CN112623201B - Electric turning and shimmy reducing mechanism with double redundancies and aircraft landing gear - Google Patents
Electric turning and shimmy reducing mechanism with double redundancies and aircraft landing gear Download PDFInfo
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- CN112623201B CN112623201B CN202011468210.5A CN202011468210A CN112623201B CN 112623201 B CN112623201 B CN 112623201B CN 202011468210 A CN202011468210 A CN 202011468210A CN 112623201 B CN112623201 B CN 112623201B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/50—Steerable undercarriages; Shimmy-damping
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/50—Steerable undercarriages; Shimmy-damping
- B64C25/505—Shimmy damping
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
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- 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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Abstract
The invention discloses a dual-redundancy electric turning and swing reducing mechanism and an aircraft landing gear, wherein the mechanism comprises a driving motor, an outer cylinder, a rotating cylinder and a piston rod; the outer barrel is provided with a first stepped hole and a second stepped hole communicated with the lower end of the outer barrel along the axial direction of the outer barrel, the driving motor is fixed in the first stepped hole, the upper part of the rotating barrel is sleeved in the second stepped hole, the rotating barrel can rotate in the circumferential direction relative to the outer barrel component but cannot move axially, and the upper end of the rotating barrel is in transmission connection with the driving motor component; the upper part of the piston rod is provided with a piston which is hermetically and slidably arranged in the rotary cylinder, and the lower part of the piston rod extends out of the rotary cylinder and is provided with a wheel shaft; an anti-torque arm component is connected between the lower part of the rotary cylinder and the lower part of the piston end. The mechanism replaces the traditional hydraulic driving turning and oil damping shimmy damping mechanism, reduces the total weight and the failure rate of the undercarriage, simplifies the structure of a turning shimmy damping system and controls, and meets the requirements of dual redundancy, safety, maintainability, high working efficiency and low cost of the modern airplane on the undercarriage.
Description
Technical Field
The invention relates to the technical field of aircraft landing gears, in particular to a double-redundancy electric turning and swing reducing mechanism and an aircraft landing gear.
Background
The turning and shimmy reducing system of the undercarriage of the airplane (particularly a large and medium airplane) still adopts hydraulic driving and oil damping at present, and a hydraulic oil source, a hydraulic pump, a plurality of hydraulic control valves, a hydraulic control executing device, a connecting oil pipe, an emergency backup device and the like need to be configured, so that the problems of complex operation and control, large and complicated structure, large energy loss, more fault points and difficult maintenance exist, and the turning and shimmy reducing system of the undercarriage is low in reliability, safety, maintainability and supportability, more faults and difficult diagnosis and is large in weight.
In order to comprehensively improve tactical performance of modern airplanes, particularly modern military aircraft, a traditional hydraulic drive and oil-liquid damping type landing gear turning and shimmy damping system cannot meet the technical development requirements on double redundancy and safety, the failure rate is low, diagnosis and maintenance are easy, the structure integration is simple, the weight is low, and the system operation is simple.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provides an electrically driven double-redundancy electric turning and swing reducing mechanism to replace a hydraulic source, a control valve, an execution accessory, a pipeline, oil and the like (comprising an emergency hydraulic source, a control valve, a pipeline and the like) required by the traditional hydraulically driven turning and oil damping swing reducing mechanism, so that the undercarriage has double redundancies, safety, maintainability, working efficiency and low comprehensive cost while the total weight and failure rate of the undercarriage are reduced, the structure of a turning system is simplified, and turning and swing reducing control is carried out. In addition, an aircraft landing gear with the dual-redundancy electric turning and pendulum reducing mechanism is further provided.
In order to solve the technical problems, the invention adopts the following technical scheme:
a double-redundancy electric turning and swing reducing mechanism comprises a driving motor assembly, an outer barrel assembly, a rotary barrel and a piston rod; the outer barrel assembly is provided with a first stepped hole and a second stepped hole communicated with the lower end of the first stepped hole along the axial direction of the outer barrel assembly, the driving motor assembly is fixed in the first stepped hole, the upper part of the rotary barrel is sleeved in the second stepped hole, the rotary barrel can rotate circumferentially relative to the outer barrel assembly but cannot move axially, and the upper end of the rotary barrel is in transmission connection with the driving motor assembly; the upper part of the piston rod is provided with a piston which is hermetically and slidably arranged in the rotary cylinder, and the lower part of the piston rod extends out of the rotary cylinder and is provided with a wheel shaft; and an anti-torque arm assembly is connected between the lower part of the rotary cylinder and the lower part of the piston end.
The outer cylinder of the undercarriage buffer is fixedly arranged on an airplane body, when the airplane needs to turn during sliding, a main control computer of the airplane sends electric energy to the driving motor component, the driving motor component drives the rotating cylinder matched with the driving motor component to rotate after being electrified, and the rotating cylinder, the anti-torsion arm component and the piston rod are axial rotation linkage bodies, so that the piston rod and the wheel shaft on the piston rod rotate together, and the undercarriage turning function is completed.
When the airplane slides at a high speed, the ground load enables the piston rod to swing through the airplane wheel and the wheel shaft of the piston rod, the rotary cylinder, the anti-torsion arm assembly and the piston rod are axial rotation linkage bodies, so that the rotary cylinder swings and drives the output shaft of the driving electric assembly to rotate, the speed reducer and the motor rotor in the driving motor assembly are driven to rotate in a reverse direction, the piston rod is stopped from swinging and the swinging trend of the piston rod is reduced through heating and consuming kinetic energy, and the damping and swinging reduction function of the undercarriage is completed.
As a further improvement of the above technical solution:
the driving motor assembly is a double-winding motor assembly. When the single winding of the motor fails, the other single winding can also enable the motor component to be electrified to act, and the functions of emergency turning and swing reduction are completed, so that the function of backup emergency turning is realized.
The bottom of the outer circumferential surface of the outer cylinder assembly is provided with an ear platform extending outwards in the radial direction, the bottom end surface of the outer cylinder assembly is provided with a third step hole extending to the ear platform, the outer circumferential surface of the rotary cylinder is provided with a circular boss extending outwards in the radial direction, and the circular boss extends into the third step hole; an angular displacement sensor is installed on the lug boss, a feedback gear is arranged at the position, below the angular displacement sensor, of the third step hole, and an input shaft of the angular displacement sensor penetrates through the lug boss and then is in transmission connection with the feedback gear; and one side of the circular boss facing the feedback gear is provided with straight teeth which are in meshing transmission with the feedback gear.
Therefore, when the rotary cylinder rotates, the feedback gear is driven to rotate through the straight cylindrical teeth of the circular boss, so that the output shaft of the angular displacement sensor is driven to rotate, and the angular displacement sensor feeds back the rotation information of the wheel shaft to the main control computer of the airplane in real time.
The feedback gear is arranged on a gear seat, and the gear seat is detachably arranged at the bottom of the outer barrel component.
A first support ring is arranged between the lower end part of the rotary cylinder and the inner wall of the second stepped hole, a second support ring is arranged between the upper end part of the rotary cylinder and the inner wall of the second stepped hole, a second counter bore for accommodating the second support ring is arranged at the upper end part of the second stepped hole, and a first counter bore for accommodating the first support ring is arranged at the lower end part of the second stepped hole; the lower end of the first supporting ring is provided with a shaft shoulder which extends outwards in the radial direction, and the shaft shoulder is abutted with the circular boss;
the middle section of the plunger is provided with a step extending outwards in the radial direction, and the upper end face of the step is provided with a support ring abutted against the top wall of the inner cavity of the rotary cylinder.
In order to realize better buffer function, the device also comprises an oil needle assembly and a plunger with an axial through hole; the upper end surface of the piston rod is provided with a blind hole, the lower section of the plunger extends into the blind hole, the middle section of the plunger is positioned in the rotary cylinder, the upper section of the plunger penetrates through the driving motor assembly and the outer cylinder assembly and is fixedly connected with the outer cylinder assembly, and the upper end of the plunger is connected with a filling nozzle communicated with the inner cavity of the plunger; the upper end of the oil needle assembly is slidably arranged in the plunger, and the lower end of the oil needle assembly is fixed at the bottom of the blind hole.
Proper oil liquid is injected into the undercarriage buffer through the filling nozzle, high-pressure nitrogen is filled into the undercarriage buffer, when the undercarriage buffer is compressed, the oil needle assembly penetrates through the hole of the plunger to form an oil through ring, and the oil liquid in the undercarriage buffer generates resistance through the oil through ring, consumes energy and achieves a buffering function.
The lower end of the plunger is provided with a damping valve, and the damping valve is provided with a central through hole through which the oil needle assembly passes.
And a shaft sleeve is arranged between the piston rod and the rotary cylinder, is positioned below the piston and is fixed on the inner wall of the rotary cylinder.
The outer barrel component comprises an outer barrel and an end cover for sealing an opening at the upper end of the outer barrel.
As a general inventive concept, the present invention also provides an aircraft landing gear including the above dual-redundancy motorized turning and shimmy reduction mechanism.
Compared with the prior art, the invention has the advantages that:
the invention adopts the structure integration technology, and the bifilar motor component, the rotary inner cylinder and the like are integrated and arranged in the buffer of the undercarriage of the airplane to form a turning and swing reducing mechanism and a feedback device, so that the functions of turning, swing reducing and emergency action of the airplane under normal conditions are realized, hydraulic sources, control valves, execution accessories, pipelines, oil and the like (comprising emergency hydraulic sources, control valves, pipelines and the like) required by the traditional hydraulically-driven turning and oil damping swing reducing mechanism are replaced, the total weight and the failure rate of the undercarriage are reduced, the structure of a turning system and the turning and swing reducing control are simplified, and the requirements of the modern airplane on dual redundancy, safety, maintainability, working efficiency and low comprehensive cost of the undercarriage are met.
Drawings
FIG. 1 is a schematic view of the external configuration and assembly location of the dual redundant motorized turn and roll reduction mechanism of the present invention.
Fig. 2 is a sectional view a-a of fig. 1.
Fig. 3 is a schematic structural view of the outer tub.
Fig. 4 is a sectional view B-B of fig. 3.
Fig. 5 is a top view of fig. 3.
Fig. 6 is a bottom view of fig. 3.
Fig. 7 is a schematic structural diagram of the outer cylinder end cover of the invention.
Fig. 8 is a cross-sectional view C-C of fig. 7.
Fig. 9 is a left side view of fig. 7.
Fig. 10 is a schematic view of the structure of the plunger of the present invention.
Fig. 11 is a top view of fig. 10.
Fig. 12 is a schematic structural view of a rotary cylinder of the present invention.
Fig. 13 is a top view of fig. 12.
Fig. 14 is a schematic view of the construction of the piston rod of the present invention.
Fig. 15 is a top view of fig. 14.
Fig. 16 is a schematic view of the structure of the feedback gear of the present invention.
Fig. 17 is a top view of fig. 16.
Fig. 18 is a schematic structural view of the gear holder of the present invention.
Fig. 19 is a cross-sectional view taken along line D-D of fig. 18.
Fig. 20 is a schematic structural view of a double winding motor assembly of the present invention.
In the figure: 1. the double-winding motor assembly comprises a filling nozzle, 2, a nut, 3, an outer barrel end cover, 4, a bolt, 5, an outer barrel, 6, a rotating barrel, 7, an anti-twisting arm assembly, 8, a plunger, 9, a double-winding motor assembly, 10, a support ring, 11, an angular displacement sensor, 12, a feedback gear, 13, a screw, 14, a gear seat, 15, a piston, 16, a lower shaft sleeve, 17, a clamping key, 18, a damping valve, 19, an oil needle assembly, 20, a piston rod, 21, a first support ring, 22, a second support ring, 23, a bolt, 24, a circular boss with a threaded through hole, 25, a groove, 26, a through hole, 27, a circular lug boss, 28, a first stepped hole, 29, a second counter bore, 30, a second stepped hole, 31, a first counter bore, 32, a circular lug boss stepped small hole, 33, a third stepped hole, 34, a threaded blind hole, 35. the structure comprises a threaded through hole, 36 lug bosses containing through holes, 37 flat slot holes, 38 boss bosses, 39 end cover counter bores, 40 upper-section threaded shafts, 41 flat bosses, 42 annular grooves, 43 seal ring grooves, 44 plunger stepped inner holes, 45 lower-section threaded shafts, 46 threaded holes, 47 spline shafts, 48 rotating cylinder outer walls, 49 round bosses, 50 cylindrical straight teeth, 51 rotating cylinder stepped large holes, 52 key clamping grooves, 53 rotating cylinder double lug plates containing through holes, 54 rotating cylinder stepped large hole bottom end faces, 55 rotating cylinder stepped small holes, 56 piston rod threaded shafts, 57 piston rod blind holes, 58 wheel shafts, 59 piston rod double lug plates containing through holes, 60 gear flat holes, 61 gear shafts, 62 large round bosses, 63 small round bosses, 64 gear mounting holes, 65. through hole, 66, internal spline hole, 67, threaded hole, 68, motor assembly internal through hole.
Detailed Description
The invention is further described below with reference to specific preferred embodiments, without thereby limiting the scope of protection of the invention.
