CN113753222B - Undercarriage side stay bar mechanism - Google Patents
Undercarriage side stay bar mechanism Download PDFInfo
- Publication number
- CN113753222B CN113753222B CN202111120727.XA CN202111120727A CN113753222B CN 113753222 B CN113753222 B CN 113753222B CN 202111120727 A CN202111120727 A CN 202111120727A CN 113753222 B CN113753222 B CN 113753222B
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- CN
- China
- Prior art keywords
- stay
- stay bar
- hinged
- locking
- landing gear
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- 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
-
- 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
- B64C25/26—Control or locking systems therefor
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Pivots And Pivotal Connections (AREA)
Abstract
The application belongs to the technical field of aircraft design, and particularly relates to an aircraft landing gear side stay bar mechanism, which comprises an upper stay bar and a lower stay bar, wherein the lower stay bar comprises a large end and a small end, the large end is hinged with a landing gear, and the small end is hinged with the upper stay bar; the stay bar locking mechanism comprises an upper locking stay bar, a lower locking stay bar and a spring, wherein the unlocking actuating cylinder is hinged with the lower locking stay bar; the locking stay bar is bent at the position where the landing gear is hinged, and the bending direction faces the tension direction of the spring; the lower lock stay bar is hinged with the small end and 1/4 of the large end close to the small end; the lower lock stay bar is of a hollow four-corner star structure, the hollow four-corner star structure comprises a groove, the unlocking actuating cylinder can be laid in the groove, and the lower lock stay bar is a side stay bar which is high in strength and has a high folding angle, so that the weight and the space of an airplane are saved.
Description
Technical Field
The application belongs to the technical field of aircraft design, and relates to an aircraft landing gear side stay bar mechanism.
Background
The stay bar of aircraft undercarriage is mainly used for fixed support, and the stay bar of integrated receive and release and locking is mostly the great forward supporting mechanism of space demand, and its space that needs is great, and its mechanism is comparatively complicated to weight is big, still has the poor problem of reliability, when the undercarriage needs specific space side stay bar to when needing integrated locking mechanical system, current configuration can not be when satisfying the aircraft high load, and the side stay bar can satisfy and have high folding effect, has good load performance concurrently again.
Disclosure of Invention
In order to solve the problems, the application provides a landing gear side stay mechanism, which comprises a stay mechanism and a stay lock mechanism;
the support rod mechanism comprises an upper support rod and a lower support rod, the lower support rod comprises a large end and a small end, the large end is hinged with the landing gear, and the small end is hinged with the upper support rod;
the stay bar locking mechanism comprises an upper locking stay bar, a lower locking stay bar and a spring, wherein the unlocking actuating cylinder is hinged with the lower locking stay bar;
the locking stay bar is bent by 50-60 degrees at the position where the landing gear is hinged, and the bending direction faces the tension direction of the spring; the lower lock stay bar is hinged with the small end and 1/4 of the large end close to the small end; the lower lock stay bar is of a hollow four-corner star structure, the hollow four-corner star structure comprises a groove, and the unlocking actuator cylinder can be laid in the groove.
Preferably, the distance between the position where the unlocking actuator is hinged with the lower locking stay bar and the position where the unlocking actuator is hinged with the upper locking stay bar is not more than 1/3 of the length of the lower locking stay bar.
Preferably, the upper stay is "Y" shaped, and when the upper stay is rotated about the hinge point to overlap the lower stay, the lower stay partially dips into the "Y" shaped gap of the upper stay.
Preferably, the joint bearings are arranged at the position where the upper stay bar is hinged with the landing gear and the position where the lower stay bar is hinged with the landing gear.
Preferably, the upper stay bar is hinged with the lower stay bar through an upper stay bar connecting shaft and a lower stay bar connecting shaft, the upper stay bar connecting shaft and the lower stay bar connecting shaft are of hollow cylindrical structures, end covers are installed at two ends, and the end covers are installed and connected through a central shaft penetrating through the upper stay bar connecting shaft and the lower stay bar connecting shaft.
Preferably, the boss is arranged at the joint of the locking stay rod and the lower locking stay rod, the boss is provided with a first threaded hole, the corresponding position of the lower locking stay rod is provided with a second threaded hole, the first threaded hole is provided with a first bolt, the second threaded hole is provided with a second bolt, and when the axis of the locking stay rod reaches a preset angle with the axis of the lower locking stay rod, the first bolt and the second bolt mutually interfere to limit the relative movement of the locking stay rod and the lower locking stay rod.
Preferably, when the first bolt and the second bolt interfere with each other, axes of the first bolt and the second bolt are parallel to each other.
Preferably, a height adjustment spacer is installed between the first screw hole or the second screw hole and the first bolt or the second bolt.
Preferably, the width of the hinge spring of the locking stay is gradually increased toward the bending position.
Preferably, the springs are double springs.
The advantages of the application include: the locking mechanism integrating the upper lock and the lower lock is integrated, the side stay bar mechanism of the landing gear of the aircraft can bear larger ground load, the stay bar lock can be mechanically locked, and the lock spring is provided with double backups; the supporting rod joints are all designed with bearings, so that the folding space folding and unfolding can be met in a self-adaptive mode, the side supporting rods are simple in structure, reliable in locking, small in occupied space, light in weight, large in folding and unfolding angle and applicable to large and medium-sized airplanes.
The side stay bar mechanism with the large folding angle can ensure that the folding and the laying positions are locked, and simultaneously, the folding and laying requirements of the large folding space can be met in a self-adaptive mode, and the mechanism is simple and novel and high in reliability.
Drawings
FIG. 1 is a schematic view of the landing gear side stay mechanism of the present application with upper and lower stay connecting shafts;
FIG. 2 is a schematic diagram showing the interference between a first bolt and a second bolt;
FIG. 3 is a perspective view of the upper brace in the shape of a "Y";
FIG. 4 is a schematic view and cross-sectional view of a lower brace;
FIG. 5 is a schematic view of a locking stay;
FIG. 6 is a schematic view of a lower lock stay;
FIG. 7 is a schematic illustration of a landing gear side stay mechanism coupled to a landing gear;
FIG. 8 is a schematic view of the folding of the upper and lower struts;
fig. 9 is a perspective view of a landing gear side stay mechanism.
The device comprises a 1-upper stay bar, a 2-lower stay bar, a 3-upper locking stay bar, a 4-lower locking stay bar, a 5-spring, a 6-upper stay bar connecting shaft, a 7-upper and lower locking stay bar connecting shaft, an 8-unlocking actuating cylinder, a 9-locking stay bar deflection, a 10-stay bar deflection, a 11-upper locking stay bar deflection adjusting bolt, a 12-bonding wire, a 15-strut, a 16-buffer and a 17-safety pin hole.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application become more apparent, the technical solutions in the embodiments of the present application will be described in more detail with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the application. The embodiments described below by referring to the drawings are exemplary and intended to illustrate the present application and should not be construed as limiting the application. All other embodiments, based on the embodiments of the application, which are apparent to those of ordinary skill in the art without inventive faculty, are intended to be within the scope of the application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
The landing gear side strut mechanisms shown in fig. 1, 7, 8 and 9 include a strut mechanism and a strut lock mechanism;
the support rod mechanism comprises an upper support rod 1 and a lower support rod 2, wherein the lower support rod 2 comprises a large end and a small end, the large end is hinged with the landing gear, and the small end is hinged with the upper support rod 1;
the stay bar locking mechanism comprises an upper locking stay bar 3, a lower locking stay bar 4 and a spring 5, an unlocking actuating cylinder 8, wherein the upper locking stay bar 3 is hinged with the lower locking stay bar 4, the lower locking stay bar 4 is hinged near a small end, the spring 5 is hinged near a large end, the spring 5 is hinged with the upper locking stay bar 3, the locking actuating cylinder 8 is hinged between the lower stay bar 2 and the lower locking stay bar 4, and the middle part of the upper locking stay bar 3 is hinged with the undercarriage; the mechanism keeps a locking state through the tension of a spring;
the locking stay bar 3 is hinged with the landing gear and is provided with a bending of 60 degrees, the bending direction faces to the tension direction of the spring, and the bending and the connecting point of the locking stay bar 3 and the landing gear form a better lever mechanism, so that the elastic performance of the spring still enables the locking stay bar 3 and the locking stay bar to be in an interference locking state under the condition of smaller spring, and the bending can enable mechanical stress to be uniform and avoid damage to the connecting point of the locking stay bar and the spring due to local strong stress in the use process of the oversized tension of the spring; the lower lock stay bar 4 is hinged at the position, 1/4 of the small end and the large end, close to the small end in the actual use process, the acting force of the lower lock stay bar 4 on the small end is larger, but the stroke of the small end is correspondingly reduced, and the stress of the small end exceeds the required stress through calculation, so that a part of the stress can be sacrificed to obtain a larger folding angle, which is a better choice;
the lower lock stay bar 4 is hollow four-corner star structure, hollow four-corner star structure includes the recess, unblanks the actuator tube 8 and can lie in the recess, unblanks the position of actuator tube 8 and is in down between lock stay bar 4 and the lower stay bar 2 generally, and in the folding in-process of lower lock stay bar 4 and lower stay bar 2, unblank the actuator tube body and can hinder folding angle, in order to avoid this kind of circumstances, design into four-corner star structure with lower stay bar as shown in fig. 4, the structure cross section is approximate four-corner star shape, the structure has better bending resistance ability, can alleviate the whole weight of lower stay bar simultaneously, and lower stay bar has four edges in addition, has a recess between every two edges, the recess can hold the actuator tube of unblanking when folding, can reduce the influence of actuator tube to minimum when the mechanism folding angle grow.
In some embodiments, if necessary, limited to the problem of unlocking cylinder type, the travel of the unlocking cylinder cannot support the unlocking cylinder 8 linked at the end point of the lower lock stay, in order to maintain a better force and reduce interference of the unlocking cylinder with the lower lock stay 4, the distance between the position where the unlocking cylinder 8 articulates the lower lock stay 4 and the position where the upper lock stay 3 articulates the lower lock stay 4 is not more than 1/3 of the length of the lower lock stay 4.
In some embodiments, the upper brace bar 1 is in a shape of "Y" as shown in fig. 3, when the upper brace bar 1 rotates around the hinge point to overlap with the lower brace bar 2, the lower brace bar 2 is partially immersed in the gap of the "Y" shape of the upper brace bar 1, and in addition, in order to ensure better accommodation performance, the two support arms of the "Y" are in a structure that the ports are parallel first, and the two support arms are bent at a large angle near the fork.
In some possible embodiments, the upper brace 1 is hinged with the landing gear, and the lower brace 2 is hinged with the landing gear, and joint bearings are arranged at the landing gear, so that the joint bearings can enable the components connected with the joint bearings to have rotational degrees of freedom in other directions under the condition of low-speed use besides meeting the basic functions of the bearings.
In some embodiments, the upper stay bar 1 is hinged with the lower stay bar 2 through an upper stay bar connecting shaft 6, the upper stay bar connecting shaft 6 and the lower stay bar connecting shaft 6 are of hollow cylindrical structures, and end covers are mounted at two ends and are connected through a central shaft penetrating through the upper stay bar connecting shaft 6 and the lower stay bar connecting shaft.
In some embodiments, the locking stay 3 is provided with a boss at the connection with the lower locking stay 4, the boss has a first threaded hole, the corresponding position of the lower locking stay 4 has a second threaded hole, the first threaded hole is provided with a first bolt, the second threaded hole is provided with a second bolt, and when the locking stay 3 reaches a preset angle with the axis of the lower locking stay 4, the first bolt and the second bolt interfere with each other to limit the relative movement of the locking stay 3 and the lower locking stay 4.
In some embodiments, when the first bolt and the second bolt interfere with each other, the axes of the first bolt and the second bolt are parallel to each other, the main function of the first bolt and the second bolt is to form an interference component between the upper lock stay 3 and the lower lock stay 4, when the first bolt and the second bolt contact each other, the two bolts are stressed by compressive stress when the axes of the first bolt and the second bolt are parallel to each other, if the two bolts are stressed by more shearing stress on the same axis, the shearing stress has larger damage to the bolts.
In some embodiments, a height adjusting gasket is installed between the first threaded hole or the second threaded hole and the first bolt or the second bolt, the height of the bolt can be adjusted by the height adjusting gasket, and when the locking stay bar 3 reaches a preset angle with the axis of the lower locking stay bar 4, the deflection of the locking stay bar and the lower locking stay bar can be adjusted, so that different angle adjustments of the lower stay bar and the landing gear are realized.
In some embodiments, the width of the hinge spring 5 of the locking stay 3 becomes larger gradually towards the bending point, the bending point bears higher force, and the larger width is beneficial to realizing higher bearing of force.
In some embodiments, the spring 5 is a double spring, which has a higher safety performance.
The foregoing is merely illustrative of the present application, and the present application is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present application should be included in the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (9)
1. A landing gear side stay mechanism comprising a stay mechanism and a stay lock mechanism;
the support rod mechanism comprises an upper support rod (1) and a lower support rod (2), the lower support rod (2) comprises a large end and a small end, the large end is hinged with the landing gear, and the small end is hinged with the upper support rod (1);
the stay bar locking mechanism comprises an upper locking stay bar (3), a lower locking stay bar (4) and a spring (5), an unlocking actuating cylinder (8), wherein the upper locking stay bar (3) is hinged with the lower locking stay bar (4), the lower locking stay bar (4) is hinged near the small end, the spring (5) is hinged near the big end, the spring (5) is hinged with the upper locking stay bar (3), the unlocking actuating cylinder (8) is hinged between the lower stay bar (2) and the lower locking stay bar (4), and the middle part of the upper locking stay bar (3) is hinged with the landing gear;
the locking support rod (3) is characterized in that the position hinged with the landing gear is provided with 50-60 degrees of bending, and the bending direction faces the tension direction of the spring; the lower locking stay bar (4) is hinged at a position, which is 1/4 of the small end and the large end and is close to the small end; the lower lock stay bar (4) is of a hollow quadrangle star structure, the hollow quadrangle star structure comprises a groove, and the unlocking actuating cylinder (8) can be laid in the groove; the boss is arranged at the joint of the locking stay bar (3) and the lower locking stay bar (4), the boss is provided with a first threaded hole, the corresponding position of the lower locking stay bar (4) is provided with a second threaded hole, the first threaded hole is provided with a first bolt, the second threaded hole is provided with a second bolt, and when the axis of the locking stay bar (3) and the axis of the lower locking stay bar (4) reach a preset angle, the first bolt and the second bolt mutually interfere to limit the relative movement of the locking stay bar (3) and the lower locking stay bar (4).
2. Landing gear side stay mechanism according to claim 1, wherein the distance at which the unlocking cylinder (8) is hinged to the lower lock stay (4) is not more than 1/3 of the length of the lower lock stay (4) from the position at which the upper lock stay (3) is hinged to the lower lock stay (4).
3. Landing gear side stay mechanism according to claim 1, wherein the upper stay (1) is "Y" -shaped, and the lower stay (2) is partially submerged in the "Y" -shaped gap of the upper stay (1) when the upper stay (1) is screwed around the hinge point to overlap the lower stay (2).
4. A side stay mechanism for a landing gear according to claim 1, wherein the joint bearings are mounted at the position where the upper stay (1) is hinged to the landing gear and at the position where the lower stay (2) is hinged to the landing gear.
5. Landing gear side stay mechanism according to claim 1, wherein the upper stay (1) is hinged to the lower stay (2) through an upper stay connecting shaft (6), the upper stay connecting shaft (6) is of a hollow cylindrical structure, end covers are mounted at two ends, and the end covers are mounted and connected through a central shaft penetrating through the upper stay connecting shaft (6).
6. The landing gear side stay mechanism according to claim 1, wherein when the first bolt and the second bolt interfere with each other, axes of the first bolt and the second bolt are parallel to each other.
7. A landing gear side stay mechanism according to claim 1, wherein a height adjustment washer is mounted between the first or second threaded hole and the first or second bolt.
8. Landing gear side stay mechanism according to claim 1, wherein the width of the articulation spring (5) of the locking stay (3) gradually increases towards the bend.
9. Landing gear side stay mechanism according to claim 1, wherein the springs (5) are double springs.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111120727.XA CN113753222B (en) | 2021-09-24 | 2021-09-24 | Undercarriage side stay bar mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111120727.XA CN113753222B (en) | 2021-09-24 | 2021-09-24 | Undercarriage side stay bar mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113753222A CN113753222A (en) | 2021-12-07 |
| CN113753222B true CN113753222B (en) | 2023-09-22 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111120727.XA Active CN113753222B (en) | 2021-09-24 | 2021-09-24 | Undercarriage side stay bar mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113753222B (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201745745U (en) * | 2010-07-20 | 2011-02-16 | 中国航空工业集团公司西安飞机设计研究所 | Strut lock mechanism in landing position of airplane landing gear |
| CN102020014A (en) * | 2010-12-09 | 2011-04-20 | 南京航空航天大学 | Airplane landing gear with deflected airplane wheel retraction jack |
| CN203439255U (en) * | 2013-08-05 | 2014-02-19 | 哈尔滨飞机工业集团有限责任公司 | Drop supporting and locking device of landing gear |
| CN104354853A (en) * | 2014-10-29 | 2015-02-18 | 中航飞机起落架有限责任公司 | Foldable supporting rod lock mechanism of landing gear |
| CN205418077U (en) * | 2016-01-13 | 2016-08-03 | 哈尔滨飞机工业集团有限责任公司 | Maintain the body that locks of undercarriage down lock |
| CN112478131A (en) * | 2020-12-08 | 2021-03-12 | 中航飞机起落架有限责任公司 | Mechanical lock mechanism of integrated linkage coordination valve |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB0702866D0 (en) * | 2007-02-14 | 2007-03-28 | Airbus Uk Ltd | Landing gear |
| GB2507823B (en) * | 2012-11-27 | 2014-10-08 | Messier Dowty Ltd | Landing gear assembly with lost motion mechanism |
-
2021
- 2021-09-24 CN CN202111120727.XA patent/CN113753222B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201745745U (en) * | 2010-07-20 | 2011-02-16 | 中国航空工业集团公司西安飞机设计研究所 | Strut lock mechanism in landing position of airplane landing gear |
| CN102020014A (en) * | 2010-12-09 | 2011-04-20 | 南京航空航天大学 | Airplane landing gear with deflected airplane wheel retraction jack |
| CN203439255U (en) * | 2013-08-05 | 2014-02-19 | 哈尔滨飞机工业集团有限责任公司 | Drop supporting and locking device of landing gear |
| CN104354853A (en) * | 2014-10-29 | 2015-02-18 | 中航飞机起落架有限责任公司 | Foldable supporting rod lock mechanism of landing gear |
| CN205418077U (en) * | 2016-01-13 | 2016-08-03 | 哈尔滨飞机工业集团有限责任公司 | Maintain the body that locks of undercarriage down lock |
| CN112478131A (en) * | 2020-12-08 | 2021-03-12 | 中航飞机起落架有限责任公司 | Mechanical lock mechanism of integrated linkage coordination valve |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113753222A (en) | 2021-12-07 |
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