CN117622478A - Four-bar unlocking mechanism of aircraft landing gear - Google Patents
Four-bar unlocking mechanism of aircraft landing gear Download PDFInfo
- Publication number
- CN117622478A CN117622478A CN202311690227.9A CN202311690227A CN117622478A CN 117622478 A CN117622478 A CN 117622478A CN 202311690227 A CN202311690227 A CN 202311690227A CN 117622478 A CN117622478 A CN 117622478A
- Authority
- CN
- China
- Prior art keywords
- strut
- landing gear
- hinged
- bar
- locking
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000000034 method Methods 0.000 description 3
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Transmission Devices (AREA)
Abstract
The application belongs to the field of aircraft structural design, and particularly relates to an aircraft landing gear four-bar unlocking mechanism, which comprises an upper supporting bar, a lower supporting bar, a landing gear strut assembly, a retractable actuating cylinder, a supporting bar locking mechanism and a driving mechanism; the lower end of the landing gear strut assembly is hinged to the lower end of the lower stay bar, the upper end of the lower stay bar is hinged to the upper stay bar, and the upper stay bar is hinged to the frame; the driving mechanism comprises an actuating cylinder, an unlocking rocker arm and a four-bar mechanism; one end of the actuating cylinder is hinged to the upper supporting rod, the other end of the actuating cylinder is hinged to the unlocking rocker arm, the unlocking rocker arm is fixedly connected to a rotating shaft hinged to the upper supporting rod, and the four-bar mechanism is fixedly connected with the rotating shaft to transmit torque to the supporting rod locking mechanism; the stay bar lock mechanism is connected between the lower stay bar and the landing gear pillar assembly, and the stay bar lock mechanism is driven to unlock and lock through the driving mechanism.
Description
Technical Field
The application belongs to the field of aircraft structural design, and particularly relates to an aircraft landing gear four-bar linkage unlocking mechanism.
Background
At present, an unlocking (locking) mechanism of an aircraft landing gear at home and abroad mostly adopts a mode that an unlocking actuator cylinder is directly unlocked (locked), but unlocking (locking) by utilizing the unlocking actuator cylinder relates to point location arrangement and travel arrangement of the unlocking actuator cylinder, and if space is tense, the point location and travel of the unlocking actuator cylinder are limited, so that the arrangement of the whole landing gear scheme is affected.
Disclosure of Invention
In order to solve the above-mentioned problem, the present application provides an aircraft landing gear four-bar linkage unlocking mechanism, includes:
the landing gear comprises an upper stay bar, a lower stay bar, a landing gear strut assembly, a retraction actuator cylinder, a stay bar lock mechanism and a driving mechanism;
the upper end of the outer cylinder of the landing gear strut assembly is hinged with the outer cylinder to be hinged with a retractable actuating cylinder on the machine body, the lower end of the outer cylinder is hinged with the lower end of a lower stay bar, the upper end of the lower stay bar is hinged with an upper stay bar, and the upper stay bar is hinged on the machine frame;
the driving mechanism comprises an actuating cylinder, an unlocking rocker arm and a four-bar mechanism; one end of the actuating cylinder is hinged to the upper supporting rod, the other end of the actuating cylinder is hinged to the unlocking rocker arm, the unlocking rocker arm is fixedly connected to a rotating shaft hinged to the upper supporting rod, and the four-bar mechanism is fixedly connected with the rotating shaft to transmit torque to the supporting rod locking mechanism;
the supporting rod locking mechanism is connected between the lower supporting rod and the supporting rod assembly of the landing gear, the supporting rod locking mechanism is driven by the driving mechanism to unlock and lock, when the landing gear is locked, the supporting rod assembly of the landing gear and the lower supporting rod form a preset opening angle, and when the landing gear is unlocked, the supporting rod assembly of the landing gear is folded with the lower supporting rod.
Preferably, the strut lock mechanism comprises a lower lock strut, an upper lock strut and a lock spring, wherein one end of the lower lock strut is hinged with one end of the upper lock strut, the other end of the upper lock strut is hinged with the landing gear strut assembly, one end of the lock spring is hinged in the middle of the strut lock mechanism, the other end of the lock spring is hinged on the lower strut, a limiting device is arranged at the hinged position of the lower lock strut and the upper lock strut, and when the lower lock strut and the upper lock strut are unfolded, the limiting device limits the relative rotation of the lower lock strut and the upper lock strut to form deflection, and the deflection is kept and the lower strut and the landing gear strut assembly form the preset opening angle through the spring.
Preferably, the four-bar linkage comprises: an upper connecting rod, a middle connecting rod and a lower connecting rod; one end of the upper connecting rod is fixedly connected with the rotating shaft, one end of the upper connecting rod is hinged with the middle connecting rod, one end of the lower connecting rod is hinged with the other end of the middle connecting rod, and the hinge shaft is fixedly connected with the lower lock stay bar for transmitting torque.
Preferably, the upper stay is hinged with the lower stay through the hinge shaft.
Preferably, the upper connecting rod, the middle connecting rod and the lower connecting rod are positioned on the same plane.
Preferably, one end of the lock spring is hinged on the lower stay bar, and the other end is hinged on the position of the upper lock stay bar close to the lower lock stay bar.
Preferably, the actuating cylinder and the unlocking rocker are positioned on the same side of the upper supporting rod, and the four-bar mechanism is positioned on the other side.
Preferably, the lower strut, landing gear strut assembly and strut lock mechanism form an isosceles triangle structure, the strut lock mechanism being the base.
Preferably, when the landing gear of the aircraft is in a down position, the actuating cylinder actuating shaft is contracted to drive the four-bar linkage mechanism to overcome the spring force of the lock spring so as to bend the stay bar lock mechanism towards the outer side of the preset opening angle; when locking, the actuating shaft of the actuating cylinder extends to drive the four-bar linkage mechanism to bend the stay bar locking mechanism towards the outer side of the preset opening angle;
when the landing gear of the aircraft is in a retracted position, the actuating shaft of the actuating cylinder extends to drive the four-bar linkage mechanism to overcome the spring force of the lock spring so as to bend the supporting rod lock mechanism towards the outer side of the preset opening angle; when locking, the actuating cylinder actuating shaft is retracted, and the four-bar linkage mechanism is driven to enable the stay bar locking mechanism to bend towards the outer side of the preset opening angle.
The advantages of the present application include: the four-bar unlocking mechanism can realize the unlocking and locking functions of the lock mechanism, can be arranged at the upper end of the stay bar in arrangement, can provide a larger space for the arrangement of the lock mechanism, meets the requirements of overall arrangement and the arrangement of the lock mechanism on the stroke of an unlocking actuating cylinder, and can provide more and better choices for the arrangement of the landing gear.
Drawings
FIG. 1 is a schematic view of the landing gear structure of a preferred embodiment of the present application, as laid out when it is down and locked;
fig. 2 is a schematic view of a portion a of fig. 2.
Detailed Description
In order to make the technical solution of the present application and the advantages thereof more apparent, the technical solution of the present application will be more fully described in detail below with reference to the accompanying drawings, it being understood that the specific embodiments described herein are only some of the embodiments of the present application, which are for explanation of the present application, not for limitation of the present application. It should be noted that, for convenience of description, only the portion relevant to the present application is shown in the drawings, and other relevant portions may refer to a general design, and without conflict, the embodiments and technical features in the embodiments may be combined with each other to obtain new embodiments.
Furthermore, unless defined otherwise, technical or scientific terms used in the description of this application should be given the ordinary meaning as understood by one of ordinary skill in the art to which this application belongs. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," "outer," and the like as used in this description are merely used to indicate relative directions or positional relationships, and do not imply that a device or element must have a particular orientation, be configured and operated in a particular orientation, and that the relative positional relationships may be changed when the absolute position of the object being described is changed, and thus should not be construed as limiting the present application. The terms "first," "second," "third," and the like, as used in the description herein, are used for descriptive purposes only and are not to be construed as indicating or implying any particular importance to the various components. The use of the terms "a," "an," or "the" and similar referents in the description of the invention are not to be construed as limited in number to the precise location of at least one. As used in this description, the terms "comprises," "comprising," or the like are intended to cover an element or article that appears before the term and that is listed after the term and its equivalents, without excluding other elements or articles.