As shown in fig. 1 and 2, the invention mainly comprises an outer cylinder 5, an outer cylinder end cover 3, a driving motor component, a nut 2, a plunger 8, a support ring 10, a rotary cylinder 6, a first support ring 21, a second support ring 22, a piston rod 20, a piston 15, a lower shaft sleeve 16, a clamping key 17, a damping valve 18, an oil needle component 16, an anti-torque arm component 7, an angular displacement sensor 11, a feedback gear 12, a gear seat 14 and a filling nozzle 1, wherein the driving motor component adopts a double-winding motor component 9.
As shown in fig. 1, 3-6, the upper end surface of the outer cylinder 5 is provided with a plurality of circular bosses 24 with threaded through holes, and through grooves 25, which are installed in cooperation with lugs 36 and 38 (see fig. 7 and 8) with through holes provided on the outer cylinder end cover 3, bolts 22 are installed in the threaded through holes of the circular bosses 24 through the through holes of the lugs 36 of the outer cylinder end cover, so as to fix the outer cylinder end cover 3 on the outer cylinder 5, the outer cylinder 5 is provided with a first stepped hole 28 and a stepped small hole (i.e. a second stepped hole) 30, the cylinder wall is provided with a plurality of through holes 26 communicated with the first stepped hole 28, the double-winding motor assembly 9 is installed in the first stepped hole 28 in a cooperation manner, the bolt 4 fixes the double-winding motor assembly 9 in the outer cylinder 5 through the through hole 26, the first counter bore 29 and the second counter bore 31 are provided at the upper and lower ends of the stepped small hole 30, and are respectively installed with the first support ring 21 and the second support ring 22 in a cooperation manner, the outer cylinder 5 is provided with a lug boss which is a circular lug boss 27, a circular lug boss stepped small hole 32 and a third stepped hole 33 are arranged in the lug boss 27 and are respectively used for being matched with and installing the angular displacement sensor 11 and the gear seat 14, the upper end surface of the circular lug boss 27 is provided with a threaded through hole 35 for installing and fixing a screw for installing and fixing the angular displacement sensor 11, the lower end surface of the circular lug boss 27 is provided with a threaded blind hole 34, the screw 13 is installed in the threaded blind hole 34 through a through hole 65 (please refer to fig. 18) arranged on the gear seat 14, and the gear seat is fixed on the circular lug boss of the outer cylinder 5.
As shown in fig. 1 and fig. 7 to 9, the outer cylinder end cover 3 is provided with an end cover counter bore 39 for fitting to the double-winding motor assembly 9, and a flat slot 37 is provided on a bottom end face of the counter bore for fitting to a flat table 41 provided on the plunger 8.
As shown in fig. 1 and 10 to 11, a stepped through hole 44 is formed in the plunger 8, an internal thread 46 is formed at an orifice, the filling nozzle 1 can be installed and used for filling oil and nitrogen gas into the landing gear buffer, the plunger is shaped like a stepped shaft, the upper section shaft is provided with a threaded shaft 40 and a flat platform 41 which are respectively used for installing the nut 2 and the flat slot hole 37 (see fig. 7) for cooperatively installing the outer cylinder end cover 3, so that the plunger can not move and rotate in the axial direction, the upper end surface of the plunger middle section shaft is provided with an annular groove 42 for cooperatively installing the support ring 10, the plunger middle section shaft is provided with a seal ring groove 43 for installing an O-shaped seal ring to realize the seal between the plunger and the rotary cylinder 6, and the plunger lower section shaft is provided with a lower section threaded shaft 45 for fixedly installing the damping valve 18.
As shown in fig. 1 and 12-13, the upper end of the rotary cylinder 6 is provided with a spline shaft 47 for fitting an internal spline hole 66 (see fig. 20) of the dual-winding motor assembly 9, the cylinder wall 48 of the rotary cylinder is provided with a circular boss 49, and the circular boss 48 is provided with straight teeth within an angle range, the straight teeth are provided as straight cylindrical teeth 50, the upper end surface of the circular boss 49 is used for abutting against the shaft shoulder of the first support ring 21 installed in the outer cylinder 5, so that the rotary cylinder 6 cannot move axially upwards, the straight cylindrical teeth 50 are used for being meshed with the feedback gear 12 installed in the circular boss 27 of the outer cylinder 5, the rotary cylinder is provided with a double lug plate 53 with a through hole for fitting with an anti-torque arm assembly, the rotary cylinder is provided with a step hole with a through hole, wherein the large step hole 51 is used for fitting with a middle shaft for installing the plunger 8, the piston 15 and the lower shaft sleeve 16, the small step hole 55 is used for fitting with an upper shaft for installing the plunger 8, the bottom end face 54 of the large stepped hole is in lap contact with the support ring 10 installed in the annular groove 42 of the plunger 8, the rotary cylinder 6 cannot move axially downward when the plunger 8 is installed and fixed, and the annular groove 52 is formed in the large stepped hole 51 and used for installing the snap key 17 to prevent the lower shaft sleeve 16 from moving downward.
As shown in fig. 1 and 14 to 15, the upper end of the piston rod 20 is provided with a threaded shaft 56 for fitting the piston 15, the piston rod is provided with a blind hole 57 for fitting the oil needle assembly 19, the piston rod is provided with a wheel shaft 58 for fitting the wheel, and is also provided with a double lug piece 59 with a through hole for fitting the anti-torque arm assembly 7.
As shown in fig. 1 and 16 to 19, the feedback gear 12 is provided with a gear shaft 61 for fitting in a gear mounting hole 64 provided in the gear base 14, the gear base 14 is provided with a small circular truncated cone 63 for fitting in the third stepped hole 33 of the outer cylinder 5, a screw 13 is mounted in a threaded hole 34 of the outer cylinder 5 through a through hole 65 provided in a large circular truncated cone 62 of the gear base 14, the gear base 14 is fixed on the circular truncated cone 27 of the outer cylinder 5, and the feedback gear 12 is provided with a gear flat hole 60 for fitting in an input shaft of the angular displacement sensor 11.
As shown in fig. 1 and 20, a through hole 68 is formed in the double-winding motor assembly 9 for inserting the upper shaft of the plunger 8, and an inner spline hole 66 for outputting torque of the motor assembly is also formed in the double-winding motor assembly 9 for fitting the spline shaft 47 of the rotary cylinder 6 to drive the rotary cylinder 6 to rotate, and the motor assembly is provided with a plurality of threaded holes 67 for mounting the bolts 4 to fix the double-winding motor assembly 9 in the outer cylinder 5.
A stepped through hole is formed in the outer cylinder 5, the double-winding motor assembly is installed in a first stepped hole 28 of the outer cylinder 5 in a matched mode, bolts fix the double-winding motor assembly in the outer cylinder 5 through a plurality of small holes vertically communicated with the first stepped hole 28, a counter bore is formed in an outer cylinder end cover, a flat slot hole is formed in the end face of the bottom of the hole, the outer cylinder end cover is installed on the double-winding motor assembly in a matched mode through the counter bore, meanwhile, a boss and a plurality of circular bosses with through holes are arranged on the outer cylinder end cover and matched with a groove and a plurality of circular bosses with threaded through holes formed in the upper end face of the first stepped hole 28 of the outer cylinder 5, and the outer cylinder end cover is fixed on the outer cylinder 5 through the circular bosses of the outer cylinder end cover, so that the double-winding motor assembly and the outer cylinder end cover are fixedly installed on the outer cylinder 5; the first and second support rings 22 are countersunk in both ends of the small stepped bore of the outer barrel 5.
The rotary cylinder 6 is sleeved on the plunger 8, the bottom end face of a first step hole 28 of the rotary cylinder 6 is in lap contact with and mounted on a support ring 10 in an annular groove of a middle section shaft of the plunger 8, the rotary cylinder 6 and the plunger 8 are inserted into a small step hole in the outer cylinder 5, an inner through hole of a double-winding motor assembly and a flat groove hole of an outer cylinder end cover, a round boss of the rotary cylinder 6 is in contact with a shaft shoulder of a second support ring 22 in the outer cylinder 5, a flat block of an upper section shaft of the plunger 8 is matched with a flat groove hole of the outer cylinder end cover, a nut 2 is mounted on a threaded shaft of the upper section shaft of the plunger 8, so that the plunger 8 cannot axially rotate and move, the rotary cylinder 6 cannot axially move, a spline shaft of the rotary cylinder 6 is matched with and mounted in an inner spline hole of the double-winding motor assembly, the cylinder wall of the rotary cylinder 6 is matched with inner holes of the first and the second support rings in the outer cylinder 5, a filling nozzle 1 is mounted in the threaded hole of the plunger 8, a damping valve 18 is fixedly mounted on the threaded shaft at the lower end of the plunger 8 through threads, thus, the plunger 8, the rotary cylinder 6, the support ring 10, the filling nozzle 1 and the damping valve 18 are axially mounted in the outer cylinder 5, the rotary cylinder 6 cannot axially move but can rotate, and the plunger 8 is provided with an O-shaped seal ring for sealing between the rotary cylinder 6 and the plunger 8.
The lower shaft sleeve 16 is sleeved on the piston rod 20, the piston 15 is fixedly arranged on the piston rod 20 through threads, the oil needle assembly 19 is arranged in a blind hole 57 of the piston rod 20, the piston 15, the lower shaft sleeve 16 and the piston rod 20 are arranged in a first stepped hole of the rotary cylinder 6 together, meanwhile, the lower end shaft of the plunger 8 is inserted into the blind hole 57 in the piston rod 20, the oil needle assembly 19 is inserted into the damping valve 18 in a matching way, in addition, a clamping key 17 is arranged in an annular groove at the first stepped hole 28 opening of the rotary cylinder 6 and used for limiting the downward movement of the lower shaft sleeve 16, an outer circular shaft and an inner circular hole of the lower shaft sleeve 16 are provided with O-shaped sealing rings which are respectively used for sealing between the lower shaft sleeve 16 and the rotary cylinder 6 and sealing between the lower shaft sleeve 16 and the piston rod 20, and then the piston rod 20, the piston 15 and the oil needle assembly 19 become an axial movement linkage body;
the upper and lower anti-torsion arms of the anti-torsion arm assembly 7 are respectively matched and fixedly installed with the double lug plates of the rotary cylinder 6 and the double lug plates of the piston rod 20 through hinged connecting shafts, so that the rotary cylinder 6, the anti-torsion arm assembly 7, the piston rod 20 and the piston 15 form an axial rotation linkage body.
In addition, the outer cylinder 5 is provided with a circular lug platform 27 parallel to the stepped through hole, a stepped hole is arranged in the circular lug platform 27, the angular displacement sensor 11 and the gear seat 14 are installed in the circular lug platform 27 in a matching way, the upper end surface and the lower end surface of the circular lug platform 27 are provided with a plurality of threaded holes, and screws are fixed on the upper end surface and the lower end surface of the circular lug platform 27 through the installation holes through which the angular displacement sensor 11 and the gear seat 14 pass; the feedback gear 12 is arranged on an inner through hole of the gear seat 14 in a matching way, the feedback gear 12 is provided with a flat hole for matching with an input flat shaft of the angular displacement sensor 11,
the rotary cylinder 6 is provided with a circular boss 49, the circular boss 49 is provided with a cylindrical straight tooth 50 within an angle range and is used for being meshed with a feedback gear 12 installed in a circular lug boss of the outer cylinder 5, when the rotary cylinder 6 rotates, the cylindrical straight tooth 50 of the circular boss 49 drives the feedback gear 12 to rotate, the feedback gear 12 drives an input flat shaft of the angular displacement sensor 11 to rotate, and therefore the angular displacement sensor 11 transmits rotation information of the rotary cylinder 6.
The working principle of the invention is as follows:
the landing gear bumpers were filled with a suitable amount of oil and with high pressure nitrogen as shown in figure 2.
The outer cylinder 5 of the landing gear buffer is fixedly arranged on an airplane body, when the airplane needs to turn during sliding, a main control computer of the airplane sends electric energy to the double-winding motor assembly, the double-winding motor assembly outputs internal spline rotation after being electrified so as to drive a spline shaft of the rotary cylinder 6 matched with the double-winding motor assembly to rotate, the rotary cylinder 6, the anti-twisting arm assembly 7 and the piston rod 20 are axial rotation linkage bodies, so that the piston rod 20 and a wheel shaft 58 on the piston rod rotate together, meanwhile, the straight cylindrical teeth 50 of a circular boss of the rotary cylinder 6 drive an output shaft of the angular displacement sensor 11 to rotate by driving a feedback gear 12 arranged in a fixed outer circular lug boss, and the angular displacement sensor 11 feeds back rotation information of the wheel shaft 58 to the main control computer of the airplane in real time, so that the landing gear turning function is completed.
When the airplane slides at a high speed, the ground load enables the piston rod 20 to swing through the airplane wheel and the wheel shaft of the piston rod 20, the rotating cylinder 6, the anti-twisting arm assembly 7 and the piston rod 20 are axial rotating linkage bodies, so that the rotating cylinder 6 swings and drives the double-winding motor assembly to output internal splines to rotate, a speed reducer and a motor rotor in the double-winding motor assembly are further rotated reversely, the piston rod 20 is prevented from swinging and rotating through heating and kinetic energy consumption, the swinging trend of the piston rod 20 is reduced, and the damping and swinging reduction functions of the landing gear are achieved. Meanwhile, the straight cylindrical teeth 50 of the large circular boss of the rotary cylinder 6 drive the feedback gear 12 installed in the fixed outer circular lug boss to rotate, so as to drive the output shaft of the angular displacement sensor 11 to rotate, and the angular displacement sensor 11 feeds back the rotation information of the wheel shaft to the main control computer of the airplane in real time.
In addition, the motor component is provided with a double-winding motor, which is equivalent to 2 motors connected in series; under normal conditions, 2 motors work at the same time to output rated rotation to drive the rotary cylinder 6, the anti-torsion arm assembly and the piston rod 20 to rotate, so that the turning and swing reducing functions are realized; when any one motor fails, the other motor can still independently and simultaneously work and output rated rotation, so that the emergency turning function of backup is realized, the backup belongs to hot redundancy backup, and a mechanism with dual redundancies coexists is adopted in the invention.
The above description is only for the preferred embodiment of the present application and should not be taken as limiting the present application in any way, and although the present application has been disclosed in the preferred embodiment, it is not intended to limit the present application, and those skilled in the art should understand that they can make various changes and modifications within the technical scope of the present application without departing from the scope of the present application, and therefore all the changes and modifications can be made within the technical scope of the present application.
Claims (9)
1. A double-redundancy electric turning and swing reducing mechanism is characterized by comprising a driving motor component, an outer cylinder component, a rotary cylinder (6) and a piston rod (20); the outer barrel assembly is provided with a first stepped hole (28) and a second stepped hole (30) communicated with the lower end of the first stepped hole (28) along the axial direction of the outer barrel assembly, the driving motor assembly is fixed in the first stepped hole (28), the upper part of the rotary barrel (6) is sleeved in the second stepped hole (30), the rotary barrel (6) can circumferentially rotate relative to the outer barrel assembly but cannot axially move, and the upper end of the rotary barrel (6) is in transmission connection with the driving motor assembly; the upper part of the piston rod (20) is provided with a piston (15) which is arranged in the rotary cylinder (6) in a sealing and sliding manner, and the lower part of the piston rod (20) extends out of the rotary cylinder (6) and is provided with a wheel shaft (58); an anti-torsion arm assembly (7) is connected between the lower part of the rotary cylinder (6) and the lower part of the end of the piston (15);
the bottom of the outer circumferential surface of the outer cylinder component is provided with an ear platform extending outwards in the radial direction, the bottom end surface of the outer cylinder component is provided with a third stepped hole (33) extending to the ear platform, the outer circumferential surface of the rotary cylinder (6) is provided with a circular boss (49) extending outwards in the radial direction, and the circular boss (49) extends into the third stepped hole (33); an angular displacement sensor (11) is mounted on the lug boss, a feedback gear (12) is arranged at the position, below the angular displacement sensor (11), of the third stepped hole (33), and an input shaft of the angular displacement sensor (11) penetrates through the lug boss and then is in transmission connection with the feedback gear (12); and one side of the circular boss (49) facing the feedback gear (12) is provided with straight teeth which are in meshing transmission with the feedback gear (12).
2. The dual-redundancy electric turning and sway mitigation mechanism of claim 1, wherein the drive motor assembly is a dual-winding motor assembly.
3. The dual-redundancy electric turning and shimmy damping mechanism according to claim 1, wherein the feedback gear (12) is mounted on a gear holder (14), and the gear holder (14) is detachably mounted on the bottom of the outer barrel assembly.
4. The dual-redundancy electric turning and pendulum reducing mechanism of claim 1, wherein a first support ring (21) is arranged between the lower end of the rotary drum (6) and the inner wall of the second stepped hole (30), a second support ring (22) is arranged between the upper end of the rotary drum (6) and the inner wall of the second stepped hole (30), the upper end of the second stepped hole (30) is provided with a second counter bore (29) for accommodating the second support ring (22), and the lower end of the second stepped hole (30) is provided with a first counter bore (31) for accommodating the first support ring (21); the lower end of the first supporting ring (21) is provided with a shaft shoulder extending outwards in the radial direction, and the shaft shoulder is abutted with the circular boss (49);
the double-redundancy electric turning and pendulum reducing mechanism further comprises a plunger (8) with an axial through hole, a step extending outwards in the radial direction is arranged at the middle section of the plunger (8), and a support ring (10) abutted to the top wall of the inner cavity of the rotating cylinder (6) is arranged on the upper end face of the step.
