CN216332859U - Aircraft cabin door posture adjusting device - Google Patents
Aircraft cabin door posture adjusting device Download PDFInfo
- Publication number
- CN216332859U CN216332859U CN202023282300.3U CN202023282300U CN216332859U CN 216332859 U CN216332859 U CN 216332859U CN 202023282300 U CN202023282300 U CN 202023282300U CN 216332859 U CN216332859 U CN 216332859U
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- cabin door
- adjusting device
- supporting
- utility
- adjustable
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- 238000000034 method Methods 0.000 abstract description 7
- 238000012795 verification Methods 0.000 abstract description 6
- 230000036544 posture Effects 0.000 description 21
- 238000010586 diagram Methods 0.000 description 5
- 229910000831 Steel Inorganic materials 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
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Abstract
The utility model discloses an aircraft cabin door attitude adjusting device, which comprises: the adjustable supporting platform is movably connected with the fixed supporting base through three groups of connecting structures; among the three groups of connecting structures, one group of connecting structure is a supporting rod, the two hydraulic actuating cylinders of the two groups of connecting structures are arranged in a triangular mode on the adjustable supporting platform and the fixed supporting base, and the supporting rod and the two hydraulic actuating cylinders are arranged in a triangular mode. The technical scheme of the utility model solves the problems that a plurality of sets of supporting structures are required to be arranged in the verification mode of the opening capability of the existing cabin, and the test piece needs to be repeatedly disassembled and assembled in the test process.
Description
Technical Field
The utility model relates to the technical field of airplane cabin doors, in particular to an airplane cabin door posture adjusting device.
Background
Transport class aircraft emergency exit doors require verification before use, typically verifying the opening capability of the doors in the event of 1 nose landing gear, 2 main landing gears breaking individually and in various possible combinations.
The verification method adopted at home at present is as follows: the method is characterized in that a fixed supporting structure is arranged to support the cabin door test bench to a required angle, then the cabin door opening capability test is carried out, 1 front undercarriage and 2 main undercarriages are required to be achieved normally, the cabin door postures under the conditions of individual breaking and various possible combined breaking conditions are required to be achieved, a plurality of sets of supporting structures are required to be arranged in the verification mode, and a test piece needs to be repeatedly disassembled and assembled in the test process.
SUMMERY OF THE UTILITY MODEL
The purpose of the utility model is as follows: the embodiment of the utility model provides an aircraft cabin door posture adjusting device, which aims to solve the problems that a plurality of sets of supporting structures are required to be arranged in a verification mode of the opening capacity of the existing cabin, and a test piece needs to be repeatedly disassembled and assembled in a test process.
The technical scheme of the utility model is as follows: the embodiment of the utility model provides an aircraft cabin door attitude adjusting device, which comprises: the device comprises a fixed support base 1, an adjustable support table 2 and three groups of connecting structures for movably connecting the adjustable support table 2 and the fixed support base 1;
in the three groups of connecting structures, one group of connecting structure is a supporting rod 3, two hydraulic actuating cylinders 4 are arranged in the two groups of connecting structures, and the supporting rod 3 and the two hydraulic actuating cylinders 4 are arranged in a triangular shape on the adjustable supporting platform 2 and the fixed supporting base 1.
Alternatively, in the aircraft door attitude adjustment device as described above,
one end of the support rod 3 is fixedly connected with the fixed support base 1, and the other end of the support rod is connected with the adjustable support platform 2 through a hinge.
Alternatively, in the aircraft door attitude adjustment device as described above,
two ends of the hydraulic actuating cylinder 4 are respectively connected with the fixed supporting base 1 and the adjustable supporting platform 2 through hinges.
Alternatively, in the aircraft door attitude adjustment device as described above,
the aircraft cabin door posture adjusting device is used for controlling and adjusting the deflection direction and the deflection angle of the supporting platform 2 by driving one or two hydraulic actuating cylinders 4 to move.
Optionally, in the aircraft door attitude adjusting apparatus described above, the aircraft door attitude adjusting apparatus further includes: a console 5 connected to each of the hydraulic rams 4, the console having a driver configured to drive the hydraulic rams 4;
the control console is used for controlling one or two hydraulic actuating cylinders 4 to extend and retract in different strokes through a driving program, so that the support platform 2 can be adjusted to deflect around a hinge point of the support rod 3 when the hydraulic actuating cylinders 4 are driven, and the deflection posture of the adjustable support platform 2 is controlled.
Alternatively, in the aircraft door attitude adjustment device as described above,
the aircraft cabin door posture adjusting device is also used for simulating various deflection postures of the aircraft cabin door when 1 nose landing gear and 2 main landing gears are independently broken and different combinations are broken by controlling the deflection posture of the adjustable supporting platform 2.
The utility model has the beneficial effects that: the embodiment of the utility model provides an aircraft cabin door attitude adjusting device, which can adjust a supporting platform 2 to deflect around 1 supporting point according to various possible angles by driving 2 hydraulic actuating cylinders 4, so that the supporting platform 2 can be adjusted to reach the angle required by a test; by adopting the angle control mode of the adjustable support platform 2 in the implementation of the utility model, the cabin door postures can be adjusted under the conditions that 1 nose landing gear and 2 main landing gears are independently broken off and various possible combinations are broken off. The airplane cabin door attitude adjusting device provided by the embodiment of the utility model is applied to a cabin door test bench, and particularly, the cabin door test bench is fixedly arranged on the attitude adjusting device, so that the cabin door test bench can be installed once only, a plurality of multi-angle tests can be executed, repeated disassembly and assembly are not needed, the operation is simple, and the realization is easy.
Drawings
The accompanying drawings are included to provide a further understanding of the utility model and are incorporated in and constitute a part of this specification, illustrate embodiments of the utility model and together with the example serve to explain the principles of the utility model and not to limit the utility model.
Fig. 1 is a schematic structural diagram of an aircraft door attitude adjustment device according to an embodiment of the present invention;
FIG. 2 is a schematic view of the three-dimensional structural components of the aircraft door attitude adjustment device shown in FIG. 1;
FIG. 3 is a schematic diagram of different attitudes or deflection angles of your aircraft door attitude adjustment device according to an embodiment of the present invention;
fig. 4 is a schematic structural diagram of another aircraft door attitude adjustment device according to an embodiment of the present invention.
DETAILED DESCRIPTION OF EMBODIMENT (S) OF INVENTION
In order to make the objects, technical solutions and advantages of the present invention more apparent, embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that the embodiments and features of the embodiments in the present application may be arbitrarily combined with each other without conflict.
Aiming at the mode that the emergency exit door of the transport aircraft in the background technology is verified before use. In the test process, for each cabin door posture, the test piece needs to be repeatedly disassembled and assembled. The supporting structures are large in quantity and large in disassembly and assembly workload, and the required specific posture (installation angle) is not easy to guarantee.
Therefore, the embodiment of the utility model provides an aircraft cabin door attitude adjusting device which is applied to an aircraft emergency exit cabin door test and used for improving an aircraft cabin door function test mode and filling the gap of cabin door verification.
The following specific embodiments of the present invention may be combined, and the same or similar concepts or processes may not be described in detail in some embodiments.
Fig. 1 is a schematic structural view of an aircraft door attitude adjusting device according to an embodiment of the present invention, a left side view of fig. 1 is a front view of the aircraft door attitude adjusting device, a right side view of the aircraft door attitude adjusting device, fig. 2 is a schematic three-dimensional structural component view of the aircraft door attitude adjusting device shown in fig. 1, the left side view of fig. 1 is a three-dimensional view, and the right side view of fig. 1 is an exploded view. As shown in fig. 1 and 2, an aircraft door attitude adjusting device provided by an embodiment of the present invention may include: the adjustable supporting platform comprises a fixed supporting base 1, an adjustable supporting platform 2 and three groups of connecting structures for movably connecting the adjustable supporting platform 2 and the fixed supporting base 1.
In the structure of the aircraft door attitude adjusting device shown in fig. 1 and 2, one of the three connecting structures is a support rod 3, and two hydraulic actuators 4 of the two connecting structures are arranged on the support rod 3 and the two hydraulic actuators 4 on the adjustable support platform 2 and the fixed support base 1 in a triangular arrangement.
In the specific connection structure of the embodiment of the utility model, on one hand, one end of the support rod 3 is fixedly connected with the fixed support base 1, and the other end is connected with the adjustable support platform 2 through a hinge.
On the other hand, two ends of the hydraulic actuating cylinder 4 are respectively connected with the fixed supporting base 1 and the adjustable supporting platform 2 through hinges.
The airplane cabin door posture adjusting device in the embodiment of the utility model has the following functions: the deflection direction and the deflection angle of the adjustable support table 2 are controlled by driving the movement of one or two hydraulic cylinders 4.
Fig. 3 is a schematic diagram of different attitudes or deflection angles of your airplane door attitude adjusting device according to an embodiment of the present invention. As shown in fig. 3, the two hydraulic cylinders 4 are driven to realize various forms capable of adjusting the yaw direction and the yaw angle of the support base 2.
By adopting the airplane cabin door attitude adjusting device provided by the embodiment of the utility model, the cabin door test bench can be fixedly arranged on the attitude adjusting device, and the adjustable supporting platform 2 can deflect around 1 supporting point by various possible angles by driving the 2 hydraulic actuating cylinders 4, so that the adjustable supporting platform 2 can reach the angle required by the test; by adopting the angle control mode of the adjustable support platform 2 in the implementation of the utility model, the cabin door postures can be adjusted under the conditions that 1 nose landing gear and 2 main landing gears are independently broken off and various possible combinations are broken off. The airplane cabin door attitude adjusting device provided by the embodiment of the utility model is applied to the cabin door test bed, so that the cabin door test bed can execute multiple multi-angle tests through one-time installation, repeated disassembly and assembly are not needed, the operation is simple, and the realization is easy.
Fig. 4 is a schematic structural diagram of another aircraft door attitude adjustment device according to an embodiment of the present invention. In a specific implementation manner, the aircraft door attitude adjustment device provided in the embodiment of the present invention may further include: a control console 5 connected to each of the hydraulic rams 4, and having a drive program configured therein for driving the hydraulic rams 4.
The control console in the embodiment of the utility model is used for controlling one or two hydraulic actuating cylinders 4 to extend and retract in different strokes through a driving program, so that the hydraulic actuating cylinders 4 can adjust the support platform 2 to deflect around the hinge point of the support rod 3 when being driven, and the deflection posture of the adjustable support platform 2 is controlled.
In practice, it is possible to programme 2 hydraulic rams 4 to have different combinations of strokes to achieve a predetermined range of possible attitude or angular deflections.
The aircraft cabin door posture adjusting device in the embodiment of the utility model is also used for simulating various deflection postures of the aircraft cabin door when 1 nose landing gear, 2 main landing gears are independently broken off and different combinations are broken off by controlling the deflection posture of the adjustable supporting platform 2.
The following describes an implementation of the aircraft door attitude adjusting device provided by the embodiment of the utility model by using a specific implementation example.
The technical problem to be solved based on the embodiment of the utility model is as follows: the problem that different deflection angles of a cabin door test bed are realized through different combinations of multiple groups of fixed supporting structures with multiple specifications is solved, and therefore the airplane cabin door attitude adjusting device is designed in the embodiment of the utility model, the device is driven by hydraulic actuators to be installed once, and different deflection angles of the cabin door test bed are realized through different stroke combinations of 2 hydraulic actuators 4. The aircraft cabin door posture adjusting device is provided with a fixed supporting base formed by welding profile steel and an adjustable supporting platform formed by welding the profile steel, wherein the fixed supporting base is used for being fixed on the ground.
When the test is carried out, the test piece can be movably arranged on the fixed supporting base, the fixed supporting base is connected with the adjustable supporting platform through three groups of connecting structures, for example, one group of connecting structures in the figure is a supporting rod, one end of the supporting rod is fixedly connected with the fixed supporting base, and the other end of the supporting rod is connected with the adjustable supporting platform through a hinge; the other two groups of connecting structures are hydraulic actuating cylinders, and two ends of each hydraulic actuating cylinder are respectively hinged with the fixed supporting base and the adjustable supporting platform. The adjustable supporting platform is driven to deflect around the hinge point of the supporting rod when the 2 hydraulic actuating cylinders move, various preset possible deflection postures of the adjustable supporting platform assembly are realized through different stroke combinations of the 2 hydraulic actuating cylinders, and therefore posture adjustment of a test piece fixedly installed on the adjustable supporting platform assembly is realized.
Although the embodiments of the present invention have been described above, the above description is only for the convenience of understanding the present invention, and is not intended to limit the present invention. It will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the utility model as defined by the appended claims.
Claims (3)
1. An aircraft door attitude adjustment device, comprising: the device comprises a fixed supporting base (1), an adjustable supporting table (2) and three groups of connecting structures for movably connecting the adjustable supporting table (2) and the fixed supporting base (1);
among the three groups of connecting structures, one group of connecting structure is a supporting rod (3), two hydraulic actuating cylinders (4) of the two groups of connecting structures are arranged, and the supporting rod (3) and the two hydraulic actuating cylinders (4) are arranged on the adjustable supporting platform (2) and the fixed supporting base (1) in a triangular mode.
2. The aircraft door attitude adjustment device of claim 1,
one end of the supporting rod (3) is fixedly connected with the fixed supporting base (1), and the other end of the supporting rod is connected with the adjustable supporting platform (2) through a hinge.
3. The aircraft door attitude adjustment device of claim 2,
two ends of the hydraulic actuating cylinder (4) are respectively connected with the fixed supporting base (1) and the adjustable supporting platform (2) through hinges.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202023282300.3U CN216332859U (en) | 2020-12-29 | 2020-12-29 | Aircraft cabin door posture adjusting device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202023282300.3U CN216332859U (en) | 2020-12-29 | 2020-12-29 | Aircraft cabin door posture adjusting device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216332859U true CN216332859U (en) | 2022-04-19 |
Family
ID=81129793
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202023282300.3U Expired - Fee Related CN216332859U (en) | 2020-12-29 | 2020-12-29 | Aircraft cabin door posture adjusting device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216332859U (en) |
-
2020
- 2020-12-29 CN CN202023282300.3U patent/CN216332859U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20220419 |