Furthermore, unless specifically stated and limited otherwise, the terms "mounted," "connected," and the like in the description herein are to be construed broadly and refer to either a fixed connection, a removable connection, or an integral connection, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can also be communicated with the inside of two elements, and the specific meaning of the two elements can be understood by a person skilled in the art according to specific situations.
As shown in fig. 1-2, the present application provides an aircraft landing gear four-bar linkage unlocking mechanism comprising:
an upper stay bar 1, a lower stay bar 2, a landing gear strut assembly 3, a retraction actuator 4, a stay bar locking mechanism and a driving mechanism;
the upper end of the outer cylinder of the landing gear strut assembly 3 is hinged with an outer cylinder, a retractable actuating cylinder 4 is hinged on the machine body, the lower end of the outer cylinder is hinged with the lower end of a lower stay bar 2, the upper end of the lower stay bar 2 is hinged with an upper stay bar 1, and the upper stay bar 1 is hinged on the machine frame;
the driving mechanism comprises an actuating cylinder 7, an unlocking rocker 9 and a four-bar mechanism; one end of the actuating cylinder 7 is hinged on the upper supporting rod 1, the other end of the actuating cylinder is hinged with the unlocking rocker arm 9, the unlocking rocker arm 9 is fixedly connected to a rotating shaft hinged on the upper supporting rod 1, and the four-bar mechanism is fixedly connected with the rotating shaft to transmit torque to the supporting rod locking mechanism;
the strut lock mechanism is connected between the lower strut 2 and the landing gear strut assembly 3, and the drive mechanism drives the strut lock mechanism to unlock and lock, and when locked, the landing gear strut assembly 3 and the lower strut 2 form a preset opening angle, and when unlocked, the landing gear strut assembly 3 and the lower strut 2 are folded.
The stay bar locking mechanism comprises a lower locking stay bar 6, an upper locking stay bar 5 and a locking spring 8, wherein one end of the lower locking stay bar 6 is hinged with one end of the upper locking stay bar 5, the other end of the upper locking stay bar 5 is hinged with the landing gear strut assembly 3, one end of the locking spring 8 is hinged in the middle of the stay bar locking mechanism, the other end of the locking spring is hinged on the lower stay bar 2, a limiting device is arranged at the hinged position of the lower locking stay bar 6 and the upper locking stay bar 5, when the lower locking stay bar 6 and the upper locking stay bar 5 are unfolded, the limiting device limits the lower locking stay bar 6 and the upper locking stay bar 5 to rotate relatively and form deflection, and the deflection is kept by the spring 8 and the lower stay bar 2 and the landing gear strut assembly 3 form the preset opening angle.
The four-bar linkage includes: an upper link 10, a middle link 11, a lower link 12; one end of the upper connecting rod 10 is fixedly connected with the rotating shaft, one end of the upper connecting rod is hinged with the middle connecting rod 11, one end of the lower connecting rod 12 is hinged with the other end of the middle connecting rod 11, and the hinge shaft is fixedly connected with the lower locking stay bar 6 for transmitting torque.
The upper stay bar 1 is hinged with the lower stay bar 2 through the hinge shaft.
The upper link 10, the middle link 11 and the lower link 12 are positioned on the same plane.
One end of the lock spring 8 is hinged on the lower supporting rod 2, and the other end is hinged on the position of the upper locking supporting rod 5 close to the lower locking supporting rod 6.
The actuating cylinder 7 and the unlocking rocker 9 are positioned on the same side of the upper supporting rod 1, and the four-bar mechanism is positioned on the other side.
The lower stay bar 2, the landing gear strut assembly 3 and the stay bar locking mechanism form an isosceles triangle structure, and the stay bar locking mechanism is a bottom side.
