CN109774925B - Airplane landing gear with anti-buffeting device - Google Patents
Airplane landing gear with anti-buffeting device Download PDFInfo
- Publication number
- CN109774925B CN109774925B CN201910022431.0A CN201910022431A CN109774925B CN 109774925 B CN109774925 B CN 109774925B CN 201910022431 A CN201910022431 A CN 201910022431A CN 109774925 B CN109774925 B CN 109774925B
- Authority
- CN
- China
- Prior art keywords
- landing gear
- buffeting
- main landing
- hinged
- flywheel
- Prior art date
- 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.)
- Active
Links
- 230000002265 prevention Effects 0.000 claims abstract description 9
- 238000000034 method Methods 0.000 claims description 3
- 238000010586 diagram Methods 0.000 description 3
- 239000000725 suspension Substances 0.000 description 3
- 238000006073 displacement reaction Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 230000021715 photosynthesis, light harvesting Effects 0.000 description 1
- 238000005381 potential energy Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
Landscapes
- Transmission Devices (AREA)
- Vibration Dampers (AREA)
Abstract
The invention discloses an aircraft landing gear with a buffeting prevention device, which comprises a main landing gear, wheels and an upper resistance stay bar (2); the lower resistance anti-buffeting device (A) is hinged with the upper resistance stay bar (2) at the upper end and the lower end of the lower resistance anti-buffeting device 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, so that dissipation of buffeting state of longitudinal ground sliding of the landing gear is realized, and serious buffeting during ground sliding of an airplane is solved; and the vibration energy induced by the low-frequency brake can be effectively absorbed, the vibration amplitude and the vibration load are greatly reduced, and the problems that buffeting is aggravated when riding, the parts are damaged and the service life is shortened are solved.
Description
Technical Field
The invention relates to the field of longitudinal buffeting of an aircraft landing gear, in particular to an aircraft landing gear with an anti-buffeting device.
Background
The low-frequency brake induced vibration of the main landing gear of the aircraft is also called buffeting phenomenon, and the buffeting vibration frequency is generally below 30 Hz. In the whole running braking process of the aircraft main landing gear after the landing gear wheel is grounded, under the action of a braking system, the landing gear is subjected to buffeting phenomenon while receiving the changed ground tire force due to the factors of ground binding force change caused by braking force excitation, flexibility of a main landing gear strut, non-rigid connection of the main landing gear and a machine body connection part, elasticity of a tire and the like. Landing gear buffeting can exacerbate jolting during riding, can cause damage to related components, generate fatigue cracks or fractures, shorten the service life of a landing gear system, and can also induce ground running safety accidents of an aircraft. Therefore, research on anti-buffeting problem of the landing gear is of great importance to the flight quality of the aircraft.
The inertial container has the characteristics of phase advance, high pass frequency and low pass frequency resistance, and university of Cambridge, england, firstly proposes the concept of the inertial container in 2002, and through ten years of development, the inertial container has been gradually applied to earthquake-proof buildings, vehicle suspensions, trains and landing gear shimmy systems. The inertial container for the heavy-duty vehicle with adjustable inertial coefficient disclosed as a suspension vibration energy driving braking system with the publication number of CN108468625A and an inertial container for the heavy-duty vehicle with the publication number of CN108488299A are used for a vehicle suspension, and the fact that the inertial container device is mature and reliable is explained. The spring piece has the characteristics of phase lag, low pass frequency and high resistance. The two are reasonably and optimally combined, so that the longitudinal buffeting phenomenon of the main undercarriage can be effectively relieved and restrained.
In order to solve the buffeting problem of the landing gear of the aerospace plane, the inertial container assembly is used for a main landing gear low-frequency brake induced vibration system, and the vibration damper consisting of the inertial container and the rigid spring piece damper with the dissipation function on energy is adopted, so that low-frequency vibration energy can be effectively absorbed, the vibration amplitude and the vibration load are greatly reduced, and the dynamic performance of the system is improved.
Disclosure of Invention
The invention aims to: aiming at the defects, the invention provides the aircraft landing gear with the anti-buffeting device, and the ball screw inertial container and the rigid spring piece damper are connected in parallel, so that the forward and backward vibration phenomenon of the landing gear in the braking process of the aircraft can be effectively reduced, and the resonance problem of the braking device is avoided.
