CN216805787U - Airplane cabin door synchronous driving device - Google Patents
Airplane cabin door synchronous driving device Download PDFInfo
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- CN216805787U CN216805787U CN202220677186.4U CN202220677186U CN216805787U CN 216805787 U CN216805787 U CN 216805787U CN 202220677186 U CN202220677186 U CN 202220677186U CN 216805787 U CN216805787 U CN 216805787U
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- fork
- rocker arm
- joint
- fork lug
- driver
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Abstract
The utility model discloses an airplane cabin door synchronous driving device which comprises a driver, a rocker arm I and two groups of transmission assemblies, wherein the driver is connected with the rocker arm I; the transmission assembly comprises a first fork lug joint, a second fork lug joint, a third fork lug joint, a rocker arm II, a pull rod and a rocker arm III which are connected in sequence; the two ends of the rotating shaft I are respectively fixedly connected with the inner ends of the corresponding first fork lug joints, the first fork lug part arranged at the outer end of the first fork lug joint is connected with the second fork lug part I arranged at the inner end of the second fork lug joint through a cross joint, the second fork lug part II arranged at the outer end of the second fork lug joint is also connected with the third fork lug part arranged at the inner end of the third fork lug joint through a cross joint, and the inner end of the rotating shaft II is fixedly connected with the outer end of the third fork lug joint; the upper end of the pull rod is hinged to the rocker arm II, and the lower end of the pull rod is hinged to the rocker arm III. The utility model can drive the non-parallel rotating shafts of the hatches at the left side and the right side by one driver, thereby being beneficial to realizing the synchronous driving of the hatches at the two sides and reducing the complexity of a control system.
Description
Technical Field
The utility model relates to the field of aeronautical instruments, in particular to an airplane cabin door synchronous driving device.
Background
In order to realize the opening and closing of the hatches at the left side and the right side of the airplane, the hatch door driving system generally comprises a power source, a hatch door mechanism and a synchronizing mechanism, wherein the power source is used for driving the hatch door mechanism, the synchronizing mechanism and the like to provide power required by movement, and the synchronizing mechanism is used for ensuring the synchronism of the movement of the hatches; a prior art door actuation system can be seen, but not limited to, patent CN 109779437 a. However, when the opening and closing rotation shafts of the doors on the left and right sides of the aircraft are disposed in a non-parallel manner (generally, symmetrically disposed, and the axes of the two doors have an included angle), the rotation shafts of the doors on the left and right sides can only be driven by different drivers (such as hydraulic actuators) respectively, and since the two drivers are controlled separately, it is not beneficial to realize synchronous driving of the doors on both sides, thereby complicating the control system.
Therefore, there is a need for a synchronous driving device for airplane doors, which can drive the non-parallel rotating shafts of the doors on the left and right sides simultaneously by a driver, thereby facilitating the realization of synchronous driving of the doors on both sides and reducing the complexity of a control system.
SUMMERY OF THE UTILITY MODEL
In view of this, the present invention provides a device for synchronously driving aircraft doors, which can drive the non-parallel rotating shafts of the doors on the left and right sides by one driver, thereby facilitating the realization of synchronous driving of the doors on both sides and reducing the complexity of a control system.
In order to achieve the aim, the utility model provides an airplane cabin door synchronous driving device which comprises a driver, a rocker arm I driven by the driver to rotate and two groups of transmission assemblies arranged in bilateral symmetry;
the transmission assembly comprises a first fork lug joint, a second fork lug joint, a third fork lug joint, a rocker arm II, a pull rod and a rocker arm III which are connected in sequence and are fixedly connected with a rotating shaft of the aircraft cabin door; the two ends of a rotating shaft I which is fixedly connected with the rocker arm I and synchronously rotates are respectively fixedly connected with the inner ends of corresponding first fork lug joints, a first fork lug part arranged at the outer end of the first fork lug joint is connected with a second fork lug part I arranged at the inner end of the second fork lug joint through a cross joint, a second fork lug part II arranged at the outer end of the second fork lug joint is also connected with a third fork lug part arranged at the inner end of the third fork lug joint through a cross joint, and the inner end of the rotating shaft II which is fixedly connected with the rocker arm II and synchronously rotates is fixedly connected with the outer end of the third fork lug joint; the upper end of the pull rod is hinged to the rocker arm II, and the lower end of the pull rod is hinged to the rocker arm III, so that the rocker arm III is driven to rotate by the rocker arm II.