5. The dual-redundancy motorized turning and shimmy damping mechanism of claim 4, further comprising an oil needle assembly (19); the upper end face of the piston rod (20) is provided with a blind hole, the lower section of the plunger (8) extends into the blind hole, the middle section of the plunger (8) is positioned in the rotary cylinder (6), the upper section of the plunger (8) penetrates through the driving motor assembly and the outer cylinder assembly and is fixedly connected with the outer cylinder assembly, and the upper end of the plunger (8) is connected with a filling nozzle (1) communicated with the inner cavity of the plunger (8); the upper end of the oil needle assembly (19) is slidably arranged in the plunger (8), and the lower end of the oil needle assembly (19) is fixed at the bottom of the blind hole.
6. The dual-redundancy electric turning and oscillation reducing mechanism according to claim 5, wherein a damping valve (18) is mounted at the lower end of the plunger (8), and a central through hole for the oil supply needle assembly (19) to pass through is formed in the damping valve (18).
7. The dual-redundancy electric turning and oscillation reducing mechanism according to claim 1 or 2, wherein a lower bushing (16) is arranged between the piston rod (20) and the rotary cylinder (6), and the lower bushing (16) is positioned below the piston (15) and fixed on the inner wall of the rotary cylinder (6).
8. The dual-redundancy electric turning and sway reducing mechanism of claim 1 or 2, wherein the outer barrel assembly comprises an outer barrel (5) and an end cap (3) closing an upper end opening of the outer barrel (5).
9. An aircraft landing gear, including a dual-redundancy electrically powered turn and sway mitigation mechanism according to any one of claims 1 to 8.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011468210.5A CN112623201B (en) | 2020-12-14 | 2020-12-14 | Electric turning and shimmy reducing mechanism with double redundancies and aircraft landing gear |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011468210.5A CN112623201B (en) | 2020-12-14 | 2020-12-14 | Electric turning and shimmy reducing mechanism with double redundancies and aircraft landing gear |
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| CN112623201B true CN112623201B (en) | 2022-08-02 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114132524B (en) * | 2021-11-01 | 2024-06-18 | 庆安集团有限公司 | Anti-torsion structure of external linear displacement sensor of actuator |
| JP2023104483A (en) * | 2022-01-18 | 2023-07-28 | 住友精密工業株式会社 | aircraft landing gear |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| FR2899871B1 (en) * | 2006-04-12 | 2008-07-04 | Messier Bugatti Sa | ATTERISSEUR HAVING MULTIPLE ELECTROMECHANICAL ACTUATORS OF ORIENTATION |
| GB0805829D0 (en) * | 2008-04-01 | 2008-04-30 | Goodrich Actuation Systems Ltd | Damping arrangement |
| CN101519120B (en) * | 2009-04-07 | 2010-11-10 | 南京航空航天大学 | Semi-active shimmy damper of undercarriage and control method thereof |
| DE102010055230B4 (en) * | 2010-12-20 | 2022-09-29 | Liebherr-Aerospace Lindenberg Gmbh | Landing gear for an aircraft |
| FR2982843B1 (en) * | 2011-11-18 | 2013-11-29 | Messier Bugatti Dowty | LITTER WITH LOWER LOWER PART |
| CN102602534B (en) * | 2012-04-05 | 2015-04-08 | 中航飞机起落架有限责任公司 | Shimmy damping device for landing gear |
| CN102923300B (en) * | 2012-10-31 | 2015-08-12 | 南京航空航天大学 | Electric drive twin worm formula aircraft nose wheel turning system |
| GB2511856B (en) * | 2013-03-15 | 2015-07-01 | Goodrich Actuation Systems Ltd | Damping arrangement for aircraft landing gear, for example a nosewheel |
| CN105173066B (en) * | 2015-09-21 | 2017-05-10 | 中国运载火箭技术研究院 | Electrically-driven nose wheel steering device for unmanned aerial vehicle |
| CN106218872B (en) * | 2016-07-26 | 2018-06-15 | 中国科学院长春光学精密机械与物理研究所 | A kind of all-electric steering shimmy damping device for unmanned plane nose-gear |
| CN107867394B (en) * | 2017-11-08 | 2020-07-28 | 北京航空航天大学 | Aircraft nose wheel turning driving device |
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