-29 | 2021-03-26 | 河北福莱卡航空科技有限公司 | High-reliability self-compensation dead-locking wing folding system |
| CN112550667B (en) * | 2020-12-29 | 2022-08-12 | 河北福莱卡航空科技有限公司 | High-reliability self-compensation locked wing folding system |
| CN112918659A (en) * | 2021-03-12 | 2021-06-08 | 中航西飞民用飞机有限责任公司 | Folding structure and folding method of airplane wing |
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