CN210101973U - Aircraft landing gear with buffeting resisting device - Google Patents
Aircraft landing gear with buffeting resisting device Download PDFInfo
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- CN210101973U CN210101973U CN201920038641.4U CN201920038641U CN210101973U CN 210101973 U CN210101973 U CN 210101973U CN 201920038641 U CN201920038641 U CN 201920038641U CN 210101973 U CN210101973 U CN 210101973U
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- landing gear
- buffeting
- main landing
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- 238000006073 displacement reaction Methods 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
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Abstract
The utility model discloses an aircraft landing gear with a buffeting resistant device, which comprises a main landing gear, an aircraft wheel and an upper resistance stay bar (2); the upper end of the lower resistance buffeting device (A) is hinged with the upper resistance stay bar (2), and the lower end of the lower resistance buffeting device (A) is hinged with the lower end of the main landing gear strut outer cylinder (1); the lower resistance anti-buffeting device (A) comprises an upper connecting piece (31), a lower connecting piece (30), and a rigid spring piece damper (a) and a rigid spring piece damper (b) which are fixed between the upper connecting piece and the lower connecting piece, the utility model realizes the dissipation of the buffeting state of the longitudinal ground sliding of the undercarriage, and solves the serious buffeting condition when the airplane slides on the ground; and the induced vibration energy of low frequency brake can be effectively absorbed, vibration amplitude and vibration load are greatly reduced, and the problems of jolting phenomenon when buffeting aggravates riding, damage to components and shortened service life are solved.
Description
Technical Field
The utility model relates to an aircraft landing gear vertically buffeting field, concretely relates to take aircraft landing gear of anti buffeting device.
Background
Low frequency brake induced vibrations of the main landing gear of an aircraft are also referred to as buffeting and the buffeting vibration frequency is typically below 30 Hz. In the whole sliding braking process after the wheels of the main landing gear of the airplane are grounded, under the action of a braking system, due to factors such as the change of ground binding force caused by the excitation of braking force, the flexibility of a strut of the main landing gear, the non-rigid connection of the main landing gear and the connection part of the airplane body, the elasticity of tires and the like, the buffeting phenomenon can occur when the landing gear is subjected to the changed ground tire force. Buffeting of the landing gear can aggravate bumping during riding, possibly cause damage to related components, fatigue cracks or breakage, shorten the service life of the landing gear system, and possibly induce ground run safety accidents of the airplane. Therefore, the research on the anti-buffeting problem of the landing gear is of great significance to the flight quality of the airplane.
The inerter has the characteristics of phase advance, high frequency passing and low frequency blocking, the university scholars of Cambridge in England firstly put forward the concept of the inerter in 2002, and through the development of decades, the inerter has been gradually applied to earthquake-proof buildings, vehicle suspensions, trains and landing gear shimmy systems. The prior art uses the inertial container for the vehicle suspension, and the publication number is CN108468625A, namely a suspension vibration energy driving braking system, and the publication number is CN108488299A, namely an inertial mass coefficient adjustable heavy vehicle inertial container, which indicate that the inertial container device is mature and reliable. The spring piece has the characteristics of phase lag, low pass frequency and high stop frequency. The longitudinal buffeting of the main undercarriage can be effectively relieved and restrained by reasonably and optimally combining the two.
In order to solve the problem of buffeting of the aircraft landing gear, the utility model discloses to be used to the container subassembly and be used for the induced vibration system of main landing gear low frequency brake, adopt to be used to the container and the damping device who constitutes to the rigid spring leaf attenuator that energy played the dissipation effect, can effective absorption low frequency vibration energy, greatly reduced vibration amplitude and vibration load improve the system dynamic property.
Disclosure of Invention
The purpose of the invention is as follows: the utility model is not enough to the aforesaid, a take aircraft undercarriage of anti buffeting device is proposed, adopts ball to be used to the parallelly connected mode of container and rigid spring piece attenuator, can effectively slow down the aircraft at the undercarriage forward and backward vibration phenomenon of braking in-process, has avoided the resonant problem of brake equipment.
An aircraft landing gear with a buffeting resisting device comprises a main landing gear, wheels and an upper drag brace rod; the main landing gear comprises a main landing gear strut outer cylinder and a main landing gear piston rod, and the main landing gear piston rod is slidably mounted in the main landing gear strut outer cylinder; the top of the main landing gear strut outer cylinder is fixedly arranged with the aircraft body, and the tail end of a main landing gear piston rod is provided with an aircraft wheel; the lower end of the main landing gear strut outer cylinder is hinged with an upper torsion arm, the lower end of a main landing gear piston rod is hinged with a lower torsion arm, and the upper torsion arm is hinged with the lower torsion arm; the upper end of the lower resistance buffeting device is hinged with the upper resistance stay bar, and the lower end of the lower resistance buffeting device is hinged with the lower end of the main landing gear strut outer cylinder;
the lower resistance anti-buffeting device comprises an upper connecting piece, a rigid spring piece damper and a lower connecting piece; the lower end of the upper resistance support rod is hinged with the upper connecting piece; the lower connecting piece is hinged with the lower end of the main landing gear strut outer cylinder; the rigid spring piece damper and the rigid spring piece damper are both fixed between the upper connecting piece and the lower connecting piece through screws.
The rigid spring piece damper comprises an upper fixed stay bar, a first threaded bushing, a connecting bolt, a second threaded bushing, a rigid spring piece and a lower fixed stay bar; the connecting bolt is provided with a nut, the tail end of the connecting bolt is provided with a thread, the connecting bolt sequentially penetrates through the first thread bushing, the rigid spring piece and the second thread bushing, and the tail ends of the connecting bolt are fixedly connected through a nut; the upper fixed stay bar is internally provided with threads, the lower fixed stay bar is internally provided with threads, and the first threaded bushing and the second threaded bushing are respectively fixedly connected with the upper fixed stay bar and the lower fixed stay bar through threads.
And a gasket and a bushing are respectively arranged at the joint of the connecting bolt and the first threaded bushing and the second threaded bushing.
The ball screw inertial container comprises a flywheel chamber, a flywheel, a screw, a bearing supporting seat, a screw supporting seat and a stroke chamber; threads are arranged at the uppermost end of the screw rod and a set distance away from the uppermost end, the distance is the length of the flywheel, and the section of the screw rod is polygonal; the flywheel is placed in the flywheel chamber, a polygon corresponding to the cross section shape of the upper end of the lead screw is arranged in the flywheel chamber, the lead screw penetrates through the flywheel, the lower end of the lead screw is fixed through a nut, a bearing supporting seat is arranged at the lower end of the lead screw, and the upper end of the lead screw is fixed through a nut; the tail end of the lead screw is arranged on the stroke chamber through the lead screw supporting seat; the stroke chamber is hollow, and a movable channel of the lead screw is formed.
And the flywheel chamber is sealed by a flywheel chamber sealing cover.
Has the advantages that:
(a) the dissipation of the buffeting state of the longitudinal ground sliding of the undercarriage is realized, and the serious buffeting condition of the airplane during ground sliding is solved;
(b) the anti-buffeting device can effectively absorb low-frequency brake induced vibration energy, greatly reduce vibration amplitude and vibration load, and solve the problems of bumping phenomenon and damage of parts caused by buffeting aggravation when a user takes the vehicle and shortening the service life.
(c) The lower resistance buffeting resisting device, the undercarriage main supporting column and the upper resistance supporting rod form a triangular structure, and the dynamic stability of an undercarriage system can be effectively improved.
Drawings
FIG. 1 is a schematic representation of an aircraft landing gear configuration with an anti-buffeting device;
FIG. 2 is a left side view of an aircraft landing gear with an anti-buffeting device;
FIG. 3 is a schematic view of the structural composition of the rigid leaf spring damper;
FIG. 4 is a schematic structural diagram of a ball screw inerter;
FIG. 5 is a schematic view of the structural connection of the lower resistance buffeting resisting apparatus;
number designation in the figures: 1. a main landing gear strut outer barrel, 2, an upper drag stay, 3, an upper torque arm, 4, a lower torque arm, 5, a tire, 6, a main landing gear piston rod, 7, a hub, 8, an upper fixed stay, 9, a first gasket, 10, a first bushing, 11, a second gasket, 12, a second bushing, 13, a fixing nut, 14, a first threaded bushing, 15, a connecting bolt, 16, a second threaded bushing, 17, a rigid leaf spring, 18, the device comprises a lower fixed stay bar, 19, a flywheel chamber sealing cover, 20, a flywheel chamber, 21, a third gasket, 22, a first nut, 23, a fourth gasket, 24, a second nut, 25, a screw, 26, a flywheel, 27, a bearing support seat, 28, a screw support seat, 29, a stroke chamber, 30, a lower connecting piece, 31, an upper connecting piece, A, a lower resistance anti-buffeting device, a rigid spring piece damper, b and a ball screw inertial container.
Detailed Description
The invention will be further elucidated with reference to the drawings and the specific embodiments.
Fig. 1 is a schematic view of the structure of an aircraft landing gear with an anti-buffeting device, and fig. 2 is a left side view of the aircraft landing gear with the anti-buffeting device. As shown in fig. 1 and 2, the landing gear with anti-buffeting device of the present invention includes a main landing gear, a wheel, an upper drag stay 2 and a lower drag anti-buffeting device a; the main landing gear comprises a main landing gear strut outer cylinder 1 and a main landing gear piston rod 6, wherein the main landing gear piston rod 6 is slidably mounted in the main landing gear strut outer cylinder 1 and can move in the main landing gear strut outer cylinder 1; the top of the main landing gear strut outer cylinder 1 is fixedly installed with the body. A wheel is mounted on the end of the main landing gear piston rod 6 through a bearing, and the wheel comprises a hub 7 and a tire 5 arranged on the hub 7. An upper torsion arm 3 is hinged to the lower end of the main landing gear strut outer cylinder 1, a lower torsion arm 4 is hinged to the lower end of the main landing gear piston rod 6, and the upper torsion arm 3 is hinged to the lower torsion arm 4.
The top end of the upper resistance stay bar 2 is arranged on the machine body, and the lower end of the upper resistance stay bar is hinged with the lower resistance buffeting resistant device A; the lower resistance anti-buffeting device A is hinged to the lower end of the main landing gear strut outer cylinder 1. The lower resistance anti-buffeting device A comprises an upper connecting piece 31, a rigid spring piece damper a, a rigid spring piece damper b and a lower connecting piece 30; lugs are arranged on the upper connecting piece 31 and the lower connecting piece 30, and the lower end of the upper resistance stay bar 2 is hinged on the lugs of the upper connecting piece 31; the lower end of the main landing gear strut outer cylinder 1 is provided with a lug, and the lug on the lower connecting piece 30 is hinged with the lug at the lower end of the main landing gear strut outer cylinder 1. The rigid spring piece damper a and the rigid spring piece damper b are fixed between the upper connecting piece and the lower connecting piece through screws.
FIG. 3 is a schematic view of the structure of the rigid leaf spring damper. As shown in fig. 3, the rigid spring piece damper a includes an upper fixed stay 8, a first threaded bush 14, a connecting bolt 15, a second threaded bush 16, a rigid spring piece 17, and a lower fixed stay 18. The connecting bolt 15 has a nut, a screw thread is provided at the end of the connecting bolt 15, the connecting bolt 15 passes through the first screw bush 14, the rigid spring piece 17 and the second screw bush 16 in sequence, and the ends thereof are fixedly connected by a nut (13). In the present invention, the joint of the connecting bolt 15 and the first threaded bushing 14 and the second threaded bushing 16 is provided with a gasket and a bushing, respectively. Threads are arranged in the upper fixing stay bar 8, threads are arranged in the lower fixing stay bar 18, and the first threaded bushing 14 and the second threaded bushing 16 are fixedly connected with the upper fixing stay bar 8 and the lower fixing stay bar 18 through threads respectively. Therefore, the ground heading resistance transmitted to the lower resistance anti-buffeting device acts on the rigid spring piece 17, the buffeting phenomenon of the undercarriage can be effectively relieved through the elasticity and plasticity of the rigid spring piece 17, the heading vibration is relieved through the stress deformation of the rigid spring piece 17, and the vibration amplitude and the vibration load are reduced.
FIG. 4 is a schematic structural diagram of a ball screw inerter. As shown in fig. 4, the ball screw inerter b includes a flywheel chamber 20, a flywheel 26, a screw 25, a bearing support 27, a screw support 28, and a stroke chamber 29. The topmost end of the screw rod 25 and a certain distance away from the topmost end are both provided with threads, the certain distance is the length of the flywheel 26, and the cross section of the screw rod is polygonal. The flywheel 26 is placed in the flywheel chamber 20, a polygon corresponding to the cross-sectional shape of the upper end of the lead screw is arranged in the flywheel chamber, the lead screw 25 penetrates through the flywheel 26, the lower end of the lead screw is fixed through a fourth gasket 23 and a second nut 24, and a bearing support seat 27 is arranged on the lead screw; and the upper end thereof is fixed by a third washer 21 and a first nut 22. The flywheel chamber 20 is sealed by a flywheel chamber cover 19. The end of the screw 25 is mounted on the stroke chamber 29 through the screw support 28. The stroke chamber 29 is hollow and forms a movable passage of the lead screw 25. Axial force transmitted by resistance generated by ground course sliding acts on two ends of the ball screw inertia container b, so that the screw 25 and the nut generate relative displacement, linear motion of the screw 25 is converted into rotary motion of the flywheel 26 through the ball screw pair, and further potential energy is converted into kinetic energy, so that brake induced vibration energy is effectively absorbed; the utility model discloses in, ball is used to vertical drawing pressure that ball received among the container b and turns into rotary motion with linear motion, and the rotatory energy dissipation that realizes of lead screw drive flywheel. The rigid spring piece damper a limits longitudinal displacement and can play a role in damping vibration. The inertia container and the spring piece device are combined, so that the low-frequency brake induced vibration energy can be effectively absorbed, the stability of the undercarriage structure is ensured, the service lives of the brake device and the undercarriage device are prolonged, the ground running stability of the airplane is improved, and the flight safety of the airplane is ensured.
The above detailed description describes the preferred embodiments of the present invention, but the present invention is not limited to the details of the above embodiments, and the technical concept of the present invention can be implemented with various equivalent transformations (such as quantity, shape, position, etc.), which all belong to the protection of the present invention.
Claims (5)
1. An aircraft landing gear with a buffeting resisting device comprises a main landing gear, wheels and an upper drag brace rod (2); the main landing gear comprises a main landing gear strut outer cylinder (1) and a main landing gear piston rod (6), and the main landing gear piston rod (6) is slidably mounted in the main landing gear strut outer cylinder (1); the top of the main landing gear strut outer cylinder (1) is fixedly arranged with a machine body, and the tail end of a main landing gear piston rod (6) is provided with a machine wheel; an upper torsion arm (3) is hinged to the lower end of the main landing gear strut outer cylinder (1), a lower torsion arm (4) is hinged to the lower end of the main landing gear piston rod (6), and the upper torsion arm (3) is hinged to the lower torsion arm (4); the method is characterized in that: the upper end of the lower resistance buffeting device (A) is hinged with the upper resistance stay bar (2), and the lower end of the lower resistance buffeting device (A) is hinged with the lower end of the main landing gear strut outer cylinder (1);
the lower resistance anti-buffeting device (A) comprises an upper connecting piece (31), a rigid spring piece damper (a), a ball screw inertial container (b) and a lower connecting piece (30); the lower end of the upper resistance stay bar (2) is hinged with the upper connecting piece (31); the lower connecting piece (30) is hinged with the lower end of the main landing gear strut outer cylinder (1); the rigid spring piece damper (a) and the ball screw inertial container (b) are fixed between the upper connecting piece and the lower connecting piece through screws.
2. An aircraft landing gear according to claim 1, wherein: the rigid spring piece damper (a) comprises an upper fixed stay bar (8), a first threaded bushing (14), a connecting bolt (15), a second threaded bushing (16), a rigid spring piece (17) and a lower fixed stay bar (18); the connecting bolt (15) is provided with a nut, the tail end of the connecting bolt (15) is provided with a thread, the connecting bolt (15) sequentially penetrates through the first thread bushing (14), the rigid spring piece (17) and the second thread bushing (16), and the tail ends of the connecting bolt (15) are fixedly connected through a nut (13); the thread is arranged in the upper fixing support rod (8), the thread is arranged in the lower fixing support rod (18), and the first thread bushing (14) and the second thread bushing (16) are fixedly connected with the upper fixing support rod (8) and the lower fixing support rod (18) through threads respectively.
3. An aircraft landing gear according to claim 2, wherein: and a gasket and a bushing are respectively arranged at the joint of the connecting bolt (15) and the first threaded bushing (14) and the second threaded bushing (16).
4. An aircraft landing gear according to claim 1, wherein: the ball screw inertial container (b) comprises a flywheel chamber (20), a flywheel (26), a screw (25), a bearing support seat (27), a screw support seat (28) and a stroke chamber (29); the uppermost end of the screw rod (25) and a set distance away from the uppermost end are both provided with threads, the distance is the length of the flywheel (26), and the section of the screw rod is polygonal; the flywheel (26) is placed in the flywheel chamber (20), a polygon corresponding to the cross section of the upper end of the lead screw (25) is formed in the flywheel chamber, the lead screw (25) penetrates through the flywheel (26), the lower end of the lead screw is fixed through a nut, a bearing support seat (27) is installed at the lower end of the lead screw, and the upper end of the lead screw is fixed through a nut; the tail end of the lead screw (25) is arranged on the stroke chamber (29) through the lead screw supporting seat (28); the stroke chamber (29) is hollow, and forms a movable channel of the lead screw (25).
5. An aircraft landing gear according to claim 4, wherein: the flywheel chamber (20) is sealed by a flywheel chamber cover (19).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920038641.4U CN210101973U (en) | 2019-01-10 | 2019-01-10 | Aircraft landing gear with buffeting resisting device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920038641.4U CN210101973U (en) | 2019-01-10 | 2019-01-10 | Aircraft landing gear with buffeting resisting device |
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| Publication Number | Publication Date |
|---|---|
| CN210101973U true CN210101973U (en) | 2020-02-21 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920038641.4U Withdrawn - After Issue CN210101973U (en) | 2019-01-10 | 2019-01-10 | Aircraft landing gear with buffeting resisting device |
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| CN (1) | CN210101973U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109774925A (en) * | 2019-01-10 | 2019-05-21 | 南京航空航天大学 | A kind of anti-undercarriage for buffeting device of band |
-
2019
- 2019-01-10 CN CN201920038641.4U patent/CN210101973U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109774925A (en) * | 2019-01-10 | 2019-05-21 | 南京航空航天大学 | A kind of anti-undercarriage for buffeting device of band |
| CN109774925B (en) * | 2019-01-10 | 2024-04-30 | 南京航空航天大学 | Airplane landing gear with anti-buffeting device |
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Granted publication date: 20200221 Effective date of abandoning: 20240430 |
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| AV01 | Patent right actively abandoned |
Granted publication date: 20200221 Effective date of abandoning: 20240430 |
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| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |