CN114030594B - Leg retracting mechanism of strut type landing gear - Google Patents
Leg retracting mechanism of strut type landing gear Download PDFInfo
- Publication number
- CN114030594B CN114030594B CN202111548281.0A CN202111548281A CN114030594B CN 114030594 B CN114030594 B CN 114030594B CN 202111548281 A CN202111548281 A CN 202111548281A CN 114030594 B CN114030594 B CN 114030594B
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- China
- Prior art keywords
- landing gear
- hook ring
- torque arm
- hook
- shackle
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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
- B64C25/20—Operating mechanisms mechanical
-
- 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)
- Vehicle Body Suspensions (AREA)
Abstract
The invention discloses a leg retraction mechanism of a strut type undercarriage, which comprises a piston rod, an outer cylinder, an upper stay bar, a lower stay bar, a hook, a shackle, an upper torque arm, a lower torque arm and a tire, wherein the outer cylinder is arranged on the piston rod; one end of the hook is fixed on the lower stay bar, the other end of the hook is positioned right below one end of the shackle with a gap, the other end of the shackle is fixed on the upper torque arm, two ends of the upper torque arm are respectively and rotatably connected with the outer wall of the outer cylinder and one end of the lower torque arm, the other end of the lower torque arm is rotatably connected with the outer wall of the piston rod, two ends of the piston rod are respectively sleeved with the outer cylinder and connected with a tire, two ends of the lower stay bar are respectively and rotatably connected with the outer wall of the outer cylinder and one end of the upper stay bar, the other ends of the outer cylinder and the upper stay bar are rotatably connected with a machine body structure, when the landing gear is in a down state, the upper stay bar and the lower stay bar are unfolded and fixed, and the hook is not contacted with the shackle; when the landing gear is in a retracted state, the upper supporting rod and the lower supporting rod are folded, the hook hooks the shackle, and the piston rod is driven to retract relative to the outer cylinder, so that the purpose of retracting the landing gear is achieved; the invention has the advantages that: simple structure and high reliability.
Description
Technical Field
The invention belongs to the field of structural design and application of landing gears, and particularly relates to a leg retracting mechanism of a strut type landing gear.
Background
Aircraft landing gear systems are among the most important systems of an aircraft, most of which stow the landing gear in the fuselage or wing during flight of the aircraft in order to reduce drag and improve aerodynamic performance. However, the space available for the landing gear to be stored in the general machine body is very compact, and even the space occupied by the landing gear after being stored is required to be as small as possible because the storage space is insufficient to cause the scheme to fail.
To reduce the landing gear stowage space, the landing gear is typically properly retracted after being stowed in place by a mechanism or hydraulic transmission. For the strut type landing gear, the existing scheme generally realizes the expansion and contraction of the buffer strut by the inflation and the deflation of the buffer strut, so that the purpose of leg retraction of the landing gear is achieved. This approach is then mechanically complex, reduces the reliability of the landing gear, and requires a significant weight penalty.
Disclosure of Invention
Aiming at the prior art, the invention aims to overcome the defects in the prior art and adapt to the actual needs, thereby providing the strut type landing gear leg-shrinking mechanism which has simple structure and can realize leg shrinking of the strut type landing gear without influencing the internal structure of the buffer strut and reduce the storage space of the landing gear.
In order to achieve the above purpose, the technical scheme adopted by the invention is as follows: a leg shrinking mechanism of a strut landing gear comprises a piston rod, an outer cylinder, an upper stay bar, a lower stay bar, a hook, a shackle, an upper torque arm, a lower torque arm and a tire; one end of the hook is fixed on the lower stay bar, the other end of the hook is positioned right below one end of the shackle and is provided with a gap, the other end of the shackle is fixed on the upper torque arm, one end of the upper torque arm is rotationally connected with the outer wall of the outer cylinder, the other end of the upper torque arm is rotationally connected with one end of the lower torque arm, the other end of the lower torque arm is rotationally connected with the outer wall of the piston rod, one end of the piston rod is sleeved with one end of the outer cylinder, the other end of the piston rod is connected with the tire, the other end of the outer cylinder is rotationally connected with the machine body structure, one end of the lower stay bar is rotationally connected with one end of the upper stay bar, the other end of the upper stay bar is rotationally connected with the machine body structure, when the undercarriage is in a down state, the lower stay bar and the upper stay bar are unfolded and fixed, a certain distance is reserved between the other end of the hook and one end of the shackle, and interaction force is not generated; when the landing gear is in a folded state, the upper supporting rod and the lower supporting rod are folded, one end of the hook ring is hooked at the other end of the hook, and the upper torque arm is driven to rotate, so that the piston rod is driven to shrink along the axis of the outer cylinder through the lower torque arm, the length of a buffering support column formed by the landing gear piston rod and the outer cylinder is shortened, and the purpose of leg shrinkage of the landing gear is achieved.
Further, one end of the lower stay bar and one end of the upper torque arm are respectively connected with the outer wall of the outer cylinder in a rotating way through bolts, and the lower stay bar is positioned at the upper end of the upper torque arm.
Further, the other end of the lower torque arm is rotationally connected with the outer wall of the piston rod through a bolt, and the tire is connected with one end of the piston rod through a wheel shaft.
Further, the other end of the outer cylinder and the other end of the upper stay bar are respectively connected with the machine body structure in a rotating way through bolts.
Further, one end of the hook is welded on the lower stay bar.
Further, the piston rod is in sliding connection with the outer cylinder.
Further, the shackle includes shackle base, shackle tab and hook ring axle, shackle base, shackle tab and hook ring axle are overall structure, and the shackle tab is equipped with two, and two shackle tab one ends all perpendicular to on the shackle base, leave the clearance and be symmetric distribution in the middle of two shackle tabs, and the shackle axle is located between two shackle tab other ends, and the shackle base passes through the bolt fastening on the torque arm, when the undercarriage is the state of putting down, the couple other end is located under the hook ring axle, and leaves the clearance, and when the undercarriage is the state of putting up, the hook ring axle is hooked to the couple other end.
Further, the shackle base is a triangle with a rounded corner, a plurality of bolt holes for bolts to pass through are formed in the shackle base, the two shackle lugs are triangular, and the connecting ends of the two shackle lugs and the shackle shaft are rounded.
In the invention, the hook is fixed on the lower stay bar, and the shackle base is fixed on the upper torque arm. In the landing gear down state, the lower stay bar and the upper stay bar are unfolded and fixed, a certain distance is reserved between the hook and the shackle, the hook and the shackle are not contacted, and no interaction force is generated, so that the normal expansion and contraction of the landing gear buffer strut are not influenced. When the landing gear is folded, the upper stay bar and the lower stay bar are folded, the lower stay bar is folded to rotate to drive the hook to rotate, the hook hooks a hook ring in the rotating process to drive the upper torque arm to rotate, so that the piston rod is driven to shrink along the axis of the outer cylinder, and the purpose of landing gear leg shrinking is achieved.
The beneficial effects of the invention are as follows: the leg retraction mechanism of the strut type landing gear can realize leg retraction of the landing gear with few structures, reduces the storage space of the landing gear, and has simple structure and high reliability; no additional pressurizing and releasing mechanism is needed, so that the inspection and maintenance are convenient, and the maintenance cost is greatly reduced; the practicability is high, the implementation is easy, and the applicability is wide.
Drawings
FIG. 1 is a schematic view of the landing gear of the present invention in an extended free state;
FIG. 2 is a schematic view of the construction of the shackle of the present invention;
FIG. 3 is a schematic view of a shackle and hook during landing gear assembly of the present invention;
FIG. 4 is a schematic illustration of the landing gear of the present invention in a retracted, on-board position.
In the figure: the novel bicycle is characterized in that the novel bicycle comprises a piston rod 1, an outer cylinder 2, an upper supporting rod 3, a lower supporting rod 4, a hook 5, a shackle 6, an upper torque arm 7, a lower torque arm 8, a tire 9, a shackle shaft 10, a shackle base 11 and a shackle lug 12.
Detailed Description
The following describes specific embodiments of the present invention in detail with reference to the drawings. It should be understood that the detailed description and specific examples, while indicating and illustrating the invention, are not intended to limit the invention.
As shown in fig. 1 to 4, the present invention provides a leg retraction mechanism of a strut landing gear, comprising a piston rod 1, an outer cylinder 2, an upper stay 3, a lower stay 4, a hook 5, a shackle 6, an upper torque arm 7, a lower torque arm 8 and a tire 9; one end of the hook 5 is fixed on the lower stay bar 4, the other end of the hook is positioned right below one end of the hook ring 6 with a gap, the other end of the hook ring 6 is fixed on the upper torque arm 7, one end of the upper torque arm 7 is rotationally connected with the outer wall of the outer cylinder 2, the other end of the upper torque arm 8 is rotationally connected with one end of the lower torque arm 8, the other end of the lower torque arm 8 is rotationally connected with the outer wall of the piston rod 1, one end of the piston rod 1 is sleeved with one end of the outer cylinder 2, the other end of the piston rod is connected with the tire 9, the other end of the outer cylinder 2 is rotationally connected with a machine body structure, one end of the lower stay bar 4 is rotationally connected with one end of the upper stay bar 3, the other end of the upper stay bar 3 is rotationally connected with the machine body structure, when the landing gear is in a down state, the lower stay bar 4 and the upper stay bar 3 are unfolded and fixed, a certain distance is reserved between the other end of the hook 5 and one end of the hook ring 6, and the landing gear are not contacted, and interaction force is not generated; when the landing gear is in a folded state, the upper supporting rod 3 and the lower supporting rod 4 are folded, one end of the hook ring 6 is hooked at the other end of the hook 5, and the upper torque arm 7 is driven to rotate, so that the piston rod 1 is driven to shrink along the axis of the outer cylinder 2 through the lower torque arm 8, the length of a buffering support column formed by the landing gear piston rod 1 and the outer cylinder 2 is shortened, and the purpose of leg shrinkage of the landing gear is achieved.
Preferably, one end of the lower stay bar 4 and one end of the upper torque arm 7 are respectively connected with the outer wall of the outer cylinder 2 in a rotating way through bolts, and the lower stay bar 4 is positioned at the upper end of the upper torque arm 7.
Preferably, the other end of the lower torque arm 8 is rotationally connected with the outer wall of the piston rod 1 through a bolt, and the tire 9 is connected with one end of the piston rod 1 through a wheel shaft.
Preferably, the other end of the outer cylinder 2 and the other end of the upper stay bar 3 are respectively connected with the machine body structure in a rotating way through bolts.
Preferably, one end of the hook 5 is welded to the lower stay 4.
Preferably, the piston rod 1 is in sliding connection with the outer cylinder 2.
Preferably, the shackle 6 comprises a shackle base 11, shackle lugs 12 and a shackle shaft 10, the shackle base 11, the shackle lugs 12 and the shackle shaft 10 are of an integral structure, the shackle lugs 12 are provided with two, one ends of the two shackle lugs 12 are perpendicular to the shackle base 11, gaps are reserved between the two shackle lugs 12 and are symmetrically distributed, the shackle shaft 10 is located between the other ends of the two shackle lugs 12, the shackle base 11 is fixed on the upper torque arm 7 through bolts, when the landing gear is in a down state, the other ends of the hooks 5 are located under the shackle shaft 10, gaps are reserved, and when the landing gear is in a up state, the other ends of the hooks 5 hook the shackle shaft 10.
Preferably, the shackle base 11 is triangular with rounded corners, a plurality of bolt holes for bolts to pass through are formed in the shackle base, the two shackle lugs 12 are triangular, and the connecting ends of the two shackle lugs 12 and the shackle shaft 10 are rounded.
The working principle of the invention is as follows: the landing gear is shown in a schematic view in a free state in which the shackle 6 is composed of a shackle base 11, a shackle tab 12 and a shackle shaft 10, and is of an integral structure, and the schematic view of the structure is shown in fig. 2. The shackle base 11 is fixed on the upper torque arm 7 through bolts, the hook 5 is fixed on the lower stay bar 4 through welding, when the landing gear is in a put-down state, the lower stay bar 4 and the upper stay bar 3 are unfolded to be almost in a straight line and locked, so that landing gear tires 9 are contacted with the ground when the aircraft lands, the tires 9 are subjected to the ground load, so that the piston rods 1 are compressed along the axis of the outer cylinder 2 to absorb landing energy, the upper torque arm 7 rotates upwards along the connecting bolt with the outer cylinder 2, the distance between the hook 5 and the shackle shaft 10 is only increased, the hook 5 and the shackle shaft 10 are not contacted, interaction force is not generated between the hook 5 and the shackle shaft 10, and normal expansion and contraction between the piston rods 1 and the outer cylinder 2 when the landing gear is subjected to the ground load are not influenced; when the landing gear is in a folded state, the stay bar system (namely the upper stay bar 3 and the lower stay bar 4) is folded, the lower stay bar 4 rotates upwards along a connecting bolt with the outer cylinder 2, in the landing gear upper process, the hook 5 hooks the hook ring shaft 10 to generate interaction force, as shown in fig. 3, the hook 5 and the hook ring shaft 10 only contact the interaction force in the landing gear upper process (namely the upper stay bar 3 and the lower stay bar 4) folding process, the hook ring shaft 10 receives the load of the hook 5 to drive the upper torque arm 7 to rotate along the connecting bolt with the outer cylinder 2, the included angle between the upper torque arm 7 and the lower torque arm 8 is reduced, the lower torque arm 8 drives the piston rod 1 to shrink along the axis of the outer cylinder 2, and therefore the landing gear leg shrinkage purpose is achieved, and finally the landing gear upper is shown in fig. 4.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, and not for limiting the same; although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some or all of the technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit of the invention.
Furthermore, those skilled in the art will appreciate that while some embodiments herein include some features but not others included in other embodiments, combinations of features of different embodiments are meant to be within the scope of the invention and form different embodiments. For example, in the claims below, any of the claimed embodiments may be used in any combination. The information disclosed in this background section is only for enhancement of understanding of the general background of the invention and should not be taken as an acknowledgement or any form of suggestion that this information forms the prior art already known to a person skilled in the art.
Claims (7)
1. A leg retraction mechanism for a strut landing gear, comprising: the device comprises a piston rod (1), an outer cylinder (2), an upper stay bar (3), a lower stay bar (4), a hook (5), a shackle (6), an upper torque arm (7), a lower torque arm (8) and a tire (9); one end of a hook (5) is fixed on a lower supporting rod (4), the other end of the hook is positioned right below one end of a hook ring (6) and is provided with a gap, the other end of the hook ring (6) is fixed on an upper torque arm (7), one end of the upper torque arm (7) is rotationally connected with the outer wall of an outer cylinder (2), the other end of the upper torque arm is rotationally connected with one end of a lower torque arm (8), the other end of the lower torque arm (8) is rotationally connected with the outer wall of a piston rod (1), one end of the piston rod (1) is sleeved with one end of the outer cylinder (2), the other end of the piston rod is connected with a tire (9), the other end of the outer cylinder (2) is rotationally connected with a machine body structure, one end of the lower supporting rod (4) is rotationally connected with one end of an upper supporting rod (3), when a landing gear is in a down state, the lower supporting rod (4) and the upper supporting rod (3) are unfolded and fixed, a certain distance is reserved between the other end of the hook (5) and one end of the hook ring (6) and the other end are not contacted, and interaction force is not generated; when the landing gear is in a retracted state, the upper stay bar (3) and the lower stay bar (4) are folded, one end of the hook ring (6) is hooked at the other end of the hook ring (5), the upper torque arm (7) is driven to rotate, thereby the piston rod (1) is driven to shrink along the axis of the outer cylinder (2) through the lower torque arm (8), the length of a buffering strut formed by the landing gear piston rod (1) and the outer cylinder (2) is shortened, the purpose of landing gear leg retraction is achieved, the hook ring (6) comprises a hook ring base (11), hook ring lugs (12) and a hook ring shaft (10), the hook ring base (11), the hook ring lugs (12) and the hook ring shaft (10) are of an integral structure, one ends of the two hook ring lugs (12) are perpendicular to the hook ring base (11), gaps are reserved between the two hook ring lugs (12) and are symmetrically distributed, the hook ring shaft (10) is positioned between the other ends of the two hook ring lugs (12), the hook ring base (11) is fixed on the upper torque arm (7) through bolts, and when the landing gear is in a landing gear in a down state, the hook ring (5) is positioned under the hook ring shaft (10), and the hook ring is in a hook ring recovering state when the hook ring (10) is in the hook ring state.
2. The strut landing gear leg band mechanism of claim 1, wherein: one end of the lower stay bar (4) and one end of the upper torque arm (7) are respectively connected with the outer wall of the outer cylinder (2) in a rotating way through bolts, and the lower stay bar (4) is positioned at the upper end of the upper torque arm (7).
3. The strut landing gear leg band mechanism of claim 1, wherein: the other end of the lower torque arm (8) is rotationally connected with the outer wall of the piston rod (1) through a bolt, and the tire (9) is connected with one end of the piston rod (1) through a wheel shaft.
4. The strut landing gear leg band mechanism of claim 1, wherein: the other end of the outer cylinder (2) and the other end of the upper stay bar (3) are respectively connected with the machine body structure in a rotating way through bolts.
5. The strut landing gear leg band mechanism of claim 1, wherein: one end of the hook (5) is welded on the lower stay bar (4).
6. The strut landing gear leg band mechanism of claim 1, wherein: the piston rod (1) is in sliding connection with the outer cylinder (2).
7. The strut landing gear leg band mechanism of claim 1, wherein: the shackle base (11) is triangular with a rounded corner, a plurality of bolt holes for bolts to pass through are formed in the shackle base, the two shackle lugs (12) are triangular, and the connecting ends of the two shackle lugs (12) and the shackle shaft (10) are rounded.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111548281.0A CN114030594B (en) | 2021-12-17 | 2021-12-17 | Leg retracting mechanism of strut type landing gear |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111548281.0A CN114030594B (en) | 2021-12-17 | 2021-12-17 | Leg retracting mechanism of strut type landing gear |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114030594A CN114030594A (en) | 2022-02-11 |
| CN114030594B true CN114030594B (en) | 2023-08-25 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111548281.0A Active CN114030594B (en) | 2021-12-17 | 2021-12-17 | Leg retracting mechanism of strut type landing gear |
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| CN (1) | CN114030594B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118270230A (en) * | 2024-05-31 | 2024-07-02 | 四川腾盾科技有限公司 | Main landing gear of high-speed aircraft and design method |
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| GB538298A (en) * | 1940-04-30 | 1941-07-28 | Fairey Aviat Co Ltd | Improvements in or relating to retractable undercarriages for aircraft |
| GB650547A (en) * | 1947-12-15 | 1951-02-28 | Electro Hydraulics Ltd | Retractable landing gear for aircraft |
| KR970038700U (en) * | 1995-12-21 | 1997-07-29 | 대우중공업 주식회사 | Aircraft landing gear lock |
| KR101288898B1 (en) * | 2011-12-29 | 2013-07-23 | 김성남 | Landing gear aircraft |
| CN105151282A (en) * | 2015-09-14 | 2015-12-16 | 江西洪都航空工业集团有限责任公司 | Control method for reliable ground locking of landing gear of airplane |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US10259568B2 (en) * | 2016-12-14 | 2019-04-16 | Goodrich Corporation | Non-jamming shrink latch assembly for retractable aircraft landing gear |
| US11498662B2 (en) * | 2019-10-09 | 2022-11-15 | Goodrich Corporation | Electrically operated landing gear lock system |
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2021
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| GB491094A (en) * | 1937-03-04 | 1938-08-26 | Mercier Jean | Improvements in and relating to jointed mechanisms for aircraft |
| GB538298A (en) * | 1940-04-30 | 1941-07-28 | Fairey Aviat Co Ltd | Improvements in or relating to retractable undercarriages for aircraft |
| GB650547A (en) * | 1947-12-15 | 1951-02-28 | Electro Hydraulics Ltd | Retractable landing gear for aircraft |
| KR970038700U (en) * | 1995-12-21 | 1997-07-29 | 대우중공업 주식회사 | Aircraft landing gear lock |
| KR101288898B1 (en) * | 2011-12-29 | 2013-07-23 | 김성남 | Landing gear aircraft |
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| CN114030594A (en) | 2022-02-11 |
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