When the landing gear of the aircraft is in a down position, the actuating cylinder 7 actuates the shaft to shrink when unlocking, and the four-bar linkage mechanism is driven to overcome the spring force of the lock spring 8 so as to bend the stay bar lock mechanism towards the outer side of the preset opening angle; when the lock is locked, the actuating cylinder 7 actuates the shaft to extend, and drives the four-bar linkage mechanism to enable the stay bar lock mechanism to bend towards the outer side of the preset opening angle;
when the landing gear of the aircraft is in a retracted position, the actuating shaft of the actuating cylinder 7 is extended during unlocking, and the four-bar linkage mechanism is driven to overcome the spring force of the lock spring 8 so as to bend the stay bar lock mechanism towards the outer side of the preset opening angle; when locking, the actuating cylinder 7 actuates the shaft to retract, and drives the four-bar linkage mechanism to bend the stay bar locking mechanism towards the outer side of the preset opening angle.
One embodiment includes:
the retraction mechanism comprises an upper supporting rod 1, a lower supporting rod 2, a landing gear strut assembly 3, a retraction actuator cylinder 4, an upper locking supporting rod 5, a lower locking supporting rod 6, an unlocking actuator cylinder 7, a locking spring 8, an unlocking rocker 9, an upper connecting rod 10, a middle connecting rod 11 and a lower connecting rod 12.
The outer cylinder end of the retractable actuating cylinder 4 is connected with the machine body through a bolt, a piston rod of the retractable actuating cylinder 4 is connected with the upper end of the landing gear strut assembly 3 through a bolt, the lower end of the landing gear strut assembly 3 is connected with the lower supporting rod 2 through a bolt, and the upper part of the upper supporting rod 1 is connected with the machine body through a bolt;
the lower part of the upper stay bar 1 is connected with the upper part of the lower stay bar 2, the lower lock stay bar 6 and the lower part of the lower connecting rod 12 through bolts (wherein a fixed joint is arranged between the lower connecting rod 6 and the bolts), the upper end of the unlocking actuating cylinder 7 is connected with the upper stay bar 1 through bolts, the lower end of the unlocking actuating cylinder 7 is connected with the unlocking rocker 9 through bolts, a shaft on the upper connecting rod 10 penetrates through an earhole of the upper stay bar 1 and is fixedly connected with the unlocking rocker 9 through bolts, the upper connecting rod 10 is connected with the middle connecting rod 11 through bolts, the middle connecting rod 11 is connected with the lower connecting rod 12 through bolts, the upper lock stay bar 5 is connected with the upper end of the landing gear strut assembly 3 through bolts, the lower end of the upper lock stay bar 5 is connected with the upper end of the lower lock stay bar 6 through bolts, the upper end of the spring 8 is connected with the upper lock stay bar 5 through bolts, and the lower end of the spring 8 is connected with the lower stay bar 2 through bolts.
The unlocking process of the application comprises the following steps:
a) Unlocking at the put-down position:
(1) The piston rod of the unlocking actuating cylinder 7 contracts to pull the unlocking rocker 9;
(2) The unlocking rocker 9 rotates and drives the upper connecting rod 10 to rotate;
(3) The upper connecting rod 10 pushes the middle connecting rod 11 to rotate;
(3) The middle connecting rod 11 pushes the lower connecting rod 12 to rotate;
(4) The lower connecting rod 12 drives the lower lock stay bar 6 to rotate and unlock against the spring force and other forces;
(5) The lock is completely unlocked after the deflection of the lower lock stay bar 6 and the upper lock stay bar 5 reaches a certain value;
(6) The landing gear retraction actuator is loaded to push the landing gear to retract.
Note that: the unlocking cylinder is extended to lock in the locking process.
b) Unlocking process at folding position
(1) The piston rod of the unlocking actuating cylinder stretches to pull the unlocking rocker arm;
(2) The unlocking rocker rotates and drives the upper connecting rod to rotate;
(3) The upper connecting rod pushes the middle connecting rod to rotate;
(3) The middle connecting rod pushes the lower connecting rod to rotate;
(4) The lower connecting rod drives the lower lock stay bar to rotate and overcomes the forces such as spring force and the like to unlock;
(5) The lock is completely unlocked after the deflection of the lower lock stay bar and the upper lock stay bar reaches a certain value;
(6) Landing gear extension actuator loading and landing gear extension pulling landing gear extension.
The advantages of the present application include: the four-bar unlocking mechanism can realize the unlocking and locking functions of the lock mechanism, can be arranged at the upper end of the stay bar in arrangement, can provide a larger space for the arrangement of the lock mechanism, meets the requirements of overall arrangement and the arrangement of the lock mechanism on the stroke of an unlocking actuating cylinder, and can provide more and better choices for the arrangement of the landing gear.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (9)
1. An aircraft landing gear four-bar linkage unlocking mechanism, comprising:
an upper stay bar (1), a lower stay bar (2), a landing gear strut assembly (3), a retractable actuator cylinder (4), a stay bar lock mechanism and a driving mechanism;
the upper end of the outer cylinder of the landing gear strut assembly (3) is hinged with the outer cylinder and is hinged with a retractable actuating cylinder (4) on the machine body, the lower end of the outer cylinder is hinged with the lower end of a lower stay bar (2), the upper end of the lower stay bar (2) is hinged with an upper stay bar (1), and the upper stay bar (1) is hinged on the machine frame;
the driving mechanism comprises an actuating cylinder (7), an unlocking rocker arm (9) and a four-bar mechanism; one end of the actuating cylinder (7) is hinged on the upper supporting rod (1), the other end of the actuating cylinder is hinged with the unlocking rocker (9), the unlocking rocker (9) is fixedly connected to a rotating shaft hinged on the upper supporting rod (1), and the four-bar mechanism is fixedly connected with the rotating shaft to transmit torque to the supporting rod locking mechanism;
the supporting rod locking mechanism is connected between the lower supporting rod (2) and the landing gear supporting rod assembly (3), the supporting rod locking mechanism is driven by the driving mechanism to unlock and lock, when the landing gear supporting rod assembly is locked, the landing gear supporting rod assembly (3) and the lower supporting rod (2) form a preset opening angle, and when the landing gear supporting rod assembly (3) and the lower supporting rod (2) are folded during unlocking.
2. An aircraft landing gear four-bar unlocking mechanism according to claim 1, wherein the strut locking mechanism comprises a lower locking strut (6), an upper locking strut (5) and a locking spring (8), one end of the lower locking strut (6) is hinged with one end of the upper locking strut (5), the other end of the upper locking strut (5) is hinged with the landing gear strut assembly (3), one end of the locking spring (8) is hinged in the middle of the strut locking mechanism, the other end of the locking spring is hinged on the lower strut (2), a limiting device is arranged at the hinged position of the lower locking strut (6) and the upper locking strut (5), and when the lower locking strut (6) and the upper locking strut (5) are unfolded, the limiting device limits the lower locking strut (6) and the upper locking strut (5) to rotate relatively and form deflection, and the deflection is kept and the lower strut (2) and the landing gear strut assembly (3) form the preset opening angle through the spring (8).
3. An aircraft landing gear four-bar linkage unlocking mechanism according to claim 2, wherein the four-bar linkage comprises: an upper connecting rod (10), a middle connecting rod (11) and a lower connecting rod (12); one end of the upper connecting rod (10) is fixedly connected with the rotating shaft, one end of the upper connecting rod is hinged with the middle connecting rod (11), one end of the lower connecting rod (12) is hinged with the other end of the middle connecting rod (11) and is fixedly connected with a hinge shaft, and the hinge shaft is fixedly connected with the lower locking stay bar (6) and transmits torque.
4. A four-bar linkage unlocking mechanism for an aircraft landing gear according to claim 3, wherein the upper strut (1) is hinged to the lower strut (2) by means of said hinge shaft.
5. A four-bar linkage unlocking mechanism for an aircraft landing gear according to claim 3, wherein the upper (10), middle (11) and lower (12) links are located in the same plane.
6. An aircraft landing gear four-bar linkage unlocking mechanism according to claim 1, wherein the lock spring (8) is hinged at one end to the lower strut (2) and at one end to the upper lock strut (5) at a position close to the lower lock strut (6).
7. An aircraft landing gear four-bar linkage unlocking mechanism according to claim 1, wherein the actuator cylinder (7) and the unlocking rocker (9) are located on the same side of the upper stay (1), and the four-bar linkage is located on the other side.
8. An aircraft landing gear four-bar linkage unlocking mechanism according to claim 1, wherein the lower strut (2), the landing gear strut assembly (3) and the strut lock mechanism form an isosceles triangle structure, the strut lock mechanism being the base.
9. An aircraft landing gear four-bar linkage unlocking mechanism according to claim 1, wherein when the aircraft landing gear is in the down position, the actuating cylinder (7) is contracted by the actuating shaft when unlocking, and the four-bar linkage is driven to overcome the spring force of the lock spring (8) so as to bend the stay bar lock mechanism towards the outer side of the preset opening angle; when the lock is locked, an actuating shaft of the actuating cylinder (7) extends to drive the four-bar linkage mechanism to enable the stay bar lock mechanism to bend towards the outer side of the preset opening angle;
when the landing gear of the aircraft is in a retracted position, the actuating shaft of the actuating cylinder (7) is extended to drive the four-bar linkage mechanism to overcome the spring force of the lock spring (8) so as to bend the stay bar lock mechanism towards the outer side of the preset opening angle; when locking, the actuating cylinder (7) actuates the shaft to retract, and drives the four-bar linkage mechanism to enable the stay bar locking mechanism to bend towards the outer side of the preset opening angle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311690227.9A CN117622478A (en) | 2023-12-11 | 2023-12-11 | Four-bar unlocking mechanism of aircraft landing gear |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311690227.9A CN117622478A (en) | 2023-12-11 | 2023-12-11 | Four-bar unlocking mechanism of aircraft landing gear |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117622478A true CN117622478A (en) | 2024-03-01 |
Family
ID=90031992
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311690227.9A Pending CN117622478A (en) | 2023-12-11 | 2023-12-11 | Four-bar unlocking mechanism of aircraft landing gear |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117622478A (en) |
-
2023
- 2023-12-11 CN CN202311690227.9A patent/CN117622478A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8602352B2 (en) | Method for operating a landing gear assembly with a breaker strut | |
| US9272775B2 (en) | Compact improved aircraft landing gear | |
| CA2814535A1 (en) | Landing gear for an aircraft | |
| US8302905B2 (en) | Aircraft landing gear comprising an operation strut device and aircraft provided therewith | |
| CN102202968B (en) | Landing gear mechanism for aircraft | |
| CN108839790B (en) | Folding type retractable structure of undercarriage and retractable method thereof | |
| CN108839668B (en) | Car coupler expansion device and car coupler | |
| CN113799646B (en) | Battery base and battery replacement trolley | |
| CN115551798A (en) | Double-column vehicle lift with compact telescopic boom | |
| CN117622478A (en) | Four-bar unlocking mechanism of aircraft landing gear | |
| CN111645850B (en) | Folding member unfolding, supporting and locking device | |
| JP5898482B2 (en) | Counterweight attachment / detachment device | |
| US20230192275A1 (en) | Retractable aircraft landing gear provided with a strut having an integrated actuator | |
| CN112623281B (en) | Redundant-drive large-self-folding-angle support locking unfolding and folding device | |
| CN109050879A (en) | A kind of folding support rod formula wingfold mechanism | |
| WO2022056623A1 (en) | Landing gear with shortening motion | |
| EP3992054B1 (en) | Foldable vehicular coupler and vehicle | |
| CN112644692A (en) | Aircraft landing gear down position locking device | |
| CN116691999A (en) | Horn assembly and aircraft | |
| CN216943526U (en) | Folding wing | |
| CN215361167U (en) | Flexible footboard and car | |
| CN219029732U (en) | Aircraft landing gear retracting mechanism | |
| CN118083117A (en) | Rocker arm type side-folding falling frame | |
| CN115489434A (en) | Flexible footboard and car | |
| CN214570144U (en) | Folding gantry bearing mechanism |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |