CN114030594A - Strut type undercarriage leg retracting mechanism - Google Patents
Strut type undercarriage leg retracting mechanism Download PDFInfo
- Publication number
- CN114030594A CN114030594A CN202111548281.0A CN202111548281A CN114030594A CN 114030594 A CN114030594 A CN 114030594A CN 202111548281 A CN202111548281 A CN 202111548281A CN 114030594 A CN114030594 A CN 114030594A
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- Prior art keywords
- shackle
- hook
- outer cylinder
- piston rod
- undercarriage
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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 strut type undercarriage leg contraction mechanism which comprises a piston rod, an outer cylinder, an upper stay bar, a lower stay bar, a hook ring, an upper torsion arm, a lower torsion arm and a tire, wherein the piston rod is connected with the outer cylinder through a bolt; one end of a hook is fixed on the lower support rod, the other end of the hook is positioned under one end of the hook ring, a gap is reserved, the other end of the hook ring is fixed on the upper torsion arm, the two ends of the upper torsion arm are respectively and rotatably connected with the outer wall of the outer cylinder and one end of the lower torsion arm, the other end of the lower torsion arm is rotatably connected with the outer wall of the piston rod, the two ends of the piston rod are respectively and rotatably connected with the outer wall of the outer cylinder and one end of the upper support rod, the other ends of the outer cylinder and the upper support rod are both rotatably connected with the machine body structure, when the undercarriage is in a down state, the upper support rod and the lower support rod are unfolded and fixed, and the hook ring are not in contact; when the undercarriage is in a folded state, the upper and lower support rods are folded, the hook hooks the hook ring, and the piston rod is driven to contract relative to the outer cylinder, so that the leg of the undercarriage is contracted; the invention has the advantages that: simple structure, the reliability is high.
Description
Technical Field
The invention belongs to the field of structural design and application of an undercarriage, and particularly relates to a strut type undercarriage leg retracting mechanism.
Background
Aircraft landing gear systems are one of the most important systems for aircraft, and most aircraft have landing gears housed in the fuselage or wings in order to reduce drag and improve aerodynamic performance while the aircraft is in flight. However, the space available for storing the landing gear in the general body is very compact, and even the solution fails because the storage space is not enough, so the landing gear needs to occupy the space as small as possible after being stored.
To reduce the stowage space of the landing gear, the legs are suitably retracted after the landing gear is stowed in place, typically by mechanical or hydraulic means. For a strut type undercarriage, the existing scheme is to realize the extension and retraction of a buffer strut by generally filling and discharging pressure in the buffer strut, so that the purpose of leg retraction of the undercarriage is achieved. This approach is then mechanically complex, reducing the reliability of the landing gear and requiring a large 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 practical requirements, thereby providing the strut type undercarriage leg-retracting mechanism which has simple structure, can realize leg retraction of the strut type undercarriage without influencing the internal structure of the buffer strut and reduces the stowage space of the undercarriage.
In order to achieve the purpose, the invention adopts the technical scheme that: a strut type landing gear leg-contracting mechanism comprises a piston rod, an outer cylinder, an upper stay bar, a lower stay bar, a hook ring, an upper torsion arm, a lower torsion arm and a tire; one end of a hook is fixed on a lower support rod, the other end of the hook is positioned under one end of a hook ring, a gap is reserved, the other end of the hook ring is fixed on an upper torsion arm, one end of the upper torsion arm is rotatably connected with the outer wall of an outer cylinder, the other end of the upper torsion arm is rotatably connected with one end of a lower torsion arm, the other end of the lower torsion arm is rotatably connected with the outer wall of a 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 a tire, the other end of the outer cylinder is rotatably connected with a machine body structure, one end of the lower support rod is rotatably connected with the outer wall of the outer cylinder, the other end of the lower support rod is rotatably connected with one end of the upper support rod, the other end of the upper support rod is rotatably connected with the machine body structure, when the undercarriage is in a down state, the lower support rod and the upper support rod are unfolded and fixed, a certain distance is reserved between the other end of the hook ring, no contact is generated, and no mutual acting force is generated; when the undercarriage is in a folded state, the upper support rod and the lower support rod are folded, one end of the hook ring is hooked at the other end of the hook, the upper torque arm is driven to rotate, the piston rod is driven to shrink along the axis of the outer cylinder through the lower torque arm, the length of a buffer strut composed of the piston rod of the undercarriage and the outer cylinder is shortened, and the purpose of leg shrinkage of the undercarriage is achieved.
Furthermore, 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 barrel in a rotating mode through bolts, and the lower stay bar is located at the upper end of the upper torque arm.
Furthermore, 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 barrel and the other end of the upper support rod are respectively in rotary connection with the machine body structure through bolts.
Furthermore, one end of the hook is welded on the lower support rod.
Further, the piston rod is connected with the outer cylinder in a sliding mode.
Further, the shackle comprises a shackle base, shackle lugs and a shackle shaft, the shackle base, the shackle lugs and the shackle shaft are of an integral structure, the number of the shackle lugs is two, one ends of the two shackle lugs are perpendicular to the shackle base, a gap is reserved between the two shackle lugs and is symmetrically distributed, the shackle shaft is located between the other ends of the two shackle lugs, the shackle base is fixed on the upper torsion arm through bolts, when the undercarriage is in a down state, the other end of the hook is located under the shackle shaft, a gap is reserved, and when the undercarriage is in a take-up state, the other end of the hook hooks the shackle shaft.
Furthermore, the shackle base is a triangle with a fillet, a plurality of bolt holes for bolts to pass through are formed in the shackle base, the two shackle lugs are both triangular, and the two shackle lugs and the shackle shaft connecting end are provided with fillets.
In the present invention, the hook is fixed to the lower stay and the shackle base is fixed to the upper torque arm. When the undercarriage is in a down state, the lower support rod and the upper support rod are unfolded and fixed, and a certain distance is reserved between the hook and the shackle, so that the hook and the shackle cannot be contacted, and no interaction force is generated, so that the normal extension and retraction of the undercarriage buffer support are not influenced. When the undercarriage is folded, the upper support rod and the lower support rod are folded, the lower support rod is folded and rotated to drive the hook to rotate, the hook hooks the hook ring in the rotating process, the upper torque arm is driven to rotate, and therefore the piston rod is driven to shrink along the axis of the outer cylinder, and the purpose of leg shrinkage of the undercarriage is achieved.
The invention has the beneficial effects that: the leg-retracting mechanism of the strut type undercarriage provided by the invention can realize leg retraction of the undercarriage only by a small number of structures, reduces the storage space of the undercarriage, and has the advantages of simple structure and high reliability; an additional charge and discharge mechanism is not needed, so that the inspection and maintenance are facilitated, and the maintenance cost is greatly reduced; high practicability, easy realization and wide applicability.
Drawings
FIG. 1 is a schematic representation of the landing gear of the present invention in a free down position;
FIG. 2 is a schematic view of a shackle of the present invention;
FIG. 3 is a schematic view of the shackle and hook being hooked during retraction of the landing gear of the present invention;
fig. 4 is a schematic view of the retractable leg of the landing gear of the present invention in the stowed condition.
In the figure: the device comprises a piston rod 1, an outer cylinder 2, an upper support rod 3, a lower support rod 4, a hook 5, a shackle 6, an upper torsion arm 7, a lower torsion arm 8, a tire 9, a shackle shaft 10, a shackle base 11 and a shackle lug 12.
Detailed Description
The following detailed description of embodiments of the invention refers to the accompanying drawings. It should be understood that the detailed description and specific examples, while indicating the present invention, are given by way of illustration and explanation only, not limitation.
As shown in fig. 1 to 4, the present invention provides a strut-type landing gear leg-retracting mechanism, comprising a piston rod 1, an outer cylinder 2, an upper strut 3, a lower strut 4, a hook 5, a shackle 6, an upper torsion arm 7, a lower torsion arm 8 and a tire 9; one end of a hook 5 is fixed on a lower support rod 4, the other end of the hook is positioned under one end of a shackle 6 and a gap is reserved, the other end of the shackle 6 is fixed on an upper torsion arm 7, one end of the upper torsion arm 7 is rotatably connected with the outer wall of an outer cylinder 2, the other end of the upper torsion arm is rotatably connected with one end of a lower torsion arm 8, the other end of the lower torsion arm 8 is rotatably 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 rotatably connected with a machine body structure, one end of the lower support rod 4 is rotatably connected with the outer wall of the outer cylinder 2, the other end of the lower support rod 4 is rotatably connected with one end of an upper support rod 3, the other end of the upper support rod 3 is rotatably connected with the machine body structure, when the undercarriage is in a down state, the lower support rod 4 and the upper support rod 3 are unfolded and fixed, a certain distance is reserved between the other end of the hook 5 and one end of the shackle 6, and no contact is generated, and no mutual acting force is generated; when the undercarriage is in a folded state, the upper support rod 3 and the lower support rod 4 are folded, the other end of the hook 5 hooks one end of the hook ring 6 to drive the upper torque arm 7 to rotate, so that the piston rod 1 is driven by the lower torque arm 8 to shrink along the axis of the outer cylinder 2, the length of a buffer strut formed by the piston rod 1 and the outer cylinder 2 of the undercarriage is shortened, and the purpose of leg contraction of the undercarriage is achieved.
Preferably, one end of the lower stay 4 and one end of the upper torque arm 7 are respectively and rotatably connected with the outer wall of the outer cylinder 2 through bolts, and the lower stay 4 is positioned at the upper end of the upper torque arm 7.
Preferably, the other end of the lower torque arm 8 is rotatably 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 an axle.
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 slidably connected 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 number of the shackle lugs 12 is two, one ends of the two shackle lugs 12 are perpendicular to the shackle base 11, a gap is reserved between the two shackle lugs 12 and is 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 torsion arm 7 through bolts, when the undercarriage is in a down state, the other end of the hook 5 is located under the shackle shaft 10, a gap is reserved, and when the undercarriage is in a up state, the other end of the hook 5 hooks the shackle shaft 10.
Preferably, the shackle base 11 is a triangle with rounded corners, a plurality of bolt holes for bolts to pass through are arranged on the triangle, the two shackle lugs 12 are both 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 free state diagram is shown in fig. 1, and 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 structural diagram is shown in fig. 2. The hook ring base 11 is fixed on the upper torque arm 7 through a bolt, the hook 5 is fixed on the lower stay bar 4 through welding, when the landing gear is in a down state, the lower stay bar 4 and the upper stay bar 3 are unfolded to be almost in a straight line and locked for bearing the landing gear ground load, the landing gear tire 9 contacts the ground when the aircraft lands, the tire 9 is subjected to the ground load to enable the piston rod 1 to be compressed along the axis of the outer cylinder 2 and 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 hook ring shaft 10 is only increased and cannot be contacted, no interaction force is generated between the hook 5 and the hook ring shaft 10, and the normal extension and retraction of the landing gear between the piston rod 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 folding state, the stay rod system (namely the upper stay rod 3 and the lower stay rod 4) is folded, the lower stay rod 4 rotates upwards along a connecting bolt with the outer cylinder 2, in the process of folding the landing gear, the hook 5 hooks the hook ring shaft 10 to generate interaction force, as shown in figure 3, the hook 5 and the hook ring shaft 10 can be contacted to generate interaction force only in the process of folding the stay rod system (namely the upper stay rod 3 and the lower stay rod 4) in the process of folding the landing gear, the hook ring shaft 10 is loaded by the hook 5 to drive the upper torsion arm 7 to rotate along the connecting bolt with the outer cylinder 2, the included angle between the upper torsion arm 7 and the lower torsion arm 8 is reduced, and the lower torsion arm 8 drives the piston rod 1 to shrink along the axis of the outer cylinder 2, so that the purpose of leg shrinkage of the landing gear is achieved, and finally the landing gear is folded as shown in figure 4.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.
Furthermore, those skilled in the art will appreciate that while some embodiments herein include some features included in other embodiments, rather than other features, 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 above, 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 (8)
1. The utility model provides a leg mechanism is contracted to strut type undercarriage which characterized in that: 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 torsion arm (7), a lower torsion arm (8) and a tire (9); one end of a hook (5) is fixed on a lower stay bar (4), the other end is positioned under 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 torsion arm (7), one end of the upper torsion arm (7) is rotationally connected with the outer wall of an outer cylinder (2), the other end of the upper torsion arm is rotationally connected with one end of a lower torsion arm (8), the other end of the lower torsion 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 stay bar (4) is rotationally connected with the outer wall of the outer cylinder (2), the other end of the upper stay bar (3) is rotationally connected with the machine body structure, when the undercarriage 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), so that the hook and the hook are not in contact and do not generate interaction force; when the undercarriage is in a folded state, the upper supporting rod (3) and the lower supporting rod (4) are folded, the other end of the hook (5) is hooked with one end of the upper hook ring (6) to drive the upper torque arm (7) to rotate, so that the piston rod (1) is driven by the lower torque arm (8) to shrink along the axis of the outer cylinder (2), the length of a buffer support column formed by the piston rod (1) and the outer cylinder (2) of the undercarriage is shortened, and the purpose of leg shrinkage of the undercarriage is achieved.
2. A strut landing gear leg reduction mechanism according to claim 1, wherein: one end of the lower stay bar (4) and one end of the upper torque arm (7) are respectively and rotatably connected with the outer wall of the outer cylinder (2) through bolts, and the lower stay bar (4) is positioned at the upper end of the upper torque arm (7).
3. A strut landing gear leg reduction mechanism according to 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 axle.
4. A strut landing gear leg reduction mechanism according to 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. A strut landing gear leg reduction mechanism according to claim 1, wherein: one end of the hook (5) is welded on the lower stay bar (4).
6. A strut landing gear leg reduction mechanism according to claim 1, wherein: the piston rod (1) is connected with the outer cylinder (2) in a sliding way.
7. A strut landing gear leg reduction mechanism according to claim 1, wherein: the shackle 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 lugs, one ends of the two shackle lugs (12) are perpendicular to the shackle base (11), a gap is reserved between the two shackle lugs (12) and is 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 an upper torsion arm (7) through bolts, when the undercarriage is in a down state, the other end of the hook (5) is located under the shackle shaft (10) and is reserved with a gap, and when the undercarriage is in a take-up state, the other end of the hook (5) hooks the shackle shaft (10).
8. A strut landing gear leg reduction mechanism according to claim 7, wherein: the shackle base (11) is a triangle with a rounded angle, a plurality of bolt holes for bolts to pass through are arranged on the shackle base, the two shackle lugs (12) are both triangular, and the connecting ends of the two shackle lugs (12) and the shackle shaft (10) are rounded angles.
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 true CN114030594A (en) | 2022-02-11 |
| CN114030594B CN114030594B (en) | 2023-08-25 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202111548281.0A Active CN114030594B (en) | 2021-12-17 | 2021-12-17 | Leg retracting mechanism of strut type landing gear |
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Citations (10)
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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 |
| 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 |
| US20180162522A1 (en) * | 2016-12-14 | 2018-06-14 | Goodrich Corporation | Non-jamming shrink latch assembly for retractable aircraft landing gear |
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| US20210107632A1 (en) * | 2019-10-09 | 2021-04-15 | 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 |
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| CN114030594B (en) | 2023-08-25 |
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