As a further improvement to the technical scheme of the utility model, the cross joint comprises a transverse rod and a longitudinal rod vertically and fixedly connected with the transverse rod; between two parallel fork ears of first fork ear portion and all be connected through corresponding longitudinal rod between two parallel fork ears of second fork ear portion II, between two parallel fork ears of second fork ear portion I and all be connected through corresponding transverse rod between two parallel fork ears of third fork ear portion.
As a further improvement of the technical scheme, the device further comprises a support I used for positioning and installing the rocker arm I, two parallel support lugs I are arranged on the support I in a protruding mode, and the left end and the right end of the rotating shaft I respectively penetrate through the two support lugs I and are connected with corresponding first fork lug joints.
As a further improvement of the technical scheme of the utility model, the device also comprises a support II for positioning and installing the rocker arm II, two parallel support lugs II are convexly arranged on the support II, and the rotating shaft II penetrates through the position between the two support lugs II and is fixedly connected with the rocker arm II.
As a further improvement to the technical scheme of the utility model, the driver is of a hydraulic actuator cylinder structure; the device still includes a biography power and connects, pass power and connect including locating the connecting cylinder on upper portion and locating the engaging lug of lower part, the fixed cover of connecting cylinder is established outside the output shaft of driver, the engaging lug is articulated mutually with rocking arm I.
As a further improvement of the technical scheme of the utility model, the device also comprises a support III for positioning and installing the driver, two parallel support lugs III are convexly arranged on the support III, and a connecting part fixed at the top end of the driver extends between the two support lugs III and is rotatably connected with the support III.
As a further improvement of the technical scheme of the utility model, the lower end of the rocker arm III is provided with a shaft fixing hole for inserting and fixedly connecting a rotating shaft of the aircraft cabin door.
Compared with the prior art, the utility model has the following beneficial technical effects:
the utility model provides an airplane cabin door synchronous driving device, which is characterized in that a driver, a rocker arm I and a transmission assembly are arranged, and the transmission assembly is designed to comprise a first fork lug joint, a second fork lug joint, a third fork lug joint, a rocker arm II, a pull rod and a rocker arm III which are connected in sequence; therefore, the driver can drive the rocker arm I to rotate within a certain angle range when acting, and the transmission assembly adopts a structure that the fork lug joint and the cross joint are matched for transmission, so that the rotating shaft I and the rotating shaft II can be in a non-parallel relation in space, the non-linear transmission of power is realized, and the power is transmitted to the non-parallel rotating shafts of the hatches at the left side and the right side;
therefore, the utility model can drive the non-parallel rotating shafts of the hatches at the left side and the right side by one driver, thereby being beneficial to realizing the synchronous driving of the hatches at the two sides and reducing the complexity of a control system. Of course, the same applies to the parallel axes of rotation of the right and left side hatches.
Advantages of additional aspects of the utility model will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the utility model.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is an enlarged view of FIG. 1 at A;
FIG. 3 is a schematic structural view of a cross joint of the present invention;
fig. 4 is a use state diagram of the present invention.
Detailed Description
The technical scheme in the embodiment of the utility model will be clearly and completely described below with reference to the accompanying drawings; it is to be understood that the embodiments described are merely exemplary embodiments, rather than exemplary embodiments, and that all other embodiments may be devised by those skilled in the art without departing from the scope of the present invention.
Examples
As shown in fig. 1 to 4: the embodiment provides an airplane cabin door synchronous driving device which comprises a driver 1, a rocker arm I2 driven by the driver 1 to rotate and two groups of transmission assemblies arranged in bilateral symmetry. The driver 1 is used as a power input source, and power can be respectively transmitted to the non-parallel rotating shafts of the hatches at the left side and the right side of the tail end through the rocker arm I2 and the two groups of transmission assemblies. The drive 1 is preferably of a hydraulic ram configuration, in which case the two sets of transmission assemblies are symmetrical about the axis of the output shaft 1a of the drive 1.
The terms "left", "right", "up" and "down" refer to the directions shown in FIGS. 1 and 4.
The transmission assembly comprises a first fork lug joint 3, a second fork lug joint 4, a third fork lug joint 5, a rocker arm II 6, a pull rod 7 and a rocker arm III 9 which are fixedly connected with an airplane cabin door rotating shaft 8.
The two ends of a rotating shaft I (not shown in the figure) which is fixedly connected with the rocker arm I2 and synchronously rotates are respectively and fixedly connected with the inner ends of corresponding first fork lug joints 3, a first fork lug part 3a arranged at the outer end of each first fork lug joint 3 is connected with a second fork lug part I4 a arranged at the inner end of a second fork lug joint 4 through a cross joint 10, a second fork lug part II 4b arranged at the outer end of the second fork lug joint 4 is also connected with a third fork lug part 5a arranged at the inner end of a third fork lug joint 5 through a cross joint 10, and the inner end of a rotating shaft II 11 which is fixedly connected with the rocker arm II 6 and synchronously rotates is fixedly connected with the outer end of the third fork lug joint 5; the upper end of the pull rod 7 is hinged to the rocker arm II 6, and the lower end of the pull rod is hinged to the rocker arm III 9, so that the rocker arm III 9 is driven to rotate by the rocker arm II 6.
The driver 1 can drive the rocking arm I2 to rotate within a certain angle range when acting, and the transmission assembly adopts a structure that the fork lug joint and the cross joint 10 are matched for transmission, so that the rotating shaft I and the rotating shaft II 11 can be in a non-parallel relation in space, the non-linear transmission of power is realized, and the power is transmitted to the non-parallel rotating shafts 8 of the hatchdoors on the left side and the right side.
In this embodiment, the cross joint 10 includes a transverse rod 10a and a longitudinal rod 10b vertically and fixedly connected to the transverse rod 10 a; between two parallel fork ears of first fork ear 3a and all be connected through corresponding longitudinal rod 10b between two parallel fork ears of second fork ear II 4b, between two parallel fork ears of second fork ear I4 a and between two parallel fork ears of third fork ear 5a all be connected through corresponding horizontal pole 10 a. The transverse rod 10a and the longitudinal rod 10b are fixedly connected to form a cross structure; the transverse bar 10a and the longitudinal bar 10b can be hollow cylindrical structures, and corresponding through holes are arranged on each parallel fork lug so as to facilitate connection among all the parts through rotating pin connection or other connection modes.
In this embodiment, the device further comprises a support I12 used for positioning and installing the rocker arm I2, two parallel support lugs I12 a are convexly arranged on the support I12, and the left end and the right end of the rotating shaft I respectively penetrate through the two support lugs I12 a and are connected with the corresponding first fork lug connectors 3. When in use, the support I12 is fixed in the engine room; the two support lugs I12 a are perpendicular to the two parallel fork lugs of the first fork lug part 3 a; the area between the two support lugs I12 a can limit the rotating direction of the rocker arm I2, and the driving accuracy is improved.
In this embodiment, the device further comprises a support II 13 for positioning and mounting the rocker arm II 6, two parallel support lugs II 13a are convexly arranged on the support II 13, and the rotating shaft II 11 penetrates through the position between the two support lugs II 13a and is fixedly connected with the rocker arm II 6. When in use, the support II 13 is fixed in the engine room; the two support lugs II 13a are perpendicular to the two parallel fork lugs of the third fork lug part 5 a; the area between the two support lugs II 13a can limit the rotation direction of the rocker arm II 6, and the driving accuracy is improved.
In this embodiment, the device further comprises a force transmission joint, the force transmission joint comprises a connecting cylinder 14a arranged on the upper portion and a connecting lug 14b arranged on the lower portion, the connecting cylinder 14a is fixedly sleeved outside the output shaft 1a of the driver 1, and the connecting lug 14b is hinged to the rocker arm I2. The connecting cylinder 14a is fixedly connected with the connecting lug 14 b; the connecting cylinder 14a can be connected with the output shaft 1a of the driver 1 in a threaded manner; when the driver 1 acts, the output shaft 1a can stretch out and draw back along the axial direction, so that the rocker arm I2 is driven to rotate.
In this embodiment, the device further comprises a support iii 15 for positioning and mounting the driver 1, two parallel support lugs iii 15a are convexly arranged on the support iii 15, and a connecting portion 1b fixed at the top end of the driver 1 extends between the two support lugs iii 15a and is rotatably connected with the two support lugs iii 15 a. In use, the support III 15 is fixed in the nacelle.
In this embodiment, a shaft fixing hole 9a for inserting and fixedly connecting the aircraft door rotating shaft 8 is formed in the lower end of the rocker arm iii 9. As shown in fig. 4, the inner ends of the two rotating shafts 8 are inserted into the shaft fixing holes 9a, and when the rocker arm iii 9 rotates, the two rotating shafts 8 are also forced to rotate, thereby realizing the synchronous driving of the hatches on the left and right sides.
The foregoing is merely an example of the present invention and common general knowledge of known specific structures and features of the embodiments is not described herein in any greater detail. It should be noted that, for those skilled in the art, without departing from the structure of the present invention, several changes and modifications can be made, which should also be regarded as the protection scope of the present invention, and these will not affect the effect of the implementation of the present invention and the practicability of the patent. The scope of the claims of the present application shall be determined by the contents of the claims, and the description of the embodiments and the like in the specification shall be used to explain the contents of the claims.
Claims (7)
1. The utility model provides an aircraft hatch door synchronous drive device which characterized in that: the device comprises a driver, a rocker arm I driven by the driver to rotate and two groups of transmission components arranged in bilateral symmetry;
the transmission assembly comprises a first fork lug joint, a second fork lug joint, a third fork lug joint, a rocker arm II, a pull rod and a rocker arm III which are connected in sequence and are fixedly connected with a rotating shaft of the aircraft cabin door; the two ends of a rotating shaft I which is fixedly connected with the rocker arm I and synchronously rotates are respectively fixedly connected with the inner ends of corresponding first fork lug joints, a first fork lug part arranged at the outer end of the first fork lug joint is connected with a second fork lug part I arranged at the inner end of the second fork lug joint through a cross joint, a second fork lug part II arranged at the outer end of the second fork lug joint is also connected with a third fork lug part arranged at the inner end of the third fork lug joint through a cross joint, and the inner end of the rotating shaft II which is fixedly connected with the rocker arm II and synchronously rotates is fixedly connected with the outer end of the third fork lug joint; the upper end of the pull rod is hinged to the rocker arm II, and the lower end of the pull rod is hinged to the rocker arm III, so that the rocker arm III is driven to rotate by the rocker arm II.
2. The aircraft door synchronous drive device according to claim 1, wherein: the cross joint comprises a transverse rod and a longitudinal rod vertically and fixedly connected to the transverse rod; between two parallel fork ears of first fork ear portion and all be connected through corresponding longitudinal rod between two parallel fork ears of second fork ear portion II, between two parallel fork ears of second fork ear portion I and all be connected through corresponding transverse rod between two parallel fork ears of third fork ear portion.
3. An aircraft door synchronous drive arrangement according to claim 1, wherein: the device is still including the support I that is used for fixing a position installation rocking arm I, I epirelief of support is equipped with two parallel journal stirrup I, pivot I about both ends run through two journal stirrups I respectively and with the first fork ear joint connection that corresponds.
4. An aircraft door synchronous drive arrangement according to claim 1, wherein: the device still includes support II that is used for fixing a position installation rocking arm II, II epirelief on the support is equipped with two lugs II that parallel, pivot II penetrate the position between two lugs II and with II fixed connection of rocking arm.
5. An aircraft door synchronous drive arrangement according to claim 1, wherein: the driver is of a hydraulic actuator cylinder structure; the device still includes a biography power and connects, pass power and connect including locating the connecting cylinder on upper portion and locating the engaging lug of lower part, the fixed cover of connecting cylinder is established outside the output shaft of driver, the engaging lug is articulated mutually with rocking arm I.
6. An aircraft door synchronous drive arrangement according to claim 5, wherein: the device is still including being used for fixing a position the support III of installation driver, the III epirelief of support is equipped with two parallel lugs III, and the connecting portion that is fixed in the driver top stretches into between two lugs III and swivelling joint.
7. An aircraft door synchronous drive arrangement according to claim 1, wherein: and a shaft fixing hole for inserting and fixedly connecting the rotating shaft of the airplane cabin door is formed in the lower end of the rocker arm III.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220677186.4U CN216805787U (en) | 2022-03-24 | 2022-03-24 | Airplane cabin door synchronous driving device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220677186.4U CN216805787U (en) | 2022-03-24 | 2022-03-24 | Airplane cabin door synchronous driving device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216805787U true CN216805787U (en) | 2022-06-24 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202220677186.4U Active CN216805787U (en) | 2022-03-24 | 2022-03-24 | Airplane cabin door synchronous driving device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216805787U (en) |
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2022
- 2022-03-24 CN CN202220677186.4U patent/CN216805787U/en active Active
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