An aircraft landing gear with a buffeting prevention device comprises a main landing gear, wheels and an upper resistance stay bar; 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 arranged in the main landing gear strut outer cylinder; the top of the main landing gear strut outer cylinder is fixedly arranged with the main body, and the tail end of the main landing gear piston rod is provided with an organic wheel; an upper torque arm is hinged to the lower end of the main landing gear strut outer cylinder, a lower torque arm is hinged to the lower end of the main landing gear piston rod, and the upper torque arm is hinged to the lower torque arm; the lower resistance anti-buffeting device is hinged with the upper resistance stay bar, and the lower end of the lower resistance anti-buffeting device is hinged with the lower end of the main landing gear strut outer cylinder;
The lower resistance buffeting prevention device comprises an upper connecting piece, a rigid spring piece damper and a lower connecting piece; the lower end of the upper resistance stay bar 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 fixed between the upper connecting piece and the lower connecting piece through screws.
The rigid spring piece damper comprises an upper fixing stay bar, a first threaded bushing, a connecting bolt, a second threaded bushing, a rigid spring piece and a lower fixing stay bar; the connecting bolt is provided with a nut, threads are arranged at the tail end of the connecting bolt, the connecting bolt sequentially penetrates through the first threaded bushing, the rigid spring piece and the second threaded bushing, and the tail ends of the connecting bolt are fixedly connected through the nuts; the upper fixing stay bar is internally provided with threads, the lower fixing stay bar is internally provided with threads, and the first threaded bushing and the second threaded bushing are respectively fixedly connected with the upper fixing stay bar and the lower fixing 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 support seat, a screw support seat and a stroke chamber; threads are arranged at the uppermost end of the screw rod and at a set distance 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 screw rod is arranged in the flywheel chamber, the screw rod penetrates through the flywheel, the lower end of the screw rod is fixed through a nut, a bearing supporting seat is arranged on the flywheel, and the upper end of the screw rod is fixed through the nut; the tail end of the screw rod is arranged on the travel chamber through the screw rod supporting seat; the travel chamber is hollow, and a movable channel of the screw rod is formed.
And the flywheel chamber is sealed by a flywheel chamber cover.
The beneficial effects are that:
(a) Dissipation of buffeting states of longitudinal ground sliding of the landing gear is achieved, and the problem of serious buffeting during ground sliding of an airplane 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 that buffeting aggravates jolting phenomenon in riding and parts are damaged and service life is shortened.
(C) The triangular structure formed by the lower resistance anti-buffeting device, the main support of the landing gear and the upper resistance stay bar can effectively improve the dynamic stability of the landing gear system.
Drawings
FIG. 1 is a schematic view of an aircraft landing gear with anti-buffeting device;
FIG. 2 is a left side view of an aircraft landing gear with anti-buffeting devices;
FIG. 3 is a schematic view of a rigid leaf spring damper construction;
FIG. 4 is a schematic structural diagram of a ball screw inertial container;
FIG. 5 is a schematic diagram of the structural connection of the lower resistance anti-buffeting device;
Reference numerals in the figures: 1. the main landing gear strut outer cylinder, 2, an upper resistance 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 fixed nut, 14, a first threaded bushing, 15, a connecting bolt, 16, a second threaded bushing, 17, a rigid spring piece, 18, a lower fixed stay, 19, a flywheel chamber 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, 28, a screw support, 29, a travel chamber, 30, a lower connector, 31, an upper connector, a lower resistance anti-buffeting device, a rigid spring piece damper, b, a ball screw container.
Detailed Description
The invention is further elucidated below in connection with the drawings and the specific embodiments.
Fig. 1 is a schematic structural view of an aircraft landing gear with a buffeting prevention device, and fig. 2 is a left side view of the aircraft landing gear with the buffeting prevention device. As shown in fig. 1 and 2, the aircraft landing gear with the buffeting prevention device comprises a main landing gear, wheels, an upper resistance stay bar 2 and a lower resistance buffeting prevention 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 arranged 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 arranged with the machine body. At the end of the main landing gear piston rod 6 is mounted an impeller via a bearing, said impeller comprising a hub 7 and a tyre 5 arranged on said hub 7. An upper torque arm 3 is hinged to the lower end of the main landing gear strut outer cylinder 1, a lower torque arm 4 is hinged to the lower end of the main landing gear piston rod 6, and the upper torque arm 3 is hinged to the lower torque 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-resisting device A; the lower resistance buffeting resisting device A is hinged with the lower end of the main landing gear strut outer cylinder 1. The lower resistance buffeting prevention 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 lug 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 a rigid leaf spring damper. As shown in fig. 3, the rigid spring piece damper a includes an upper fixing stay 8, a first threaded bushing 14, a connecting bolt 15, a second threaded bushing 16, a rigid spring piece 17, and a lower fixing stay 18. The connecting bolt 15 has a nut, a thread is provided at the end of the connecting bolt 15, the connecting bolt 15 sequentially passes through the first threaded bushing 14, the rigid spring piece 17 and the second threaded bushing 16, and the ends thereof are fixedly connected by a fixing nut (13). In the present invention, a washer and a bushing are provided at the connection of the connection bolt 15 with the first and second threaded bushings 14 and 16, respectively. The upper fixing stay bar 8 is internally provided with threads, the lower fixing stay bar 18 is internally provided with threads, and the first threaded bushing 14 and the second threaded bushing 16 are respectively fixedly connected with the upper fixing stay bar 8 and the lower fixing stay bar 18 through threads. Therefore, the ground course resistance transmitted to the lower resistance anti-buffeting device acts on the rigid spring piece 17, buffeting phenomenon of the landing gear can be effectively relieved through elasticity and plasticity of the rigid spring piece 17, and the rigid spring piece 17 is stressed to deform to relieve course vibration, so that vibration amplitude and vibration load are reduced.
Fig. 4 is a schematic structural diagram of the ball screw inertial container. As shown in fig. 4, the ball screw inertial container 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. Threads are arranged at the uppermost end of the lead screw 25 and at a certain distance from the uppermost end, the certain distance is the length of the flywheel 26, and the section of the lead screw 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 screw rod is arranged in the flywheel chamber, the screw rod 25 passes through the flywheel 26, the lower end of the screw rod is fixed by the fourth gasket 23 and the second nut 24, and a bearing support seat 27 is arranged in the screw rod; the upper end of which is fixed by a third washer 21 and a first nut 22. Sealed on the flywheel chamber 20 by a flywheel chamber cover 19. The end of the screw 25 is mounted on the travel chamber 29 by the screw support 28. The stroke chamber 29 is hollow, and forms a movable passage of the screw 25. The axial force transmitted by the resistance generated by the ground heading sliding acts on the two ends of the ball screw inertial container b, so that the screw 25 and the nut generate relative displacement, the linear motion of the screw 25 is converted into the rotary motion of the flywheel 26 through the ball screw pair, and potential energy is further converted into kinetic energy, and therefore brake induced vibration energy is effectively absorbed; in the invention, the longitudinal pulling pressure applied to the ball screw in the ball screw inertial container b converts linear motion into rotary motion, and the screw drives the flywheel to rotate so as to realize energy dissipation. The rigid spring piece damper a limits the longitudinal displacement and can play a role in vibration reduction. The inertial container and the spring leaf device are combined, so that low-frequency brake induced vibration energy can be effectively absorbed, the stability of a landing gear structure is guaranteed, the service lives of the brake device and the landing gear device are prolonged, the ground running stability of an airplane is improved, and the flight safety of the airplane is guaranteed.
The preferred embodiments of the present invention have been described in detail above, but the present invention is not limited to the specific details of the above embodiments, and various equivalent changes (such as number, shape, position, etc.) may be made to the technical solution of the present invention within the scope of the technical concept of the present invention, and these equivalent changes all belong to the protection of the present invention.
Claims (4)
1. An aircraft landing gear with a buffeting prevention device comprises a main landing gear, wheels and an upper resistance stay bar (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 arranged in the main landing gear strut outer cylinder (1); the top of the main landing gear strut outer cylinder (1) is fixedly arranged with the machine body, and the tail end of the main landing gear piston rod (6) is provided with an organic wheel; an upper torque arm (3) is hinged to the lower end of the main landing gear strut outer cylinder (1), a lower torque arm (4) is hinged to the lower end of the main landing gear piston rod (6), and the upper torque arm (3) is hinged to the lower torque arm (4); the method is characterized in that: the lower resistance anti-buffeting device (A) is hinged with the upper resistance stay bar (2) at the upper end and the lower end of the lower resistance anti-buffeting device is hinged with the lower end of the main landing gear strut outer cylinder (1);
The lower resistance buffeting-resistant 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;
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 travel chamber (29); threads are arranged at the uppermost end of the screw rod (25) and at a set distance from the uppermost end, 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-sectional shape of the upper end of the screw rod (25) is arranged in the flywheel chamber, the screw rod (25) penetrates through the flywheel (26), the lower end of the screw rod is fixed through a nut, a bearing support seat (27) is arranged, and the upper end of the screw rod is fixed through the nut; the tail end of the screw rod (25) is arranged on the travel chamber (29) through the screw rod supporting seat (28); the travel chamber (29) is hollow, and forms a movable channel of the screw rod (25).
