CN114320049B - Cabin door linkage mechanism of ram air turbine system - Google Patents
Cabin door linkage mechanism of ram air turbine system Download PDFInfo
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- CN114320049B CN114320049B CN202111662661.7A CN202111662661A CN114320049B CN 114320049 B CN114320049 B CN 114320049B CN 202111662661 A CN202111662661 A CN 202111662661A CN 114320049 B CN114320049 B CN 114320049B
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- connecting rod
- lock cover
- door linkage
- turbine system
- air turbine
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- 238000009434 installation Methods 0.000 abstract description 6
- 230000000694 effects Effects 0.000 abstract description 3
- 239000013585 weight reducing agent Substances 0.000 abstract description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000005461 lubrication Methods 0.000 description 1
Abstract
The invention discloses a cabin door linkage mechanism of a ram air turbine system. Comprises an upper pin rod (1), an upper lock cover (4), a lower lock cover (9), a connecting rod (6), a connecting rod (11) and a lower pin rod (14); wherein, the upper pin rod (1) is connected with the upper locking cover (4) through a first shaft shoulder screw (2); one end of the connecting rod (6) is provided with a disc structure (19), and the disc structure (19) is fixed through a cavity between the upper lock cover (4) and the lower lock cover (9); the connecting rod (11) is connected with the connecting rod (6) through threads; the connecting rod is connected with the lower pin rod through a second shoulder screw (12), so that the connecting rod and the lower pin rod can rotate relatively along the second shoulder screw (12). The invention has the characteristics of convenient length adjustment, convenient installation, obvious weight reduction effect and good bearing capacity.
Description
Technical Field
The invention belongs to the technical field of aircraft emergency power systems, and particularly relates to a cabin door linkage mechanism of a ram air turbine system.
Background
Ram air turbine systems (RAT for short) are mainly used in aircraft emergency power systems to provide emergency energy for aircraft. The RAT is typically recovered in the RAT cabin in a standby state. When the airplane is in an emergency state, the RAT is unfolded through the retraction jack, the turbine component is released into the air flow, and the stamping energy of the air flow is converted into emergency hydraulic energy/electric energy for emergency use of the airplane.
At present, the domestic RAT adopts a door link mechanism with adjustable length invented by patent (issued bulletin number: CN 204452916U) to realize the linkage function of the RAT and the door. However, the cabin door connecting rod mechanism designed by the invention has a complex structure, the structural external dimension of the connecting rod main body part is larger, the weight of the connecting rod mechanism is larger, and the tensile load born by the connecting rod mechanism is smaller.
Disclosure of Invention
The purpose of the invention is that: a ram air turbine system door linkage is provided. The invention has the characteristics of convenient length adjustment, convenient installation, obvious weight reduction effect and good bearing capacity.
The technical scheme of the invention is as follows: a cabin door linkage mechanism of a ram air turbine system comprises an upper pin rod, an upper lock cover, a lower lock cover, a connecting rod and a lower pin rod; the upper pin rod is connected with the upper lock cover through a first shaft shoulder screw; one end of the connecting rod is provided with a disc structure, and the disc structure is fixed through a cavity between the upper lock cover and the lower lock cover; the connecting rod is connected with the connecting rod through threads; the connecting rod is connected with the lower pin rod through a second shoulder screw, so that the connecting rod and the lower pin rod can relatively rotate along the second shoulder screw.
In the cabin door linkage mechanism of the ram air turbine system, one end of the connecting rod is provided with the disc structure, and after the upper lock cover and the lower lock cover are relatively fixed, a cylindrical cavity is formed inside; after assembly, the disc structure is limited by the cylindrical cavity, so that the axial movement of the connecting rod is limited, and the connecting rod can be ensured to axially rotate.
In the cabin door linkage mechanism of the ram air turbine system, the first connecting rod bushing and the second connecting rod bushing are respectively arranged between the disc structure and the upper lock cover and between the disc structure and the lower lock cover, and are used for reducing friction force between the connecting rod and the upper lock cover and between the connecting rod and the lower lock cover.
In the cabin door linkage mechanism of the ram air turbine system, in order to ensure the axial rotation stability of the connecting rod, a cylindrical boss is arranged on the outer side of the connecting rod disc structure and is supported in the first connecting rod bushing.
In the cabin door linkage mechanism of the ram air turbine system, the connecting rods are connected with the connecting rods through threads, and the length of the cabin door linkage mechanism is adjusted by adjusting the screwing length of the threads between the connecting rods.
In the cabin door linkage mechanism of the ram air turbine system, the shoulder screws are fixed by self-locking nuts, so that the connection reliability is ensured.
In the cabin door linkage mechanism of the ram air turbine system, the upper pin rod and the lower pin rod are respectively provided with the first screw bushing and the second screw bushing, and the first screw bushing and the second screw bushing are used for reducing friction force among the upper pin rod, the lower pin rod and the shoulder screw.
In the ram air turbine system door linkage described above, the door linkage can also be used for the linkage of landing gear doors.
In the cabin door linkage mechanism of the ram air turbine system, the lining used by the cabin door linkage mechanism is an antifriction lining.
The beneficial effects of the invention are as follows: 1) The cabin door linkage mechanism of the ram air turbine system designed by the invention can realize the linkage between the RAT and the cabin door of the RAT; 2) The length of the cabin door linkage mechanism of the ram air turbine system is adjustable within a certain range so as to be convenient for adapting to the installation requirement on a machine; 3) The cabin door linkage mechanism of the ram air turbine system designed by the invention can greatly reduce the diameter of the connecting rod, and has the characteristics of small outline dimension and weight; 3) The cabin door linkage mechanism of the ram air turbine system is provided with the bushings with lubrication function, so that the movement flexibility of the cabin door linkage mechanism is ensured; 4) The cabin door linkage mechanism of the ram air turbine system designed by the invention can be assembled with large-size bushings, so that the capability of the mechanism for bearing axial load is improved; 5) Compared with the traditional cabin door connecting rod, the diameter of the connecting rod designed by the invention can be reduced by 20-30% under the same load condition. The total weight of the cabin door linkage mechanism can be reduced by more than 10-15% compared with the weight of the transmission cabin door linkage mechanism under the influence of the weight of the connecting rod; 6) Compared with the traditional cabin door linkage mechanism, the axial bearing capacity of the cabin door linkage mechanism designed by the invention can be improved by more than 20-30% under the same weight.
Drawings
FIG. 1 is an exterior view of a ram air turbine system door linkage of the present invention;
FIG. 2 is an exploded view of the ram air turbine system door linkage of the present invention;
fig. 3 is a partial cross-sectional view of a ram air turbine system door linkage.
Reference numerals: the novel lock comprises a 1-upper pin rod, a 2-first shaft shoulder screw, a 3-first screw bush, a 4-upper lock cover, a 5-first connecting rod bush, a 6-connecting rod, a 7-stop block, an 8-second connecting rod bush, a 9-lower lock cover, a 10-stop nut, a 11-connecting rod, a 12-second shaft shoulder screw, a 13-second screw bush, a 14-lower pin rod, a 15-second self-locking nut, a 16-third self-locking nut, a 17-screw, a 18-first self-locking nut and a 19-disc structure.
Detailed Description
The invention is further illustrated by the following figures and examples, which are not intended to be limiting.
Example 1. A cabin door linkage mechanism of a ram air turbine system is composed of an upper pin rod, an upper lock cover, a first connecting rod bushing, a second connecting rod bushing, a lower lock cover, a connecting rod, a lower pin rod and the like as shown in figures 1-3. The upper pin rod is connected with the RAT, the lower pin rod is connected with the aircraft RAT cabin door, and the upper pin rod and the lower pin rod can rotate around respective axes after being arranged in the RAT and the cabin door. The upper lock cover and the lower lock cover are fixed by screws, the connecting rod is arranged between the upper lock cover and the lower lock cover by a disc-shaped structure at the end part of the connecting rod, the upper lock cover and the lower lock cover limit the axial movement of the connecting rod by the disc-shaped structure of the connecting rod, and meanwhile, the connecting rod can be ensured to rotate around the axis of the lock cover. The connecting rod is connected with the connecting rod through a threaded structure, and the length of the cabin door linkage mechanism can be adjusted by adjusting the threaded length of the connecting rod screwed into the connecting rod. The upper connecting rod is connected with the upper locking cover, and the connecting rod is connected with the lower pin rod through a shoulder screw, and each part can axially rotate around the shoulder screw.
The upper pin rod is installed in the RAT installation hole and is axially fixed through a nut, and after the installation, the upper pin rod can rotate around the axis of the upper pin rod.
The upper pin rod is connected with the upper locking cover through a shaft shoulder screw, and the upper pin rod and the upper locking cover can rotate around the shaft shoulder screw.
In order to reduce friction force between the shoulder screw and the upper lock cover, a bushing with antifriction function is arranged at the upper lock cover.
The upper lock cover is connected with the lower lock cover through a screw and a nut. The connecting rod is fixed between the upper lock cover and the lower lock cover through a disc-shaped structure at one end of the connecting rod. In order to reduce the friction force between the connecting rod and the lock cover, a first connecting rod bushing with antifriction function is arranged between the upper lock cover and the connecting rod, and a second connecting rod bushing with antifriction function is arranged between the lower lock cover and the connecting rod.
The two lock covers limit the axial movement of the connecting rod through the disc-shaped structure of the connecting rod, and the connecting rod can be ensured to rotate around the axis of the lock covers. In order to increase the rotation stability of the connecting rod in the lock pin cover, the upper end of the connecting rod disc-shaped structure is provided with a cylindrical boss and is supported in a corresponding hole structure of the first connecting rod bushing.
The connecting rod is connected with the connecting rod through threads, and the function that the length of the cabin door linkage mechanism is adjustable in a certain range is realized by adjusting the screwing length of the threads.
In order to increase the reliability of threaded connection between the connecting rod and the connecting rod, a nut and a nut stop block are arranged at the connecting rod, and after the threaded screwing length is adjusted, a fuse is used for fixing between the connecting rod and the nut stop block.
The connecting rod and the lower pin rod are fixed through a shoulder screw, the connecting rod and the lower pin rod can rotate around the shoulder screw,
in order to reduce the friction force between the extension rod and the shoulder screw, an antifriction bushing is arranged at the extension rod.
The lower pin rod is installed in the installation hole of the RAT cabin door and is axially fixed through a nut, and after the lower pin rod is installed, the lower pin rod can rotate around the axis of the lower pin rod.
Example 2. The cabin door linkage mechanism of the ram air turbine system is composed of an upper pin rod 1, an upper lock cover 4, a lower lock cover 9, a connecting rod 6, a connecting rod 11, a lower pin rod 14 and the like as shown in figures 1-3.
The upper pin rod 1 is connected with the upper lock cover 4 through the first shaft shoulder screw 2 and the first self-locking nut 18, and in order to reduce friction between the shaft shoulder screw 2 and the upper lock cover 4, two first screw bushings 3 with antifriction effect are assembled in the mounting hole of the upper lock cover 4, and the upper pin rod 1 and the upper lock cover 4 can rotate around the first shaft shoulder screw 2.
Referring to fig. 3, a door linkage mechanism is partially cut-away, one end of a connecting rod 6 is provided with a disc-shaped structure 19, and an upper lock cover 4 and a lower lock cover 9 are provided with hole structures. When assembled, the first connecting rod bushing 5 is installed in the corresponding hole of the upper lock cover 4, and the second connecting rod bushing 8 is installed in the corresponding hole of the lower lock cover 9. The connecting rod 6 is inserted into the second connecting rod bushing hole 8, the disc-shaped structure 19 of the connecting rod 6 is attached to the second connecting rod bushing 8, and finally, the upper lock cover 4 and the lower lock cover 9 are fixed through the screw 17 and the third self-locking nut 16. This structure can realize the axial rotation of the connecting rod 6 on the upper lock cover 4, and at the same time, the axial movement of the connecting rod 6 is limited. A cylindrical boss structure is arranged on the outer side of the disc structure 19 of the connecting rod 6 and is matched with the first connecting rod bushing 5, so that the rotating stability of the connecting rod piece 6 is improved.
The connecting rod 11 is connected with the connecting rod 6 through threads, and the overall length of the cabin door linkage mechanism is adjusted by adjusting the screwing length of the threads. In order to increase the reliability of the threaded connection of the connecting rod 11 and the connecting rod 6, an axial groove structure is arranged on the connecting rod 6 for installing the stop block 7. After the length of the cabin door linkage mechanism is adjusted, the stop nut 10 is rotated to be attached to the end face of the connecting rod 11, and the stop block 7 and the connecting rod 11 are fixed by a fuse, so that the phenomenon of loosening of threaded connection of the connecting rod 11 is prevented.
The connecting rod 11 is connected with the lower pin rod 14 through a second shoulder screw 12, and in order to reduce friction between the connecting rod 11 and the second shoulder screw 12, two second screw bushings 13 with antifriction function are assembled at the mounting hole of the connecting rod 11, and the connecting rod 11 and the lower pin rod 14 can rotate around the second shoulder screw 12.
The cabin door linkage mechanism of the ram air turbine system designed by the invention can realize the linkage function of the RAT and the cabin door and adjust the length of the cabin door linkage mechanism in a certain range.
Example 3. A cabin door linkage mechanism of a ram air turbine system, which is shown in figures 1-3, and comprises an upper pin rod 1, an upper lock cover 4, a lower lock cover 9, a connecting rod 6, a connecting rod 11 and a lower pin rod 14; wherein, the upper pin rod 1 is connected with the upper lock cover 4 through a first shoulder screw 2; one end of the connecting rod 6 is provided with a disc structure 19, and the disc structure 19 is fixed through a cavity between the upper lock cover 4 and the lower lock cover 9; the connecting rod 11 is connected with the connecting rod 6 through threads; the connecting rod is connected with the lower pin rod through the second shoulder screw 12, so that the connecting rod and the lower pin rod can relatively rotate along the second shoulder screw 12.
One end of the connecting rod 6 is provided with a disc structure 19, and after the upper lock cover 4 and the lower lock cover 9 are relatively fixed, a cylindrical cavity is formed inside; after assembly, the disc structure 19 is limited by the cylindrical cavity, so that the axial movement of the connecting rod 6 is limited, and the axial rotation of the connecting rod 6 is ensured.
The disc structure 19 is respectively provided with a first connecting rod bushing 5 and a second connecting rod bushing 8 between the upper locking cover 4 and the lower locking cover 9, and is used for reducing friction force between the connecting rod 6 and the upper locking cover 4 and the lower locking cover 9.
In order to ensure the stability of the axial rotation of the connecting rod 6, a cylindrical boss is arranged on the outer side of the disc structure 19 of the connecting rod 6 and is supported in the first connecting rod bushing 5.
The connecting rod 11 is in threaded connection with the connecting rod 6, and the length of the cabin door linkage mechanism is adjusted by adjusting the threaded screwing length between the connecting rod 11 and the connecting rod 6.
The shoulder screws are all fixed by self-locking nuts, so that connection reliability is guaranteed.
The upper pin rod 1 and the lower pin rod 14 are respectively provided with a first screw bushing 3 and a second screw bushing 13 for reducing friction force between the upper pin rod, the lower pin rod and the shaft shoulder screw.
The door linkage can also be used for the linkage of landing gear doors.
The bush adopted by the cabin door linkage mechanism is an antifriction bush.
Claims (8)
1. The cabin door linkage mechanism of the ram air turbine system is characterized by comprising an upper pin rod (1), an upper lock cover (4), a lower lock cover (9), a connecting rod (6), a connecting rod (11) and a lower pin rod (14); wherein, the upper pin rod (1) is connected with the upper locking cover (4) through a first shaft shoulder screw (2); one end of the connecting rod (6) is provided with a disc structure (19), and the disc structure (19) is fixed through a cavity between the upper lock cover (4) and the lower lock cover (9); the connecting rod (11) is connected with the connecting rod (6) through threads; the connecting rod is connected with the lower pin rod through a second shoulder screw (12), so that the connecting rod and the lower pin rod can relatively rotate along the second shoulder screw (12); the outer side of the disc structure (19) of the connecting rod (6) is provided with a cylindrical boss and is supported in the first connecting rod bushing (5).
2. The ram air turbine system cabin door linkage mechanism according to claim 1, wherein one end of the connecting rod (6) is provided with a disc structure (19), and after the upper lock cover (4) and the lower lock cover (9) are relatively fixed, a cylindrical cavity is formed inside; after assembly, the disc structure (19) is limited by the cylindrical cavity, so that the axial movement of the connecting rod (6) is limited, and the connecting rod (6) can be ensured to axially rotate.
3. Ram air turbine system hatch door linkage according to claim 1, characterized in that a first link bushing (5) and a second link bushing (8) are arranged between the disc structure (19) and the upper lock cover (4), the lower lock cover (9), respectively, for reducing friction between the links (6) and the upper lock cover (4), the lower lock cover (9).
4. The cabin door linkage mechanism of the ram air turbine system according to claim 1, wherein the connecting rod (11) and the connecting rod (6) are connected through threads, and the length of the cabin door linkage mechanism is adjusted by adjusting the screwing length between the connecting rod (11) and the connecting rod (6).
5. The ram air turbine system door linkage as claimed in claim 1, wherein the shoulder screws are secured with self-locking nuts, ensuring connection reliability.
6. Ram air turbine system hatch linkage according to claim 1, characterized in that the upper pin (1) and the lower pin (14) are provided with a first screw bushing (3) and a second screw bushing (13), respectively, for reducing friction between the upper pin, the lower pin and the shoulder screw.
7. The ram air turbine system door linkage of claim 1, wherein the door linkage is further operable for the linkage of landing gear doors.
8. The ram air turbine system hatch door linkage according to claim 1, wherein the bushings employed by the hatch door linkage are antifriction bushings.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111662661.7A CN114320049B (en) | 2021-12-30 | 2021-12-30 | Cabin door linkage mechanism of ram air turbine system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111662661.7A CN114320049B (en) | 2021-12-30 | 2021-12-30 | Cabin door linkage mechanism of ram air turbine system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114320049A CN114320049A (en) | 2022-04-12 |
| CN114320049B true CN114320049B (en) | 2023-11-07 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111662661.7A Active CN114320049B (en) | 2021-12-30 | 2021-12-30 | Cabin door linkage mechanism of ram air turbine system |
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| CN (1) | CN114320049B (en) |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20150167702A1 (en) * | 2013-12-12 | 2015-06-18 | Triumph Actuation Systems - Yakima, LLC | Actuator assemblies |
| CN204452916U (en) * | 2014-12-10 | 2015-07-08 | 中国航空工业集团公司金城南京机电液压工程研究中心 | A kind of length-adjustable hatch door connecting rod mechanism |
| US10661913B2 (en) * | 2018-04-30 | 2020-05-26 | Hamilton Sundstrand Corporation | Hybrid ram air turbine with in-line hydraulic pump and generator |
| CN110905608B (en) * | 2019-11-19 | 2022-05-13 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Ram air turbine system structure |
| CN111003198A (en) * | 2019-12-27 | 2020-04-14 | 中国航空工业集团公司西安飞机设计研究所 | Airplane cabin door connecting rod force fixing method and device |
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2021
- 2021-12-30 CN CN202111662661.7A patent/CN114320049B/en active Active
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| CN114320049A (en) | 2022-04-12 |
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