CN116498680B - Electromagnetic damper for aircraft - Google Patents
Electromagnetic damper for aircraft Download PDFInfo
- Publication number
- CN116498680B CN116498680B CN202310612451.XA CN202310612451A CN116498680B CN 116498680 B CN116498680 B CN 116498680B CN 202310612451 A CN202310612451 A CN 202310612451A CN 116498680 B CN116498680 B CN 116498680B
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- Prior art keywords
- shell
- electromagnetic
- sliding
- extrusion
- symmetrically distributed
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- 238000001125 extrusion Methods 0.000 claims abstract description 44
- 230000006698 induction Effects 0.000 claims abstract description 26
- 238000013016 damping Methods 0.000 claims abstract description 21
- 230000000712 assembly Effects 0.000 claims description 8
- 238000000429 assembly Methods 0.000 claims description 8
- 230000017525 heat dissipation Effects 0.000 claims description 6
- 238000009423 ventilation Methods 0.000 claims description 4
- 230000002035 prolonged effect Effects 0.000 abstract description 9
- 230000008878 coupling Effects 0.000 abstract 2
- 238000010168 coupling process Methods 0.000 abstract 2
- 238000005859 coupling reaction Methods 0.000 abstract 2
- 238000010521 absorption reaction Methods 0.000 description 4
- 238000006243 chemical reaction Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000013459 approach Methods 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 230000003111 delayed effect Effects 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
Classifications
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01F—MAGNETS; INDUCTANCES; TRANSFORMERS; SELECTION OF MATERIALS FOR THEIR MAGNETIC PROPERTIES
- H01F5/00—Coils
-
- 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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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F6/00—Magnetic springs; Fluid magnetic springs, i.e. magnetic spring combined with a fluid
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01F—MAGNETS; INDUCTANCES; TRANSFORMERS; SELECTION OF MATERIALS FOR THEIR MAGNETIC PROPERTIES
- H01F27/00—Details of transformers or inductances, in general
- H01F27/08—Cooling; Ventilating
- H01F27/085—Cooling by ambient air
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01F—MAGNETS; INDUCTANCES; TRANSFORMERS; SELECTION OF MATERIALS FOR THEIR MAGNETIC PROPERTIES
- H01F27/00—Details of transformers or inductances, in general
- H01F27/28—Coils; Windings; Conductive connections
- H01F27/2876—Cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F2230/00—Purpose; Design features
- F16F2230/0005—Attachment, e.g. to facilitate mounting onto confer adjustability
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Vibration Prevention Devices (AREA)
Abstract
The invention relates to the field of electromagnetic vibration reduction, in particular to an electromagnetic damper for an aircraft. Including the shell, the shell rigid coupling has the inner shell of symmetric distribution, the equal sliding connection of inner shell of symmetric distribution has the slip cover shell, be provided with the electromagnetic rod in the slip cover shell, the slip cover shell is provided with the screw groove, the electromagnetic rod is provided with the cutting piece, the inner shell rigid coupling has the lug, the lug passes through screw groove and slip cover shell sliding fit, be provided with solenoid in the inner shell, the shell is provided with the radiating subassembly of gas and solenoid in being used for the inner shell, the shell is provided with the extrusion subassembly of symmetric distribution, the extrusion subassembly is used for increasing the damping force of this device, the slip cover shell of symmetric distribution all is provided with the adjusting part that is used for adjusting this device basic damping force. According to the invention, the magnetic induction wires of the electromagnetic rods are matched with the magnetic induction wires of the cutting pieces to generate damping force for collision and cutting of the magnetic induction wires of the electromagnetic coils, so that the extrusion kinetic energy of the aircraft with the ground during landing is ensured to be absorbed, the landing gear of the aircraft is protected, and the service life of the landing gear is prolonged.
Description
Technical Field
The invention relates to the field of electromagnetic shock absorption, in particular to an electromagnetic damper for an aircraft.
Background
In the whole running braking process of an aircraft main landing gear after the landing gear wheel is grounded, under the factors of braking force, ground binding force, elasticity of tires and the like, the landing gear is subjected to the ground tire force and buffeting phenomenon, so that a damper is required to absorb vibration and reduce vibration, and the electromagnetic damper is often applied to the aircraft landing gear with the advantages of high efficiency, high response speed, high reliability and the like.
The traditional electromagnetic damper converts mechanical kinetic energy of an aircraft during landing into internal energy through relative sliding of an electromagnetic rod and a coil, the method has low mechanical kinetic energy conversion efficiency, and when the aircraft landing gear is in contact with the ground, severe shaking still occurs, so that the service life of the aircraft landing gear is reduced, and meanwhile, when the electromagnetic damper converts the mechanical kinetic energy into the internal energy, a large amount of heat is accumulated in the coil, if the electromagnetic damper is not discharged in time, the coil is damaged due to overhigh temperature, and the conversion efficiency of the electromagnetic damper is reduced.
Disclosure of Invention
In order to overcome the defects that the conversion efficiency of mechanical kinetic energy of an electromagnetic damper is low and heat cannot be discharged when an aircraft lands, the invention provides the electromagnetic damper for the aircraft, which solves the problems.
The technical proposal is as follows: the utility model provides an electromagnetic damper for aircraft, including the shell, shell fixedly connected with symmetric distribution's inner shell, the equal sliding connection of symmetric distribution's inner shell has the slip cover shell, be provided with the electromagnetic rod in the slip cover shell, the slip cover shell is provided with the screw groove, the electromagnetic rod is provided with evenly distributed's cutting piece, inner shell fixedly connected with lug, the lug passes through screw groove and slip cover shell sliding fit, be provided with solenoid in the inner shell, the shell is provided with the radiating subassembly of gas and solenoid in being used for the inner shell, symmetric distribution's slip cover shell all is provided with the adjusting part that is used for adjusting basic damping force, electromagnetic rod magnetic induction line collides with solenoid magnetic induction line and produces damping force, the cutting piece produces the rotation damping force to solenoid's magnetic induction line cutting simultaneously.
Preferably, the diameter of the end of the electromagnetic coil close to the electromagnetic rod is gradually reduced to the diameter of the end of the electromagnetic coil far away from the electromagnetic rod.
Preferably, a first return spring is fixedly connected between the shell and the sliding sleeve, and the first return spring is used for counteracting the vibration force.
Preferably, the area of the cut pieces near the electromagnetic coil is smaller than the area of the cut pieces far from the electromagnetic coil.
Preferably, the device further comprises symmetrically distributed extrusion assemblies, wherein the extrusion assemblies are arranged on the outer shell and comprise extrusion shells fixedly connected to the outer shell, the sliding shells are slidably connected with circumferentially distributed sliding blocks, and second reset springs are fixedly connected between the circumferentially distributed sliding blocks and the sliding shells and are in sliding fit with the extrusion shells.
Preferably, the central axis of the squeeze shell is collinear with the central axis of the slide sleeve, and the direction of the opposing force applied by the circumferentially distributed slides and squeeze shell is located at the central axis of the slide sleeve.
Preferably, the radius of the inner wall of the end of the squeeze shell near the outer shell is not smaller than the radius of the outer wall of the bottom end of the slide sleeve, for increasing the sliding distance of the slide sleeve along the inner shell.
Preferably, the heat dissipation assembly comprises symmetrically distributed air inlet fans which are fixedly connected to the outer shell, the outer shell is provided with symmetrically distributed exhaust fans, symmetrically distributed exhaust pipelines are arranged in the outer shell, the symmetrically distributed exhaust fans are communicated with the inner barrel of the outer shell through adjacent exhaust pipelines, the inner shell is provided with circumferentially distributed first vent holes, and the circumferentially distributed first vent holes in the inner shell are communicated with the inner cavity of the inner shell through uniformly distributed second vent holes.
Preferably, the second ventilation holes which are uniformly distributed in the axial direction deflect towards the adjacent electromagnetic rod, so as to prolong the heat exchange time between the gas and the electromagnetic coil.
Preferably, the adjusting component comprises a fixing frame, wherein the fixing frame is provided with blind holes which are uniformly distributed, the fixing frame is rotationally connected with a sliding block which is rotationally connected with an electromagnetic rod, the sliding block is in threaded connection with bolts which are symmetrically distributed, and the fixing frame limits the sliding block through the threaded fit of the blind holes and the bolts which are symmetrically distributed.
The invention has the beneficial effects that: 1. the magnetic induction wire of the electromagnetic rod is matched with the magnetic induction wire of the cutting piece to collide and cut the magnetic induction wire of the electromagnetic coil to generate damping force, so that extrusion kinetic energy between the electromagnetic coil and the ground when the aircraft falls is ensured to be absorbed, the landing gear of the aircraft is protected, and the service life of the landing gear is prolonged.
2. Through the special shape of electromagnetic coil, be close to the one end diameter of electromagnetic rod to its one end diameter that keeps away from electromagnetic rod reduces gradually, therefore electromagnetic coil is close to the one end that electromagnetic rod produced the relatively one end that keeps away from of magnetic induction line comparatively sparse, further strengthens this device and to the absorption of extrusion kinetic energy when the aircraft descends.
3. The sliding blocks distributed in the circumferential direction are matched with the extrusion shell to apply reverse acting force to the sliding sleeve, extrusion force when the aircraft lands is further counteracted, and meanwhile, the second reset springs distributed in the circumferential direction absorb shaking force when the aircraft lands through compression, so that stability when the aircraft lands is guaranteed.
4. The exhaust fan and the air inlet fan are matched to drive air to circulate, so that the electromagnetic coil absorbs heat generated by kinetic energy when the aircraft descends and discharges the heat, and the service life of the electromagnetic coil is prolonged.
5. The first ventilation holes and the second ventilation holes are matched to change the gas flow state, so that the heat exchange time of the gas to the electromagnetic coil is prolonged, and the heat dissipation efficiency of the electromagnetic coil is further improved.
6. The distance between the electromagnetic rod and the electromagnetic coil is adjusted through the cooperation of the fixing frame and the sliding block, so that the initial electromagnetic damping force generated by the electromagnetic coil on the electromagnetic rod is increased, and the stability of the aircraft during landing is ensured.
Drawings
Fig. 1 is a schematic perspective view of the present invention.
Fig. 2 is a schematic cross-sectional perspective view of the present invention.
Fig. 3 is a schematic perspective view showing a sectional view of the sliding sleeve and the pressing shell of the present invention and internal parts thereof.
Fig. 4 is a schematic perspective view of an electromagnetic rod and a cutting blade according to the present invention.
Fig. 5 is a schematic perspective view of the sectional view of the housing of the present invention and its internal components.
Fig. 6 is a schematic cross-sectional view of the inner shell of the present invention and a schematic perspective view of the first vent and the second vent inside the inner shell.
Fig. 7 is a schematic perspective view of an adjusting assembly according to the present invention.
Reference numerals illustrate: 101-outer shell, 102-inner shell, 103-sliding sleeve, 104-electromagnetic rod, 105-thread groove, 106-cutting piece, 107-bump, 108-electromagnetic coil, 109-first reset spring, 2-extrusion component, 201-extrusion shell, 202-slider, 203-second reset spring, 3-heat dissipation component, 301-air inlet fan, 302-air outlet fan, 303-air outlet pipe, 304-first vent, 305-second vent, 4-adjustment component, 401-fixing frame, 402-sliding block, 403-bolt.
Detailed Description
The invention is further described below with reference to the drawings and the detailed description.
Example 1: an electromagnetic damper for an airplane, as shown in fig. 1-4, comprises an outer shell 101, wherein the outer shell 101 is fixedly connected with two inner shells 102 which are symmetrically distributed, the two inner shells 102 which are symmetrically distributed are both in sliding connection with a sliding sleeve shell 103, the sliding sleeve shell 103 is a cylindrical shell, an electromagnetic rod 104 is arranged in the sliding sleeve shell 103, the electromagnetic rod 104 is of a cylindrical structure, a thread groove 105 is formed in the inner wall of the sliding sleeve shell 103, the lower end of the cylindrical electromagnetic rod 104 is fixedly connected with a uniformly distributed cutting sheet 106, the inner shell 102 is fixedly connected with a lug 107, the lug 107 is in sliding fit with the sliding sleeve shell 103 through the thread groove 105, an electromagnetic coil 108 is arranged in the inner shell 102, the diameter of the electromagnetic coil 108, which is close to one end of the electromagnetic rod 104, is gradually reduced to the diameter of the electromagnetic coil 108, which is close to one end of the electromagnetic rod 104, the magnetic induction line, which is far away from the electromagnetic rod 104 is sparse, therefore, the closer the electromagnetic rod 104 is to the inside of the electromagnetic coil 108, the larger the damping force of the electromagnetic coil 108 is borne by the electromagnetic rod 104, meanwhile, the larger the area of the cutting piece 106 at the lower end of the electromagnetic rod 104 is, the larger the area of the cutting piece 106 is, the cutting area of the cutting piece 106 on the magnetic induction line of the electromagnetic coil 108 is increased, the damping force of the electromagnetic coil 108 on the electromagnetic rod 104 is further increased, a first return spring 109 is fixedly connected between the shell 101 and the sliding sleeve shell 103, the shell 101 is provided with a heat dissipation component 3 for dissipating heat of gas in the inner shell 102 and the electromagnetic coil 108, the two symmetrically distributed sliding sleeve shells 103 are both provided with an adjusting component 4 for adjusting the basic damping force, the magnetic induction line of the electromagnetic rod 104 collides with the magnetic induction line of the electromagnetic coil 108 to generate the sliding damping force, meanwhile, the cutting piece 106 cuts the magnetic induction line of the electromagnetic coil 108 to generate the rotating damping force, and severe vibration during aircraft landing is avoided, the complete absorption and cancellation are difficult, so that the aircraft landing gear still has intense shaking and vibration, and the service life of the aircraft landing gear is reduced.
As shown in fig. 3, the device further comprises symmetrically distributed extrusion assemblies 2, the extrusion assemblies 2 are arranged on the upper side and the lower side of the casing 101, the extrusion assemblies 2 comprise extrusion shells 201, the extrusion shells 201 are provided with round table-shaped hollow structures, the extrusion shells 201 are fixedly connected with the casing 101, the sliding casings 103 are slidingly connected with three sliding blocks 202 which are circumferentially distributed, the sliding blocks 202 are provided with inclined planes matched with the inner wall of the extrusion shells 201, second return springs 203 are fixedly connected between the three sliding blocks 202 which are circumferentially distributed and the sliding casings 103, the three sliding blocks 202 which are circumferentially distributed are in extrusion fit with the extrusion shells 201 through the inclined planes, the three sliding blocks 202 which are circumferentially distributed are matched with the extrusion shells 201 apply reverse acting force to the sliding casings 103, meanwhile, three second return springs 203 distributed in the circumferential direction compress and absorb shaking force, shaking and vibration during landing of an airplane are further absorbed, the service life of an undercarriage of the airplane is prolonged, the central axis of the extrusion shell 201 and the central axis of the sliding shell 103 are collinear, the direction of the reverse force applied by extrusion of the sliding blocks 202 distributed in the circumferential direction and the extrusion shell 201 is located on the central axis of the sliding shell 103, the inclination of the reverse force applied by extrusion of the sliding blocks 202 distributed in the circumferential direction and the extrusion shell 201 is avoided, the abrasion degree of the sliding shell 103 is increased, the service life is prolonged, the radius of the inner wall of the lower end of the extrusion shell 201 is identical to the radius of the outer wall of the bottom end of the sliding shell 103, and the sliding distance of the sliding shell 103 along the inner shell 102 is increased.
During the landing period of the aircraft, the tires are in contact with the ground, at the moment, the weight of the aircraft and the extrusion force of the kinetic energy of the aircraft and the ground are received, so that the two symmetrically distributed sliding sleeves 103 slide along the adjacent inner shells 102, at the moment, the sliding sleeves 103 drive the sliding sleeves 103 to move through the upper thread grooves 105 and the protruding blocks 107 of the sliding sleeves 103 to slide along the protruding blocks 107 on the inner shells 102, meanwhile, the sliding sleeves 103 drive the electromagnetic rods 104 to synchronously move, meanwhile, the first reset spring 109 compresses and absorbs part of extrusion force, the movement of the electromagnetic rods 104 gradually approaches to the electromagnetic coils 108, at the moment, the magnetic induction wires of the electromagnetic coils 108 and the magnetic induction wires of the electromagnetic rods 104 are in contact to generate repulsive force, the kinetic energy of the extrusion force is absorbed through the repulsive force of the magnetic induction wires during landing, the impact on the ground is prevented from being too large, and the aircraft is caused to shake violently and landing is difficult to be completed.
Meanwhile, the electromagnetic rod 104 rotates to drive the cutting blade 106 on the electromagnetic rod 104 to synchronously rotate, the cutting blade 106 rotates to cut the magnetic induction wire of the electromagnetic coil 108, the cutting blade 106 and the magnetic induction wire of the electromagnetic coil 108 are cut to generate rotation repulsive force, and as the cutting blade 106 at the lower end of the electromagnetic rod 104 is far away from the electromagnetic coil 108, the area of the cutting blade is larger, along with the approach of the electromagnetic rod 104 to the electromagnetic coil 108, the cutting area of the cutting blade 106 on the electromagnetic rod 104 to the magnetic induction wire of the electromagnetic coil 108 is larger, at the moment, the rotation repulsive force of the magnetic induction wire of the electromagnetic coil 108 is larger, the cutting blade 106 is subjected to rotation repulsive force, and then the electromagnetic rod 104 is blocked from approaching the electromagnetic coil 108, further the extrusion force with the ground is counteracted by magnetic field force when the aircraft drops, the impact between the electromagnetic rod 104 and the ground is avoided, the damping force generated by the electromagnetic rod 108 cannot completely absorb the kinetic energy generated by the impact, and the aircraft shakes violently when the aircraft drops, so that the landing gear of the aircraft is damaged.
Because the electromagnetic coil 108 is in an hourglass shape, that is, the diameters of the two ends of the electromagnetic coil 108 are larger than the inner diameter of the electromagnetic coil, magnetic induction lines generated by the two ends of the electromagnetic coil 108 are relatively sparse, so that damping force of the two ends of the electromagnetic coil 108 to the electromagnetic rod 104 is relatively small compared with the inner part of the electromagnetic coil, when the distance between the electromagnetic rod 104 and the electromagnetic coil 108 is gradually reduced, the damping force of the electromagnetic coil 108 to the electromagnetic rod 104 is gradually increased, kinetic energy absorption during aircraft landing is further enhanced, and shaking generated by the aircraft landing gear on the ground during aircraft landing are avoided to be too severe, so that the aircraft landing gear is damaged.
When the aircraft lands, when two sliding sleeves 103 which are symmetrically distributed slide along the adjacent inner shells 102, at the moment, the sliding sleeves 103 drive three sliding blocks 202 which are circumferentially distributed on the sliding sleeves to synchronously slide, the three sliding blocks 202 which are circumferentially distributed move and squeeze the squeezing shell 201, reverse acting force is applied to the sliding sleeves 103 by the three sliding blocks 202 which are circumferentially distributed through squeezing the squeezing shell 201, extrusion force during landing of the aircraft is further counteracted, meanwhile, three second return springs 203 which are circumferentially distributed are synchronously compressed, and shaking force during landing of the aircraft is absorbed through flexible change by the compression of the three second return springs 203 which are circumferentially distributed, so that shaking force is severe during landing of the aircraft is avoided, and landing gear of the aircraft is damaged.
Example 2: on the basis of embodiment 1, as shown in fig. 5 and 6, the heat dissipating component 3 comprises two air inlet fans 301 which are symmetrically distributed, the two air inlet fans 301 which are symmetrically distributed are fixedly connected to the housing 101, the housing 101 is provided with two air outlet fans 302 which are symmetrically distributed, the two air inlet fans 301 which are symmetrically distributed and the two air outlet fans 302 which are symmetrically distributed are alternately distributed, the two air outlet fans 302 which are symmetrically distributed and the two air inlet fans 301 which are symmetrically distributed cooperate to drive air to circulate, heat generated when an airplane descends is discharged, the service life of the electromagnetic coil 108 is prolonged, two air outlet pipelines 303 which are symmetrically distributed are arranged in the housing 101, the two air outlet fans 302 which are symmetrically distributed are communicated with the inner cylinder of the housing 101 through adjacent air outlet pipelines 303, the two inner shells 102 which are vertically and symmetrically distributed are respectively provided with a first vent hole 304 which is circumferentially distributed, the two inner shells 102 which are vertically and symmetrically distributed are respectively provided with a second vent hole 305 which is axially and uniformly distributed, the second vent holes 305 which are axially and uniformly distributed deflect towards the adjacent electromagnetic rod 104 for increasing the heat exchange duration of gas and the electromagnetic coil 108, the inner part of the inner shell 102 is communicated with the inner cavity of the outer shell 101 through the second vent holes 305 which are uniformly distributed and the first vent holes 304 which are circumferentially distributed, the gas flow state is changed through the cooperation of the first vent holes 304 and the second vent holes 305, the gas circulation speed is delayed, the heat exchange duration of gas and the electromagnetic coil 108 is increased, and the heat dissipation efficiency of the electromagnetic coil is improved.
Simultaneously, when the aircraft descends, two air inlet fans 301 and two air outlet fans 302 which are symmetrically distributed are started, at this time, the two air inlet fans 301 which are symmetrically distributed rotate to extract external air, the two air inlet fans 301 which are symmetrically distributed rotate to be extracted into a cavity in the air shell 101, then the air in the cavity in the shell 101 enters into the two inner shells 102 which are vertically symmetrical along a first vent hole 304 which is circumferentially distributed, the air in the first vent hole 304 which is circumferentially distributed enters into the inner shells 102 through a second vent hole 305 which is uniformly distributed, the air passing through the second vent hole 305 is collected into the inner shells 102 and is mutually opposite to each other, the air is further diffused and is heat-exchanged with the electromagnetic coil 108, the movement state of the air is changed, the circulation speed of the air is delayed, the heat exchange time between the air and the electromagnetic coil 108 is prolonged, the heat exchange time of the electromagnetic coil 108 is further improved, at this time, the electromagnetic coil 108 is converted into internal energy through magnetic field force, the temperature of the electromagnetic coil 108 is rapidly increased, and simultaneously, the air in the directions of the adjacent electromagnetic rods 104 are deflected towards each other, the second vent hole 305, the air and the air is discharged from the two air outlet pipes which are symmetrically distributed through the two air outlet fans 108, the heat exchange time is prolonged, and the heat of the heat is exhausted from the two air channels which is reciprocally distributed through the electromagnetic coil 108, the two air channels 108 is exhausted, the heat is avoided, and the heat is recovered, and the heat is exhausted from the air heat of the air is exhausted by the electromagnetic coil 108, and the air is greatly when the heat is greatly when the temperature is greatly when the air is temperature is in and is in.
Example 3: on the basis of embodiment 2, as shown in fig. 7, the adjusting component 4 comprises a fixing frame 401, the fixing frame 401 is composed of a butt joint disc and two symmetrically distributed fixing shafts, the fixing frame 401 is rotationally connected with a sliding sleeve shell 103, the fixing frame 401 is slidingly connected with a sliding block 402, the sliding block 402 is rotationally connected with an electromagnetic rod 104, the sliding block 402 is in threaded connection with two symmetrically distributed bolts 403, the fixing frame 401 is in limit fit with the sliding block 402 through the two symmetrically distributed bolts 403, the fixing frame 401 and the sliding block 402 adjust the distance between the electromagnetic rod 104 and the electromagnetic coil 108, the initial electromagnetic damping force generated by the electromagnetic coil 108 on the electromagnetic rod 104 is increased, and the stability of the aircraft during landing is ensured.
When the device is initially installed, a worker adjusts the distance between the electromagnetic rod 104 and the electromagnetic coil 108 according to the model and the carrying capacity of the airplane, at this time, the worker rotates two symmetrically distributed bolts 403, the two symmetrically distributed bolts 403 slide along the sliding block 402, after the limit of the fixing frame 401 and the sliding block 402 is released by the two symmetrically distributed bolts 403, the worker drives the sliding block 402 to slide along the fixing frame 401, the sliding block 402 slides to a required position along the fixing frame 401, then the two symmetrically distributed bolts 403 reversely rotate, after the fixing frame 401 and the sliding block 402 are limited again by the two symmetrically distributed bolts 403, the two symmetrically distributed bolts 403 stop rotating, at this time, the adjustment is completed, the airplane is prevented from being supported by the initial electromagnetic damping force generated by the electromagnetic coil 108 and the electromagnetic rod 104, and the airplane cannot be supported, and severe shaking occurs during the landing of the airplane.
The foregoing description is only illustrative of the present invention and is not intended to limit the scope of the invention, and all equivalent structures or equivalent processes or direct or indirect application in other related arts are included in the scope of the present invention.
Claims (7)
1. The electromagnetic damper for the aircraft is characterized by comprising an outer shell (101), wherein the outer shell (101) is fixedly connected with an inner shell (102) which is symmetrically distributed, the inner shells (102) which are symmetrically distributed are all connected with a sliding sleeve (103) in a sliding manner, electromagnetic rods (104) are arranged in the sliding sleeve (103), the sliding sleeve (103) is provided with thread grooves (105), the electromagnetic rods (104) are provided with evenly distributed cutting blades (106), the inner shell (102) is fixedly connected with a lug (107), the lug (107) is in sliding fit with the sliding sleeve (103) through the thread grooves (105), an electromagnetic coil (108) is arranged in the inner shell (102), the outer shell (101) is provided with a heat dissipation assembly (3) which is used for dissipating heat of gas in the inner shell (102) and the electromagnetic coil (108), the sliding sleeve (103) which is symmetrically distributed is provided with an adjusting assembly (4) which is used for adjusting basic damping force, and the magnetic induction lines of the electromagnetic rods (104) collide with the electromagnetic coil (108) to generate damping force, and simultaneously the magnetic induction lines of the cutting blades (106) generate damping force to the magnetic induction lines of the electromagnetic coil (108);
the novel anti-theft device is characterized by further comprising symmetrically distributed extrusion assemblies (2), wherein the extrusion assemblies (2) are arranged on the outer shell (101), the extrusion assemblies (2) comprise extrusion shells (201), the extrusion shells (201) are fixedly connected to the outer shell (101), the sliding shells (103) are slidably connected with circumferentially distributed sliding blocks (202), second reset springs (203) are fixedly connected between the circumferentially distributed sliding blocks (202) and the sliding shells (103), and the circumferentially distributed sliding blocks (202) are in sliding fit with the extrusion shells (201);
the central axis of the extrusion shell (201) is collinear with the central axis of the sliding sleeve (103), and the direction of the opposite force applied by the extrusion of the sliding blocks (202) and the extrusion shell (201) which are distributed in the circumferential direction is positioned at the central axis of the sliding sleeve (103);
the radius of the inner wall of the end of the extrusion shell (201) close to the outer shell (101) is not smaller than the radius of the outer wall of the bottom end of the sliding shell (103), so that the sliding distance of the sliding shell (103) along the inner shell (102) is increased.
2. An electromagnetic damper for an aircraft according to claim 1, wherein the diameter of the end of the electromagnetic coil (108) near the electromagnetic rod (104) is gradually reduced to the diameter of the end thereof far from the electromagnetic rod (104).
3. An electromagnetic damper for an aircraft according to claim 1, characterized in that a first return spring (109) is fixedly connected between the housing (101) and the sliding sleeve (103), the first return spring (109) being arranged to counteract the vibratory force.
4. An electromagnetic damper for an aircraft according to claim 1, wherein the area of the cutting blade (106) proximate the electromagnetic coil (108) is smaller than the area of the cutting blade (106) distal from the electromagnetic coil (108).
5. The electromagnetic damper for the aircraft according to claim 1, wherein the heat dissipation assembly (3) comprises symmetrically distributed air inlet fans (301), the symmetrically distributed air inlet fans (301) are fixedly connected to the outer shell (101), the outer shell (101) is provided with symmetrically distributed air outlet fans (302), symmetrically distributed air outlet pipelines (303) are arranged in the outer shell (101), the symmetrically distributed air outlet fans (302) are communicated with the inner barrel of the outer shell (101) through adjacent air outlet pipelines (303), the inner shell (102) is provided with circumferentially distributed first vent holes (304), and the circumferentially distributed first vent holes (304) in the inner shell (102) are communicated with the inner cavity of the inner shell (102) through uniformly distributed second vent holes (305).
6. An electromagnetic damper for aircraft according to claim 5, characterized in that the axially uniformly distributed second ventilation holes (305) are each deflected towards an adjacent electromagnetic rod (104) for increasing the length of the heat exchange between the gas and the electromagnetic coil (108).
7. An electromagnetic damper for an aircraft according to claim 1, characterized in that the adjusting assembly (4) comprises a fixing frame (401), the fixing frame (401) is provided with blind holes which are uniformly distributed, the fixing frame (401) is rotatably connected with the sliding sleeve (103), the fixing frame (401) is slidably connected with a sliding block (402), the sliding block (402) is rotatably connected with the electromagnetic rod (104), the sliding block (402) is in threaded connection with bolts (403) which are symmetrically distributed, and the fixing frame (401) limits the sliding block (402) through threaded matching of the blind holes and the bolts (403) which are symmetrically distributed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310612451.XA CN116498680B (en) | 2023-05-29 | 2023-05-29 | Electromagnetic damper for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310612451.XA CN116498680B (en) | 2023-05-29 | 2023-05-29 | Electromagnetic damper for aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN116498680A CN116498680A (en) | 2023-07-28 |
| CN116498680B true CN116498680B (en) | 2024-01-26 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310612451.XA Active CN116498680B (en) | 2023-05-29 | 2023-05-29 | Electromagnetic damper for aircraft |
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| CN (1) | CN116498680B (en) |
Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
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