CN111470034B - Linkage mechanism of follow-up switch of landing gear cabin door of airplane - Google Patents
Linkage mechanism of follow-up switch of landing gear cabin door of airplane Download PDFInfo
- Publication number
- CN111470034B CN111470034B CN202010353543.7A CN202010353543A CN111470034B CN 111470034 B CN111470034 B CN 111470034B CN 202010353543 A CN202010353543 A CN 202010353543A CN 111470034 B CN111470034 B CN 111470034B
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- CN
- China
- Prior art keywords
- rocker arm
- linkage
- movably connected
- cabin door
- landing gear
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/18—Operating mechanisms
- B64C25/22—Operating mechanisms fluid
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/16—Fairings movable in conjunction with undercarriage elements
Abstract
The invention discloses a linkage mechanism of a cabin door follow-up switch of an aircraft landing gear, which comprises a cabin door linkage mechanism, wherein a first rocker arm and a second rocker arm are movably connected, the right end of the first rocker arm is movably connected with a rack, the first rocker arm is movably connected with the top of a hydraulic action cylinder, and the lower end of a piston rod of the hydraulic action cylinder is movably connected with the rack; the linkage disc is sleeved outside the rotating shaft through a spline, the rotating shaft is installed inside the installation ring, the left end of the rocker arm II is movably connected with the top of the undercarriage damping cylinder, a rolling pin groove for a rolling pin to penetrate through is formed in the driven disc, the bottom of the connecting rod I is movably connected with a connecting rod II, the lower end of the connecting rod II is movably connected with the cabin door linkage shaft, and the cabin door linkage shaft is movably installed on the cabin door; according to the invention, when the undercarriage is completely retracted, the cabin door of the undercarriage is just completely closed, so that the cabin door is automatically closed in a linkage manner when the undercarriage is retracted, and the cabin door of the undercarriage is opened and closed in a linkage manner in the retracting process of the undercarriage.
Description
Technical Field
The invention relates to the technical field of aircraft accessories, in particular to a linkage mechanism of a follow-up switch of a door of an aircraft landing gear.
Background
The main task of the landing gear of the airplane is to meet the functions of running, moving, parking and the like of the airplane. In the flight process of the airplane, most of the undercarriages of the airplane are collected in the airplane body, most of the undercarriages of the airplane are provided with undercarriages cabin doors, the cabin doors are closed after the undercarriages are collected, the airplane has excellent pneumatic performance during flight, and the cabin doors of the undercarriages of the existing large civil aviation transport airplane are closed and opened by adopting a hydraulic system. The landing and landing doors of some small airplanes depend on mechanical linkage when the landing gear is retracted and extended to control the closing and opening of the doors.
The invention designs a lifting cabin door opening and closing linkage mechanism, which realizes linkage opening and closing of a cabin door of a landing gear in the process of retraction and extension of a landing gear.
Disclosure of Invention
The invention aims to provide a linkage mechanism of a follow-up switch of a door of an aircraft landing gear, which solves the problems in the prior art.
In order to achieve the purpose, the invention adopts the following technical scheme:
the linkage mechanism of the servo switch of the cabin door of the aircraft landing gear comprises a cabin door linkage mechanism, wherein the cabin door linkage mechanism comprises a rocker arm structure and a linkage disk, the rocker arm structure sequentially comprises a first rocker arm and a second rocker arm from right to left, the first rocker arm and the second rocker arm are movably connected, the right end of the first rocker arm is movably connected with a rack, the first rocker arm is movably connected with the top of a hydraulic action cylinder, and the lower end of a piston rod of the hydraulic action cylinder is movably connected with the rack;
the linkage disc passes through the spline housing and adorns in the outside of pivot, the inside at the installation ring is installed in the pivot, the welding of installation ring is in the frame, pivot and undercarriage damper cylinder fixed connection, the left end of rocking arm two with the top swing joint of undercarriage damper cylinder keeps away from one side of linkage disc the outside movable sleeve of pivot is equipped with the driven plate, the welding has the roll round pin on the base member of linkage disc, set up the confession on the driven plate the roll cotter way that the roll round pin passed, the linkage disc with be equipped with the connecting rod between the driven plate, the bottom left side movable mounting of driven plate has connecting rod one, connecting rod one bottom swing joint has connecting rod two, the lower extreme and the hatch door universal driving shaft swing joint of connecting rod two, hatch door universal driving shaft movable mounting is on the hatch door.
By adopting the technical scheme: when the hydraulic action cylinder contracts, the first rocker arm and the first rocker arm contract downwards, the first rocker arm drives the undercarriage damping cylinder to rotate clockwise around the rotating shaft, so that the whole undercarriage is retracted, in the process of retracting the undercarriage, when the rotating shaft on the undercarriage damping cylinder rotates, the linkage disc also rotates clockwise along with the rotating shaft, when the undercarriage is retracted to a certain position, the rolling pin on the linkage disc just moves to the lowest part of the rolling pin groove on the driven disc, so that the driven disc is driven to rotate, and the driven disc starts to move clockwise; the driven disc rotates clockwise, the cabin door linkage shaft is driven to rotate through the first connecting rod and the second connecting rod, the cabin door linkage shaft rotates, the cabin door is driven to rotate, when the undercarriage is completely folded, the cabin door of the undercarriage is just completely closed, automatic linkage closing of the cabin door when the undercarriage is folded is achieved, and the landing frame is capable of linking the cabin door of the undercarriage in the folding and unfolding processes.
Preferably, the first rocker arm comprises a first vertical plate and a second vertical plate from front to back in sequence, the right end of the second rocker arm is inserted into the left side of the first rocker arm, the connection part of the first rocker arm and the second rocker arm is movably connected through a bolt, and the middle of the bolt is provided with a smooth section.
By adopting the technical scheme: the connecting part of the first rocker arm and the second rocker arm is movably connected through a bolt, so that the first rocker arm and the second rocker arm can be conveniently disassembled and assembled, and the middle part of the bolt is a smooth section, so that the first rocker arm and the second rocker arm can rotate more smoothly.
Preferably, a protrusion is integrally formed on the outer wall of the rack at the joint of the first rocker arm, the protrusion is inserted into the first rocker arm, and the first rocker arm and the protrusion are movably connected through a bolt.
By adopting the technical scheme: the protrusion is inserted into the first rocker arm, and the first rocker arm and the protrusion are movably connected through the bolt, so that the first rocker arm can rotate more smoothly.
Preferably, with the department of meeting of the piston rod of a hydraulic action section of thick bamboo the outer wall welding of frame has splint one, the welding of the piston rod lower extreme of a hydraulic action section of thick bamboo has the rectangular connecting block, the rectangular connecting block inserts the inside of splint one, the rectangular connecting block with pass through bolt swing joint between the splint one.
By adopting the technical scheme: the concrete structure of the joint of the piston rod of the hydraulic action cylinder and the frame is limited.
Preferably, the top of the hydraulic action cylinder is inserted into the rocker arm I, and the rocker arm I is movably connected with the hydraulic action cylinder through a round rod.
By adopting the technical scheme: the first rocker arm is movably connected with the hydraulic action barrel through a round rod, and smooth rotation of the first rocker arm and the hydraulic action barrel is facilitated.
Preferably, a second clamping plate is welded on the right side of the top of the landing gear damping cylinder, the left end of the second rocker arm is inserted into the second clamping plate, and the second rocker arm and the second clamping plate are movably connected through a bolt.
By adopting the technical scheme: due to smooth rotation between the second clamping plate and the landing gear damping cylinder.
Preferably, round holes are formed in the left side of the bottom of the driven disc and in the upper end and the lower end of the first connecting rod and the second connecting rod, the two coincident round holes are movably connected through a bolt, and the cabin door linkage shaft penetrates through the round holes in the bottom of the second connecting rod.
By adopting the technical scheme: and the smooth rotation among the first connecting rod, the driven disc and the second connecting rod is facilitated.
Preferably, the body of the cabin door is provided with a body coupling hole and a linkage shaft hole for the cabin door linkage shaft to pass through.
By adopting the technical scheme: the installation of the cabin door universal driving shaft is convenient.
Compared with the prior art, the linkage mechanism of the follow-up switch of the cabin door of the aircraft landing gear provided by the invention comprises the following components:
when the undercarriage is completely retracted, the cabin door of the undercarriage is just completely closed, the cabin door is automatically linked and closed when the undercarriage is retracted, and the cabin door of the undercarriage is linked and opened in the retracting process.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic view of the linkage disk of the hatch opening and closing linkage of the present invention;
FIG. 3 is a schematic view of the construction of the bolt of the present invention;
figure 4 is a right side view of the door of the present invention.
In the figure: 1. a frame; 101. installing a circular ring; 102. a protrusion; 103. a first clamping plate; 2. a first rocker arm; 21. a first vertical plate; 22. a second vertical plate; 3. a second rocker arm; 4. a landing gear shock tube; 41. a second clamping plate; 5. a hydraulic action cylinder; 51. a rectangular connecting block; 6. a rotating shaft; 7. a linkage disk; 71. a roll pin; 8. a driven plate; 81. a rolling pin slot; 82. a connecting rod; 9. a bolt; 10. a first connecting rod; 11. a second connecting rod; 12. a hatch linkage shaft; 13. a cabin door; 131. a fuselage coupling aperture; 132. a linkage shaft hole; 14. a bolt; 141. and (7) a smooth section.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail below with reference to specific embodiments and the accompanying drawings. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
Example 1
As shown in fig. 1 and 2, a linkage mechanism of a servo switch of a cabin door of an aircraft landing gear comprises a cabin door linkage mechanism, wherein the cabin door linkage mechanism comprises a rocker arm structure and a linkage disc 7, the rocker arm structure sequentially comprises a rocker arm I2 and a rocker arm II 3 from right to left, the rocker arm I2 is movably connected with the rocker arm II 3, the right end of the rocker arm I2 is movably connected with a rack 1, the rocker arm I2 is movably connected with the top of a hydraulic action barrel 5, and the lower end of a piston rod of the hydraulic action barrel 5 is movably connected with the rack 1;
the linkage disc 7 is sleeved outside the rotating shaft 6 through a spline, the rotating shaft 6 is installed inside the installation ring 101, the installation ring 101 is welded on the rack 1, the rotating shaft 6 is fixedly connected with the landing gear damping cylinder 4, the left end of the rocker arm II 3 is movably connected with the top of the landing gear damping cylinder 4, the driven disc 8 is movably sleeved outside the rotating shaft 6 on one side far away from the linkage disc 7, a rolling pin 71 is welded on a base body of the linkage disc 7, a rolling pin groove 81 for the rolling pin 71 to penetrate is formed in the driven disc 8, a connecting rod 82 is arranged between the linkage disc 7 and the driven disc 8, a first connecting rod 10 is movably installed on the left side of the bottom of the driven disc 8, a second connecting rod 11 is movably connected to the bottom of the first connecting rod 10, the lower end of the second connecting rod 11 is movably connected with the linkage shaft 12, and the cabin door linkage shaft 12 is movably installed on the cabin door 13.
By adopting the technical scheme: when the hydraulic action cylinder 5 contracts, the rocker arm I2 and the rocker arm II 3 contract downwards, the rocker arm I2 drives the landing gear damping cylinder 4 to rotate clockwise around the rotating shaft 6, so that the whole landing gear is retracted, when the rotating shaft 6 on the landing gear damping cylinder 4 rotates in the retraction process of the landing gear, the linkage disc 7 also rotates clockwise along with the rotating shaft 6, and when the landing gear is retracted to a certain position, the rolling pin 71 on the linkage disc 7 just moves to the lowest part of the rolling pin groove 81 on the driven disc 8, so that the driven disc 8 is driven to rotate, and the driven disc 8 starts to move clockwise; the driven disc 8 rotates clockwise, the cabin door linkage shaft 12 is driven to rotate through the first connecting rod 10 and the second connecting rod 11, the cabin door linkage shaft 12 rotates to drive the cabin door 13 to rotate, when the undercarriage is completely retracted, the cabin door 13 of the undercarriage is just completely closed, the automatic linkage closing of the cabin door 13 when the undercarriage is retracted is realized, and the linkage switch of the undercarriage cabin door 13 in the retracting process of the undercarriage is realized.
As shown in fig. 1 and 3, the rocker arm i 2 sequentially comprises a first vertical plate 21 and a second vertical plate 22 from front to back, the right end of the rocker arm i 3 is inserted into the left side of the rocker arm i 2, the joint of the rocker arm i 2 and the rocker arm i 3 is movably connected through a bolt 14, and the middle part of the bolt 14 is provided with a smooth section 141.
By adopting the technical scheme: the first rocker arm 2 and the second rocker arm 3 are movably connected through the bolt 14, so that the first rocker arm 2 and the second rocker arm 3 are conveniently dismounted and mounted, and the bolt 14 is arranged in the middle of the smooth section 141, so that the first rocker arm 2 and the second rocker arm 3 can rotate more smoothly.
As shown in fig. 1 and 3, a protrusion 102 is integrally formed on the outer wall of the frame 1 at the joint with the first rocker arm 2, the protrusion 102 is inserted into the first rocker arm 2, and the first rocker arm 2 and the protrusion 102 are movably connected through a bolt 14.
By adopting the technical scheme: the protrusion 102 is inserted into the rocker arm 2, and the rocker arm 2 and the protrusion 102 are movably connected through the bolt 14, so that the rotation of the rocker arm 2 is smoother.
As shown in fig. 1 and 3, a first clamping plate 103 is welded on the outer wall of the frame 1 at the joint of the first clamping plate and the piston rod of the hydraulic action cylinder 5, a rectangular connecting block 51 is welded at the lower end of the piston rod of the hydraulic action cylinder 5, the rectangular connecting block 51 is inserted into the first clamping plate 103, and the rectangular connecting block 51 and the first clamping plate 103 are movably connected through a bolt 14.
By adopting the technical scheme: the concrete structure of the joint of the piston rod of the hydraulic action cylinder 5 and the frame 1 is defined.
As shown in figures 1 and 3, the top of the hydraulic action cylinder 5 is inserted into the rocker arm I2, and the rocker arm I2 and the hydraulic action cylinder 5 are movably connected through a round rod.
By adopting the technical scheme: the first rocker arm 2 and the hydraulic action cylinder 5 are movably connected through a round rod, and smooth rotation of the first rocker arm 2 and the hydraulic action cylinder 5 is facilitated.
As shown in fig. 1 and 3, a second clamping plate 41 is welded on the right side of the top of the landing gear shock-absorbing cylinder 4, the left end of the second rocker arm 3 is inserted into the second clamping plate 41, and the second rocker arm 3 and the second clamping plate 41 are movably connected through a bolt 14.
By adopting the technical scheme: due to the smooth rotation between the second clamping plate 41 and the landing gear shock tube 4.
As shown in fig. 1 and 2, round holes are respectively formed in the left side of the bottom of the driven disc 8 and the upper and lower ends of the first connecting rod 10 and the second connecting rod 11, the two superposed round holes are movably connected through a bolt 9, and the cabin door linkage shaft 12 penetrates through the round hole in the bottom of the second connecting rod 11.
By adopting the technical scheme: and smooth rotation between the first connecting rod 10 and the driven disc 8 and the second connecting rod 11 is facilitated.
As shown in fig. 1 and 4, a body coupling hole 131 and a linkage shaft hole 132 for the door linkage shaft 12 to pass through are formed on the base of the door 13.
By adopting the technical scheme: the installation of the cabin door linkage shaft 12 is facilitated through the linkage shaft hole 132, the movable connection between the cabin door 13 and the rack 1 is facilitated through the body connecting hole 131, and the cabin door linkage shaft 12 is driven to drive the cabin door 13 to move when the cabin door linkage shaft 12 moves.
The structure principle is as follows: when the hydraulic action cylinder 5 contracts, the rocker arm I2 and the rocker arm II 3 contract downwards, the rocker arm I2 drives the landing gear damping cylinder 4 to rotate clockwise around the rotating shaft 6, so that the whole landing gear is retracted, when the rotating shaft 6 on the landing gear damping cylinder 4 rotates in the retraction process of the landing gear, the linkage disc 7 also rotates clockwise along with the rotating shaft 6, and when the landing gear is retracted to a certain position, the rolling pin 71 on the linkage disc 7 just moves to the lowest part of the rolling pin groove 81 on the driven disc 8, so that the driven disc 8 is driven to rotate, and the driven disc 8 starts to move clockwise; the driven disc 8 rotates clockwise, the cabin door linkage shaft 12 is driven to rotate through the first connecting rod 10 and the second connecting rod 11, the cabin door linkage shaft 12 rotates to drive the cabin door 13 to rotate, when the undercarriage is completely retracted, the cabin door 13 of the undercarriage is just completely closed, the automatic linkage closing of the cabin door 13 when the undercarriage is retracted is realized, and the linkage switching of the cabin door 13 of the undercarriage in the retracting process is realized;
it should be noted that a torsion spring is mounted on the fixed pivot of the door to the fuselage of the aircraft, and when the door 13 is closed, the door 13 is closed against the action of the spring, and during landing gear lowering, the door automatically opens under the action of the torsion spring as the landing gear is lowered. When the door 13 moves upwards, the door is driven to close by the motion of the driven disc 8, the first connecting rod 10 and the second connecting rod 11 against the action of spring force.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be able to cover the technical scope of the present invention and the equivalent alternatives or modifications according to the technical solution and the inventive concept of the present invention within the technical scope of the present invention.
Claims (7)
1. A linkage mechanism for an aircraft landing gear door follower switch, comprising:
the cabin door linkage mechanism comprises a rocker arm structure and a linkage disc (7), the rocker arm structure sequentially comprises a first rocker arm (2) and a second rocker arm (3) from right to left, the first rocker arm (2) and the second rocker arm (3) are movably connected, the right end of the first rocker arm (2) is movably connected with the rack (1), the first rocker arm (2) is movably connected with the top of the hydraulic action barrel (5), and the lower end of a piston rod of the hydraulic action barrel (5) is movably connected with the rack (1);
the linkage disc (7) is sleeved outside the rotating shaft (6) through a spline, the rotating shaft (6) is installed inside the installation ring (101), the installation ring (101) is welded on the rack (1), the rotating shaft (6) is fixedly connected with the landing gear damping cylinder (4), the left end of the rocker arm II (3) is movably connected with the top of the landing gear damping cylinder (4), one side of the linkage disc (7) is far away from the outer movable sleeve of the rotating shaft (6) is provided with a driven disc (8), a rolling pin (71) is welded on the base body of the linkage disc (7), a rolling pin groove (81) for the rolling pin (71) to pass is formed in the driven disc (8), a connecting rod (82) is arranged between the linkage disc (7) and the driven disc (8), and a first connecting rod (10) is movably installed on the left side of the bottom of the driven disc (8), the bottom of the first connecting rod (10) is movably connected with a second connecting rod (11), the lower end of the second connecting rod (11) is movably connected with a cabin door linkage shaft (12), and the cabin door linkage shaft (12) is movably arranged on a cabin door (13);
round holes are formed in the left side of the bottom of the driven disc (8) and in the upper end and the lower end of the first connecting rod (10) and the second connecting rod (11), the two coincident round holes are movably connected through a bolt (9), and the cabin door linkage shaft (12) penetrates through the round hole in the bottom of the second connecting rod (11).
2. An aircraft landing gear door follower switch linkage according to claim 1, wherein: rocking arm (2) are by preceding first riser (21) and second riser (22) of including in proper order after to, insert the right-hand member of rocking arm two (3) inside the left side of rocking arm one (2), rocking arm one (2) with the department of meeting of rocking arm two (3) is through bolt (14) swing joint, the middle part of bolt (14) is smooth section (141) setting.
3. An aircraft landing gear door follower switch linkage according to claim 2, wherein: the outer wall of the rack (1) at the joint of the rocker arm I (2) is integrally formed with a protrusion (102), the protrusion (102) is inserted into the rocker arm I (2), and the rocker arm I (2) is movably connected with the protrusion (102) through a bolt (14).
4. An aircraft landing gear door follower switch linkage according to claim 2, wherein: with the department of meeting of the piston rod of a hydraulic action section of thick bamboo (5) the outer wall welding of frame (1) has splint one (103), the welding of the piston rod lower extreme of a hydraulic action section of thick bamboo (5) has rectangle connecting block (51), rectangle connecting block (51) insert the inside of splint one (103), rectangle connecting block (51) with pass through bolt (14) swing joint between splint one (103).
5. An aircraft landing gear door follower switch linkage according to claim 2, wherein: the top of the hydraulic action cylinder (5) is inserted into the rocker arm I (2), and the rocker arm I (2) is movably connected with the hydraulic action cylinder (5) through a round rod.
6. An aircraft landing gear door follower switch linkage according to claim 2, wherein: the welding of the top right side of undercarriage damper cylinder (4) has splint two (41), the left end of rocker arm two (3) inserts the inside of splint two (41), rocker arm two (3) with through bolt (14) swing joint between splint two (41).
7. An aircraft landing gear door follower switch linkage according to claim 1, wherein: the basal body of the hatch (13) is provided with a fuselage coupling hole (131) and a linkage shaft hole (132) for the hatch linkage shaft (12) to pass through.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010353543.7A CN111470034B (en) | 2020-04-29 | 2020-04-29 | Linkage mechanism of follow-up switch of landing gear cabin door of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010353543.7A CN111470034B (en) | 2020-04-29 | 2020-04-29 | Linkage mechanism of follow-up switch of landing gear cabin door of airplane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111470034A CN111470034A (en) | 2020-07-31 |
| CN111470034B true CN111470034B (en) | 2021-09-07 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010353543.7A Active CN111470034B (en) | 2020-04-29 | 2020-04-29 | Linkage mechanism of follow-up switch of landing gear cabin door of airplane |
Country Status (1)
| Country | Link |
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| CN (1) | CN111470034B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114248912A (en) * | 2020-09-22 | 2022-03-29 | 海鹰航空通用装备有限责任公司 | Undercarriage folding and unfolding and cabin door linkage mechanism for small-sized fixed wing unmanned aerial vehicle |
| CN112498665B (en) * | 2020-12-04 | 2023-01-13 | 中国航空工业集团公司成都飞机设计研究所 | Undercarriage retracting mechanism |
| CN113602484B (en) * | 2021-08-26 | 2022-08-23 | 中国商用飞机有限责任公司 | Undercarriage retraction system and aircraft comprising same |
| CN114030597B (en) * | 2021-12-17 | 2023-07-21 | 北京北航天宇长鹰无人机科技有限公司 | Landing gear cabin door linkage mechanism, landing gear cabin door linkage system and unmanned aerial vehicle |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2180462A (en) * | 1937-12-16 | 1939-11-21 | Seversky Aircraft Corp | Aircraft structure |
| CN104527972A (en) * | 2014-12-05 | 2015-04-22 | 中国航天空气动力技术研究院 | Unmanned plane undercarriage cabin door retraction-extension servo mechanism |
| CN104724282A (en) * | 2013-12-02 | 2015-06-24 | 埃姆普里萨有限公司 | Emergency Gravity Free-fall Deployment Systems For Retractable Aircraft Landing Gear Assemblies |
| WO2015134182A1 (en) * | 2014-03-07 | 2015-09-11 | Gulfstream Aerospace Corporation | Nose landing gear arrangements including a flexible sheet and methods for making the same |
| CN105056543A (en) * | 2015-08-03 | 2015-11-18 | 金剑 | Five-link nose landing gear |
| CN206968967U (en) * | 2017-06-09 | 2018-02-06 | 蒋旭瑞 | A kind of undercarriage draw off gear |
| CN207889972U (en) * | 2018-02-02 | 2018-09-21 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft door and undercarriage link jack |
| CN110127039A (en) * | 2018-02-02 | 2019-08-16 | 赛峰起落架系统公司 | Has the undercarriage of slotted strut |
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2020
- 2020-04-29 CN CN202010353543.7A patent/CN111470034B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2180462A (en) * | 1937-12-16 | 1939-11-21 | Seversky Aircraft Corp | Aircraft structure |
| CN104724282A (en) * | 2013-12-02 | 2015-06-24 | 埃姆普里萨有限公司 | Emergency Gravity Free-fall Deployment Systems For Retractable Aircraft Landing Gear Assemblies |
| WO2015134182A1 (en) * | 2014-03-07 | 2015-09-11 | Gulfstream Aerospace Corporation | Nose landing gear arrangements including a flexible sheet and methods for making the same |
| CN104527972A (en) * | 2014-12-05 | 2015-04-22 | 中国航天空气动力技术研究院 | Unmanned plane undercarriage cabin door retraction-extension servo mechanism |
| CN105056543A (en) * | 2015-08-03 | 2015-11-18 | 金剑 | Five-link nose landing gear |
| CN206968967U (en) * | 2017-06-09 | 2018-02-06 | 蒋旭瑞 | A kind of undercarriage draw off gear |
| CN207889972U (en) * | 2018-02-02 | 2018-09-21 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft door and undercarriage link jack |
| CN110127039A (en) * | 2018-02-02 | 2019-08-16 | 赛峰起落架系统公司 | Has the undercarriage of slotted strut |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111470034A (en) | 2020-07-31 |
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