2. An aircraft landing gear according to claim 1, wherein: the rigid spring piece damper (a) comprises an upper fixing 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 fixing stay bar (18); the connecting bolt (15) is provided with a nut, threads are arranged at the tail end of the connecting bolt (15), the connecting bolt (15) sequentially penetrates through the first threaded bushing (14), the rigid spring piece (17) and the second threaded bushing (16), and the tail ends of the connecting bolt are fixedly connected through the nut (13); the upper fixing support rod (8) is internally provided with threads, the lower fixing support rod (18) is internally provided with threads, and the first threaded bushing (14) and the second threaded 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: a gasket and a bushing are respectively arranged at the connection part 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: is sealed on the flywheel chamber (20) by a flywheel chamber cover (19).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910022431.0A CN109774925B (en) | 2019-01-10 | 2019-01-10 | Airplane landing gear with anti-buffeting device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910022431.0A CN109774925B (en) | 2019-01-10 | 2019-01-10 | Airplane landing gear with anti-buffeting device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109774925A CN109774925A (en) | 2019-05-21 |
| CN109774925B true CN109774925B (en) | 2024-04-30 |
Family
ID=66500099
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910022431.0A Active CN109774925B (en) | 2019-01-10 | 2019-01-10 | Airplane landing gear with anti-buffeting device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109774925B (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB832005A (en) * | 1957-06-24 | 1960-04-06 | Gordon Winston Yarber | Improvements in and relating to brake control systems |
| EP0607721A1 (en) * | 1992-12-28 | 1994-07-27 | Messier Bugatti | Retractable landing-gear for wide-body aircraft |
| JP2007112408A (en) * | 2005-10-19 | 2007-05-10 | Jun Toyama | Method and device for giving wheel of aircraft rotational speed according to speed upon landing and achieving smooth landing |
| CN107054630A (en) * | 2016-02-10 | 2017-08-18 | 赛峰起落架系统公司 | Aircraft landing gear including main damper and antidetonation time damper |
| CN210101973U (en) * | 2019-01-10 | 2020-02-21 | 南京航空航天大学 | Aircraft landing gear with buffeting resisting device |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2563826A (en) * | 2017-06-19 | 2019-01-02 | Airbus Operations Ltd | Landing Gear |
-
2019
- 2019-01-10 CN CN201910022431.0A patent/CN109774925B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB832005A (en) * | 1957-06-24 | 1960-04-06 | Gordon Winston Yarber | Improvements in and relating to brake control systems |
| EP0607721A1 (en) * | 1992-12-28 | 1994-07-27 | Messier Bugatti | Retractable landing-gear for wide-body aircraft |
| JP2007112408A (en) * | 2005-10-19 | 2007-05-10 | Jun Toyama | Method and device for giving wheel of aircraft rotational speed according to speed upon landing and achieving smooth landing |
| CN107054630A (en) * | 2016-02-10 | 2017-08-18 | 赛峰起落架系统公司 | Aircraft landing gear including main damper and antidetonation time damper |
| CN210101973U (en) * | 2019-01-10 | 2020-02-21 | 南京航空航天大学 | Aircraft landing gear with buffeting resisting device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109774925A (en) | 2019-05-21 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109747816B (en) | Undercarriage with oil-gas buffer type longitudinal buffeting vibration damper | |
| CN210149548U (en) | Undercarriage with oil gas buffering type longitudinal buffeting vibration damper | |
| CN106428535A (en) | Nose landing gear of unmanned aerial vehicle | |
| CN203512061U (en) | Impact reducing structure suitable for small spacecraft | |
| CN103523212A (en) | Nose landing gear of aircraft | |
| CN202783777U (en) | Unmanned aerial vehicle undercarriage | |
| CN206299736U (en) | Shock damper | |
| CN108454834B (en) | Buffering type landing gear for unmanned helicopter | |
| US20170217574A1 (en) | Suspension For Aircraft Tail Wheel | |
| US2559451A (en) | Landing gear with drag strut dynamic damper | |
| CN104321252A (en) | Aircraft brake assembly | |
| CN204136914U (en) | Buffer device for collision | |
| CN109774925B (en) | Airplane landing gear with anti-buffeting device | |
| CN210101973U (en) | Aircraft landing gear with buffeting resisting device | |
| US2233191A (en) | Aircraft landing gear | |
| CN211844888U (en) | Helicopter is with effectual support that rises and falls of buffering | |
| CN103523209A (en) | Retractable main landing frame for small aircrafts | |
| CN206265293U (en) | A kind of unmanned plane nose-gear | |
| CN104029578A (en) | Automobile suspension system | |
| CN108656887B (en) | Automobile chassis with suspension system | |
| CN203157648U (en) | Balanced suspension system using cone-shaped rubber bearings | |
| CN112722251B (en) | Multi-stage buffering anti-crosswind skid landing device and working method thereof | |
| CN115435042A (en) | Limiting method of spherical hinge for suspension vibration reduction | |
| CN204895841U (en) | Be provided with an arm -type main landing gear of buffer | |
| CN107387627A (en) | A kind of automobile damper rubber support |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |