CN115261794B - Bearing applied to air rudder of ultra-high sound velocity aircraft and preparation method thereof - Google Patents

Bearing applied to air rudder of ultra-high sound velocity aircraft and preparation method thereof Download PDF

Info

Publication number
CN115261794B
CN115261794B CN202210909075.6A CN202210909075A CN115261794B CN 115261794 B CN115261794 B CN 115261794B CN 202210909075 A CN202210909075 A CN 202210909075A CN 115261794 B CN115261794 B CN 115261794B
Authority
CN
China
Prior art keywords
bearing
ring
layer
metal rubber
lubricating
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
Application number
CN202210909075.6A
Other languages
Chinese (zh)
Other versions
CN115261794A (en
Inventor
朱丽娜
康嘉杰
岳�文
杨瑞凯
田斌
王浩东
付志强
佘丁顺
孟德忠
梁健
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Zhengzhou Research Institute China University Of Geosciences Beijing
China University of Geosciences Beijing
Institute of Flexible Electronics Technology of THU Zhejiang
Original Assignee
Zhengzhou Research Institute China University Of Geosciences Beijing
China University of Geosciences Beijing
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Zhengzhou Research Institute China University Of Geosciences Beijing, China University of Geosciences Beijing filed Critical Zhengzhou Research Institute China University Of Geosciences Beijing
Priority to CN202210909075.6A priority Critical patent/CN115261794B/en
Publication of CN115261794A publication Critical patent/CN115261794A/en
Application granted granted Critical
Publication of CN115261794B publication Critical patent/CN115261794B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/06—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
    • C23C14/14—Metallic material, boron or silicon
    • C23C14/16—Metallic material, boron or silicon on metallic substrates or on substrates of boron or silicon
    • C23C14/165—Metallic material, boron or silicon on metallic substrates or on substrates of boron or silicon by cathodic sputtering
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
    • B05D—PROCESSES FOR APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
    • B05D7/00—Processes, other than flocking, specially adapted for applying liquids or other fluent materials to particular surfaces or for applying particular liquids or other fluent materials
    • B05D7/22—Processes, other than flocking, specially adapted for applying liquids or other fluent materials to particular surfaces or for applying particular liquids or other fluent materials to internal surfaces, e.g. of tubes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
    • B05D—PROCESSES FOR APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
    • B05D7/00—Processes, other than flocking, specially adapted for applying liquids or other fluent materials to particular surfaces or for applying particular liquids or other fluent materials
    • B05D7/24—Processes, other than flocking, specially adapted for applying liquids or other fluent materials to particular surfaces or for applying particular liquids or other fluent materials for applying particular liquids or other fluent materials
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/02—Pretreatment of the material to be coated
    • C23C14/021—Cleaning or etching treatments
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/02—Pretreatment of the material to be coated
    • C23C14/021—Cleaning or etching treatments
    • C23C14/022—Cleaning or etching treatments by means of bombardment with energetic particles or radiation
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/02—Pretreatment of the material to be coated
    • C23C14/028—Physical treatment to alter the texture of the substrate surface, e.g. grinding, polishing
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/06—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
    • C23C14/0623—Sulfides, selenides or tellurides
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/22—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the process of coating
    • C23C14/34—Sputtering
    • C23C14/35—Sputtering by application of a magnetic field, e.g. magnetron sputtering
    • C23C14/352—Sputtering by application of a magnetic field, e.g. magnetron sputtering using more than one target
    • 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
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
    • F16C33/30—Parts of ball or roller bearings
    • F16C33/66—Special parts or details in view of lubrication
    • F16C33/6696—Special parts or details in view of lubrication with solids as lubricant, e.g. dry coatings, powder
    • 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

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Wood Science & Technology (AREA)
  • General Engineering & Computer Science (AREA)
  • Physical Vapour Deposition (AREA)

Abstract

The invention provides a bearing applied to an air rudder of an ultra-high sound velocity aircraft and a preparation method thereof, and relates to the technical field of material surface engineering. The bearing comprises a bearing outer ring, a bearing inner ring, balls and a metal rubber lubrication ring; annular grooves are formed in the ball contact surfaces corresponding to the outer ring and the inner ring of the bearing along the circumferential direction; the surfaces of the ball contact surfaces with the annular grooves and the metal rubber lubrication rings are respectively and completely covered with the self-lubricating composite coating; the metal rubber lubrication ring is arranged in the annular groove. A plurality of lubricating medium filling grooves are arranged on the surface of the metal rubber lubricating ring facing the balls. The filling groove is in a trapezoid structure. According to the invention, through the optimized design of the structure of the bearing ring of the air rudder, the metal rubber lubrication ring with better stability is added, so that the bearing ring is better adapted to complex and changeable service environments; through design self-lubricating coating and have the indent of lubricating medium, effectively promote the sliding behavior of ball in the bearing ring, improve steering wheel's running accuracy and stability.

Description

Bearing applied to air rudder of ultra-high sound velocity aircraft and preparation method thereof
Technical Field
The invention belongs to the technical field of material surface engineering, and particularly relates to a bearing applied to an air rudder of an ultra-high sound velocity aircraft and a preparation method thereof.
Background
With the continuous enhancement of military forces of various countries, the aerospace technology is driven to rapidly and vigorously develop, and various ultra-high sound velocity aircrafts become a very important part of national defense forces. However, due to the complex and changeable service environment, the ultra-high sound speed aircraft is often faced with multiple tests, and not only needs to have lasting and stable working capacity, but also has higher requirements on the service life of materials. In order to avoid the overall replacement of machine components due to wear damage of aircraft parts, cost reduction, and lubrication between kinematic pairs is particularly important. The flight Mach number of the ultra-high sound velocity aircraft is larger than 5, the operation speed is very high, the local temperature can be rapidly increased to a very high value from normal temperature, and the traditional grease lubrication obviously cannot meet the lubrication requirement.
The air rudder is an operation system of the hypersonic aircraft, and generates required control force or control moment through the interaction of air and a control surface, so that the purpose of controlling the flight direction and the attitude of the aircraft is achieved. As aircraft flight speeds and times increase, aerodynamic heat becomes more and more severe, which can cause the rudder to increase in temperature and decrease in structural strength and rigidity. Meanwhile, the air rudder bearing for bearing the steering engine rotation can also cause oil way blockage, friction aggravation and insufficient lubrication due to local temperature rise and the like, and can cause the bearing to be blocked when serious, thereby affecting the safe operation of the aircraft.
Therefore, designing a self-lubricating bearing structure suitable for high-temperature working conditions to replace the traditional grease lubricated bearing is a technical problem to be solved by the person skilled in the art.
Disclosure of Invention
The invention aims to provide a bearing applied to an air rudder of an ultra-high sound velocity aircraft, and by optimally designing the structure of a bearing ring of the air rudder, a metal rubber lubrication ring with better stability is added, so that the bearing ring can effectively absorb shock and resist high temperature while lubricating, and is better adapted to complex and changeable service environments; the composite self-lubricating coating is deposited on the surfaces of the bearing ring wall and the groove by utilizing an unbalanced magnetron sputtering method, so that the sliding performance of the ball in the bearing ring is effectively improved; the small groove with the lubricating medium is arranged on the metal rubber lubricating ring, so that abrasion between the bearing ring and the balls is further reduced, and the lubricating medium can be continuously and effectively supplemented while the friction coefficient is reduced. When the steering engine is in extreme working conditions of oil way blockage, friction aggravation and insufficient lubrication, the metal rubber lubrication ring can replace a bearing ring to participate in lubrication and rotation, and the operation precision and stability of the steering engine are improved.
The high-temperature-resistant self-lubricating bearing structure provided by the invention overcomes the problem that the traditional aircraft air rudder has poor grease lubrication effect, realizes low damping between the aircraft air rudder rotating shaft and the structural main body, reliably rotates and connects in long voyage, still keeps good self-lubricating performance in high-temperature conditions, supports the high-temperature-resistant self-lubricating bearing structure, realizes severe long voyage and high maneuvering flight indexes, and has important significance for the operation of the whole ultra-high sound velocity aircraft.
In order to achieve the above purpose, the invention provides a bearing applied to an air rudder of an ultra-high sound velocity aircraft, which comprises a bearing outer ring, a bearing inner ring, balls and a metal rubber lubrication ring;
annular grooves are formed in the ball contact surfaces corresponding to the outer ring and the inner ring of the bearing along the circumferential direction;
the surfaces of the ball contact surfaces with the annular grooves and the metal rubber lubrication rings are respectively and completely covered with the self-lubricating composite coating;
the metal rubber lubrication ring is arranged in the annular groove.
In a preferred embodiment, the annular grooves are formed in two on the same bearing ring surface and are symmetrically distributed on two sides of the annular wall, and four grooves are formed in total on one bearing.
In a preferred embodiment, a plurality of medium filling grooves are formed in the surface of the metal rubber lubrication ring facing the balls, and the inside is filled with a lubricating medium, preferably graphene powder, more preferably, 6 medium filling grooves are formed in the surface of each metal rubber lubrication ring.
The purpose of the small grooves designed on the contact surface with the balls is to allow the lubrication medium in the grooves to participate in the ball lubrication. The graphene powder has a good lubricating effect, and can supplement the graphene layer material on the surface of the self-lubricating composite coating, so that the preferable lubricating medium is the graphene powder. The medium filling groove at the position 6 is designed to enable the lubricating medium to surround the whole bearing ring, so that the effect and range of the supplementary lubrication are improved, but the stability of the metal rubber lubricating ring is reduced due to the excessive number of filling grooves, so that the position 6 is designed.
In a preferred embodiment, the medium-filled trench has a trapezoid structure with a small surface opening and a large internal opening. According to the structural design, when the lubricating effect is good, only a small amount of medium participates in lubrication, the metal rubber lubricating ring is gradually worn along with the reduction of the lubricating effect, the opening of the filling groove is enlarged, and more medium stored in the filling groove can effectively participate in a lubricating system to supplement lubricating substances.
In a preferred embodiment, the self-lubricating composite coating has a three-layer structure, and a Ti layer and a MoS layer are sequentially arranged from the surface of the substrate to the outside 2 -a Ni layer and a graphene layer. The Ti layer is a transition layer and can have better combination capability with the matrix; moS (MoS) 2 The Ni layer is a main lubrication layer, and the graphene layer is a secondary lubrication layer, which cooperate to provide a lubrication effect. At the MoS 2 In the Ni layer, each element atomThe percentages are as follows: mo 35-40at%, S25-30 at%, ti 1-5at%, ni 25-35at%, and at% represents atomic percentage. Preferably, the atomic percentages of the elements are: 36-38at% of Mo, 28-30at% of S, 1-3at% of Ti and 27-30at% of Ni, and more preferably, the atomic percentages of the elements are as follows: 36.7at% of Mo, 28.4at% of S, 2.1at% of Ti and 27.5at% of Ni.
In a preferred embodiment, the self-lubricating composite coating has a thickness of 2.7-2.8 μm, overall hardness of 10Gpa or more, elastic modulus of 107Gpa or more, and plastic deformation resistance H 3 /E 2 The surface roughness of the surface graphene layer is 4-5nm, and the friction coefficient is 0.03-0.06 within the temperature range of 100-300 ℃.
The self-lubricating composite coating prepared by the invention has small overall fluctuation, stable tribological performance at high temperature, and the coating after composite deposition combines MoS 2 And the physical and chemical properties of Ni and the oxidation resistance, corrosion resistance and wear resistance are improved. Plastic deformation resistance H 3 /E 2 0.09, where H represents hardness and E represents elastic modulus, indicating that the doping of Ni effectively improves the coating's resistance to plastic deformation.
Another object of the present invention is to provide a method for preparing a bearing applied to an air rudder of an ultra-high sound velocity aircraft, in which a Ti layer and a MoS are prepared by magnetron sputtering deposition 2 The Ni layer is used for preparing a graphene layer by a carbon dropping method, so that the self-lubricating composite coating with both hardness and low friction coefficient can be obtained; the preparation of the groove on the surface of the bearing ring and the preparation of the lubrication medium filling groove on the surface of the metal rubber lubrication ring are all carried out by the conventional method in the field. The preparation method is simple and efficient, not only can the bearing ring be newly prepared, but also the existing air rudder bearing can be simply modified, so that the wear resistance and stability of the bearing ring can be greatly improved, and the resource utilization effect is improved.
In order to achieve the above purpose, the invention provides a preparation method of a bearing applied to an air rudder of an ultra-high sound velocity aircraft, which specifically comprises the following steps:
machining grooves: annular grooves are formed in the ball contact surfaces corresponding to the inner surface of the outer ring of the bearing and the outer surface of the inner ring of the bearing along the circumferential direction;
and (3) equipment installation: an arc-shaped target, an arc-shaped cathode seat, permanent magnet steel and an air rudder bearing clamp are arranged on magnetron sputtering coating equipment;
preparing a self-lubricating composite coating: preparing composite coatings on the inner surface of the outer ring of the bearing, the outer surface of the inner ring of the bearing, the surface of the groove and the surface of the metal rubber lubrication ring respectively;
processing a metal rubber lubrication ring: a plurality of medium filling grooves are formed in the surface of the metal rubber lubrication ring facing the ball, and the interior of the metal rubber lubrication ring is filled with lubrication medium;
and (3) assembling: and embedding the metal rubber ring into the groove covered with the self-lubricating composite coating, and keeping the opening of the trapezoid medium filling groove towards the ball.
In a preferred embodiment, the groove forming manner may be any manner known to those skilled in the art, and preferably, the groove forming manner is milling by using a numerical control machine, and rough milling is performed before finish milling, so as to obtain the annular groove. More preferably, after the annular groove is obtained, the inner wall of the bearing ring can be polished by a polishing machine so as to facilitate subsequent processing.
In a preferred embodiment, in the apparatus mounting step, air is pumped into the apparatus using a high vacuum diffusion pump, maintaining a suitable vacuum in the chamber at 10 degrees f -3 Pa or more.
In a preferred embodiment, the preparation of the self-lubricating composite coating specifically comprises the following steps:
s1, preparing a Ti layer: after polishing the surface of the material, cleaning the surface with acetone and absolute ethyl alcohol in sequence; carrying out bombardment etching pretreatment; finally, sputtering and depositing to obtain a Ti layer;
s2 preparation of MoS 2 -Ni layer: on the Ti layer obtained, pure metal Ni target and MoS were used 2 Target double-target co-sputtering deposition to obtain MoS 2 -a Ni layer;
s3, preparing a graphene layer: mixing multilayer graphene powder with ethanol, performing ultrasound to obtain graphene ethanol suspension, and uniformly spreading the graphene ethanol suspension on the obtained MoS 2 The surface of the Ni layer is kept stand and the graphene is obtained after the ethanol volatilizesA layer.
Further preferably, in the step S1, the etching pretreatment conditions are as follows: setting bias voltage of an unbalanced magnetron sputtering deposition coating system to 450-500V, introducing high-purity argon gas to 15-20sccm, and carrying out corrosion pretreatment for 15-20min, wherein the Ti target current is 0.1-0.3A; the rotating speed of the clamp is 30-60r/min.
The conditions for obtaining the Ti layer by sputtering deposition are as follows: the bias voltage of a deposition coating system is 90-100V, high-purity argon is introduced for 15-20sccm, ti target current is 1-3A, and sputtering deposition time is 10-15min;
in the step S2, moS is obtained by sputter deposition 2 The Ni layer conditions were: the bias voltage of the deposition coating system is 40-60V, high-purity argon is introduced to 10-15sccm, moS 2 Target current is 0.7-1A, ni target current is 0.1-0.3A, and sputtering deposition time is 120-130min;
in the step S3, the purity of the multilayer graphene powder is more than 90wt%, the concentration of ethanol is 97wt%, the concentration of graphene ethanol suspension is 20mg/L, and the ultrasonic time is 10-15min.
In a preferred embodiment, the prepared graphene layer is formed by stacking 4-6 layers of graphene particles, the thickness of the graphene layer is 5-8nm, the carbon content is more than or equal to 98%, and the specific surface area is 50-150m 2 /g。
In a preferred embodiment, after the self-lubricating composite coating is prepared on the surface of the metal rubber lubricating ring, the protective coating is firstly coated on the contact surface of the self-lubricating composite coating and the ball, so that the protective coating is prevented from being damaged in the subsequent medium filling groove processing, and the protective adhesive tape is removed after the filling groove is prepared.
In a preferred embodiment, the metal rubber lubrication ring processing method can be any mode known by a person skilled in the art, preferably, a milling and forming process of a numerical control machine tool is adopted, firstly rough milling is carried out on trapezoid filling grooves with small surface openings and large internal openings in finish milling, and 6 trapezoid grooves are processed on each rubber ring; the manner of filling the grooves with the lubricating medium may be any manner known to those skilled in the art as long as the surface of the lubricating medium is maintained in alignment with the surface of the self-lubricating composite coating.
Compared with the prior art, the technical scheme of the invention has the following advantages:
the bearing ring applied to the air rudder of the ultra-high sound velocity aircraft, disclosed by the invention, has the advantages that the wear rate between the bearing ring and the balls is reduced, the friction resistance is reduced, and the problem of locking of the steering engine caused by insufficient lubrication of the bearing can be effectively solved. Meanwhile, the steering stability and the steering precision of the air rudder of the ultra-high sound velocity aircraft are improved.
The invention combines the mode of depositing the lubricating coating and improving the bearing ring structure, and doubly improves the lubricating and stabilizing effects, in particular:
in optimizing the lubricating coating: 1. the lubricating coating comprises two lubricating materials with excellent lubricating performance: graphene and MoS 2 And a composite lubricant composed of Ni. Wherein, metal element Ni doped MoS 2 Structurally and performance better than pure MoS 2 The metal rubber lubricating ring is particularly suitable for surface lubrication of the metal rubber lubricating ring, provides low friction coefficient, simultaneously has high hardness, and improves the stability of the metal rubber lubricating ring in a complex service environment. 2. In the preparation method, the composite coating is coated on the inner wall of the bearing ring by adopting a magnetron sputtering technology, and has strong bearing capacity. 3. The preparation method of the film is simple, the cost is low, the elements of the prepared film layer are uniformly distributed, and the bonding strength of the film base is high. 4. The average thickness of the prepared lubricating film is only 2.8 mu m, the assembly problem of the bearing is not affected, the graphene coverage rate of the graphene layer is high, and the lubricating effect of the graphene can be exerted to the greatest extent. 5. The surface layer graphene layer of the prepared antifriction self-lubricating composite coating has the surface roughness of 4-5nm, the overall hardness of the coating is above 10Gpa, the elastic modulus can reach above 107Gpa, the plastic deformation resistance rate is 0.09, the minimum friction coefficient can reach 0.03 in the temperature range of 100-300 ℃, and the antifriction self-lubricating composite coating can meet the lubrication requirement of an air rudder of an ultra-high sonic aircraft at a higher service temperature.
In terms of improving the bearing ring structure: 1. four annular grooves are symmetrically machined on the surface contacted with the ball bearings and are used for embedding the metal rubber lubrication ring, and the grooves are also deposited with a composite coating, so that the sliding capacity of the metal rubber lubrication ring can be increased, and the friction resistance is reduced. 2. The metal rubber lubrication ring is inlaid in the groove and matched with the bearing ring to form a new bearing ring. 3. The surface of the metal rubber lubrication ring is provided with a plurality of trapezoid small grooves for storing lubrication media, and preferably, the filled lubrication media are graphene in a dispersed powder form for supplementary lubrication. The small groove opening part is positioned on the surface of the coating, is aligned with the coating after being filled with the lubricating medium, and forms a plane which is beneficial to the rotation of the ball.
The advantage of this structure is: firstly, the metal rubber lubrication ring has high temperature resistance and good elasticity, and can buffer and absorb shock. Secondly, the arrangement of the small groove on the lubricating ring, the small groove is trapezoid-shaped, the opening is small, the inside is large, the lubricating medium is filled, at ordinary times, the lubricating medium participates in lubrication through small opening small parts when lubrication is good, when the consumption of the lubricating coating is large or the lubricating effect is reduced and further the coating is damaged, the opening of the trapezoid-shaped groove of the metal rubber lubricating ring is also enlarged along with the enlargement, and the stored lubricating medium is added into a lubricating system more to supplement lubrication, so that the lubrication requirement of bearing work is ensured. Finally, when the bearing is insufficiently lubricated or abrasive particles enter the bearing to enable the bearing to rotate unstably or to be blocked, the lubricating ring with the surface fully covered by the self-lubricating composite coating can temporarily replace the bearing ring to contact with the balls to participate in rotation, so that the lubricating effect is further improved, and the safe operation of the aircraft is ensured.
Drawings
These and/or other aspects and advantages of the present invention will become more apparent and more readily appreciated from the following detailed description of the embodiments of the invention, taken in conjunction with the accompanying drawings, wherein:
FIG. 1 is a schematic view of a bearing and bearing ring for an ultra-high sound velocity aircraft rudder according to the present invention;
FIG. 2 is a cross-sectional view of a bearing ring and a schematic view of layers of an inner wall self-lubricating composite coating applied to an air rudder of an ultra-high sonic velocity aircraft;
FIG. 3 is a schematic diagram of a metal rubber lubrication ring applied to an air rudder of an ultra-high sound velocity aircraft;
FIG. 4 is a cross-sectional microstructure of a self-lubricating composite coating prepared in example 3 of the present invention;
FIG. 5 is a three-dimensional white light surface morphology of the self-lubricating composite coating prepared in example 3 of the present invention;
FIG. 6 is a graph showing the friction coefficient of the self-lubricating composite coating prepared in example 3 of the present invention at different temperatures.
Detailed Description
For a better understanding of the present invention, those skilled in the art will now make further details with reference to the drawings and the detailed description, but it should be understood that the scope of the invention is not limited by the detailed description.
The embodiment of the invention solves the problem of poor grease lubrication effect of the traditional bearing in the prior art by providing the bearing applied to the air rudder of the ultra-high sound velocity aircraft and the preparation method thereof.
Unless otherwise indicated, the technical means used in the present invention are conventional means well known to those skilled in the art, and various raw materials, reagents, instruments, equipment, etc. used in the present invention are commercially available or can be prepared by existing methods. The metal rubber lubrication ring used was purchased from Hebei Jiu Liu glass fiber reinforced plastic Co.
The bearing ring applied to the air rudder of the ultra-high sound velocity aircraft has a structure schematic diagram shown in figure 1, and particularly comprises an inner bearing ring and an outer bearing ring 1, a metal rubber lubrication ring 2 and a self-lubricating composite coating 4,
as can be seen from fig. 1, annular grooves are formed in the ball contact surfaces corresponding to the outer ring and the inner ring of the bearing along the circumferential direction, two annular grooves are formed in the surface of the same bearing ring, the two annular grooves are symmetrically distributed on two sides of the annular wall, and four grooves are distributed on one bearing in total. The metal rubber lubrication ring is inlaid in the groove, and total four lubrication rings are arranged. The metal rubber ring is uniformly distributed with a plurality of medium filling grooves 3, and the specific structure is shown in figure 3.
As can be seen from fig. 3, 8 is a medium-filled groove filled with a lubricating medium, which has a trapezoid structure with a small surface opening and a large internal opening. And the openings of the media filled channels are aligned with the self-lubricating composite coating 10.
FIG. 2 clearly shows the schematic structure of each layer of the self-lubricating composite coating, and 5, 6 and 7 are pairs respectivelyGraphene layer of lubricating layer and MoS of main lubricating layer 2 N i layer and transition layer Ti layer, and the whole self-lubricating composite coating consists of the three layers. The bearing is covered on the inner surface of the outer ring of the bearing, the outer surface of the inner ring of the bearing, the surface of the groove and the surface of the metal rubber lubrication ring.
The invention relates to a bearing ring as a tribological performance test object of a coating, which comprises the following steps:
the hardness test adopts a nanoindentation instrument, the indentation depth is set to be 200 nanometers and is not more than 1/10 of the whole thickness of the film, 8 test points on the surface of a sample are uniformly tested, and finally the average hardness is obtained by taking the average value. At the same time, the modulus of elasticity of the lubricating coating material was measured.
The coefficient of friction of the coating is measured by a high temperature reciprocating friction machine as shown in figure 6, the reciprocating frequency is set to be 10Hz, the reciprocating amplitude is set to be 10mm, the time is set to be 30min, and the load is set to be 10N. GCr15 steel balls are selected as grinding balls.
The microscopic morphology of the film section is characterized by adopting a scanning electron microscope as shown in figure 4, and the magnification is 15K times. Characterization of the three-dimensional profile the surface topography and roughness of the coating can be measured using a three-dimensional white light interferometer as shown in fig. 5.
Example 1:
machining grooves: and milling and forming the annular groove by using a numerical control machine tool, and performing rough milling and finish milling. And then polishing the inner wall of the bearing ring by using a polishing machine. The size of the annular groove is consistent with that of the metal rubber lubrication ring, and the positions of the annular groove are distributed on two sides of the inner and outer bearing annular walls.
And (3) equipment installation: an arc-shaped target, an arc-shaped cathode seat, permanent magnet steel and an air rudder bearing clamp are arranged on the magnetron sputtering coating equipment.
Preparing a self-lubricating composite coating: preparing composite coatings on the inner surface of the outer ring of the bearing, the outer surface of the inner ring of the bearing, the surface of the groove and the surface of the metal rubber lubrication ring respectively, wherein the composite coatings comprise a bearing ring substrate treatment and a metal rubber lubrication ring treatment;
the bearing ring substrate is processed as follows:
the method comprises the steps of (A) preprocessing, namely sequentially ultrasonically cleaning a bearing ring with a processed groove in acetone and ethanol for 10min, drying by nitrogen, putting the bearing ring into a sputtering bin, then carrying out bombardment etching preprocessing on the inner wall of the bearing for 15min, setting the bias voltage of an unbalanced magnetron sputtering deposition coating system to 450V, and introducing high-purity argon for 15sccm; ti target current 0.1A.
Preparing a transition layer Ti layer, keeping the pretreated bearing and the metal rubber lubrication ring unchanged, adjusting the Ti target current to 1A, biasing a deposition coating system to 90V, and introducing high-purity argon to 15sccm; the deposition time was 10min.
Step (III) preparing a main lubricating layer Ni-MoS 2 Layer, using high purity metal Ni target and MoS 2 Target double targets are jointly sputtered and deposited for 120min, the bias voltage of a deposition coating system is 40V, high-purity argon gas 10sccm is introduced, moS is carried out 2 Target current 0.8A, ni target current 0.1A deposition time 120min.
Preparing a graphene layer of an auxiliary lubricating layer, firstly weighing 0.001g of graphene particles with purity of more than 90wt%, then adding the graphene particles into a 50ml ethanol solution beaker filled with 97wt% concentration to prepare a graphene suspension with concentration of 20g/ml, then carrying out ultrasonic treatment for 20min to uniformly mix graphene and ethanol, finally uniformly coating a graphene suspension layer on the inner wall of a bearing, and standing for 1min until ethanol is completely volatilized to obtain the graphene layer.
Repeating the steps (one) to (four) on the surface of the metal rubber lubrication ring, so that the surface of the metal rubber lubrication ring is completely covered with the self-lubricating composite coating.
Processing a metal rubber lubrication ring: on the surface of the metal rubber lubrication ring facing the ball, 6 trapezoid medium filling grooves with small surface openings and large internal openings are formed, graphene powder is filled in the trapezoid medium filling grooves, and the height of the graphene powder is aligned with that of the self-lubricating composite coating.
And (3) assembling: and embedding the processed metal rubber ring into an annular groove covered with the self-lubricating composite coating, and keeping the opening of the trapezoid medium filling groove towards the ball, thereby obtaining the bearing applied to the air rudder of the ultra-high sound velocity aircraft.
The prepared bearing surface coating was subjected to the following test, and its properties were tested.
And (3) detecting: mechanical properties
Will be implementedThe ultra-high sound velocity aircraft air rudder bearing ring deposited with the antifriction solid lubrication coating in example 1 was placed in a nanoindenter for detection of nano hardness and elastic modulus. The test result shows that the nano-hardness of the film is 10.1Gpa, and the elastic modulus is 105.1Gpa. The hardness is improved because Ni has higher density and ductility, and more gaps and holes are occupied when deposition is carried out, so that MoS is better inhibited 2 As a loose columnar structure is formed when the transition metal dihalide compound is deposited, the coating becomes more compact, and the mechanical property is improved correspondingly. Meanwhile, the doped Ni effectively improves the plastic deformation resistance of the coating and resists the plastic deformation rate H 3 /E 2 0.09.
And II, detecting: high temperature tribological properties
The superhigh sound velocity aircraft air rudder bearing ring deposited with the antifriction solid lubrication coating in the embodiment 1 is placed into a high temperature friction and wear testing machine to carry out a high temperature wear test, and the test result shows that the friction coefficient is kept to be 0.04-0.06 and the minimum is 0.04 at 100-300 ℃.
And (3) detecting: morphology testing of lubricating coatings
SEM test is carried out on the anti-friction solid lubricating film on the inner wall of the air rudder bearing of the ultra-high sound velocity aircraft, which is prepared in the example 1, and the thickness of the coating is 2.785 mu m, and the roughness of the three-dimensional white light test is 4.562nm.
Example 2:
preparing a self-lubricating composite coating:
the method comprises the steps of (a) preprocessing, namely sequentially ultrasonically cleaning a processed bearing ring in acetone and ethanol for 10min, drying by nitrogen, putting the bearing ring into a sputtering bin, then carrying out bombardment etching preprocessing on the inner wall of the bearing for 15min, setting the bias voltage of an unbalanced magnetron sputtering deposition coating system to be 450V, and introducing high-purity argon for 15sccm; the Ti target current was 0.2A.
Preparing a transition layer Ti layer, keeping the pretreated bearing unchanged, adjusting the Ti target current to 2A, biasing the deposition coating system to 90V, and introducing high-purity argon to 15sccm; the deposition time was 10min.
Step (III) preparing a main lubricating layer Ni-MoS 2 Layer, using high purityMetal Ni target and MoS of (C) 2 Target double targets are jointly sputtered and deposited for 120min, the bias voltage of a deposition coating system is 40V, high-purity argon gas 10sccm is introduced, moS is carried out 2 Target current 0.9A, ni target current 0.2A, deposition time 120min.
Preparing a graphene layer of an auxiliary lubricating layer, firstly weighing 0.001g of graphene particles, then adding the graphene particles into a 50ml beaker filled with a high-purity ethanol solution, preparing a graphene suspension with the concentration of 20g/ml, carrying out ultrasonic treatment for 20min to uniformly mix graphene and ethanol, finally uniformly spreading a graphene suspension layer on the inner wall of a bearing by using a water drop method, standing for 1min, and completely volatilizing alcohol to obtain the graphene layer.
The remaining steps are exactly the same as in example 1.
And (3) detecting: mechanical properties
The ultra-high sound speed aircraft air rudder bearing ring with the antifriction solid lubrication coating deposited in example 2 was placed in a nanoindenter for nano hardness and elastic modulus detection. The test result shows that the nano-hardness of the film is 10.03Gpa, and the elastic modulus is 105.1Gpa.
And II, detecting: high temperature tribological properties
The superhigh sound velocity aircraft air rudder bearing ring deposited with the antifriction solid lubrication coating in the embodiment 2 is placed into a high temperature friction and wear testing machine to carry out a high temperature wear test, and the test result shows that the friction coefficient is kept to be 0.04-0.07 and the minimum is 0.04 at 100-300 ℃.
And (3) detecting: morphology testing of lubricating coatings
SEM testing was performed on the ultra-high sonic aircraft air rudder bearing ring with the anti-friction solid lubrication coating deposited in example 2, to determine a coating thickness of 2.806 μm and a three-dimensional white light test roughness of 4.758nm.
Example 3:
preparing a self-lubricating composite coating:
the method comprises the steps of (a) preprocessing, namely sequentially ultrasonically cleaning a processed bearing ring in acetone and ethanol for 10min, drying by nitrogen, putting the bearing ring into a sputtering bin, then carrying out bombardment etching preprocessing on the inner wall of the bearing for 15min, setting the bias voltage of an unbalanced magnetron sputtering deposition coating system to be 450V, and introducing high-purity argon for 15sccm; the Ti target current was 0.3A.
Preparing a transition layer Ti layer, keeping the pretreated bearing unchanged, adjusting the Ti target current to 3A, biasing the deposition coating system to 90V, and introducing high-purity argon to 15sccm; the deposition time was 10min.
Step (III) preparing a main lubricating layer Ni-MoS 2 Layer, using high purity metal Ni target and MoS 2 Target double targets are jointly sputtered and deposited for 120min, the bias voltage of a deposition coating system is 40V, high-purity argon gas 10sccm is introduced, moS is carried out 2 Target current 1A, ni target current 0.3A deposition time was 120min.
Preparing a graphene layer of an auxiliary lubricating layer, firstly weighing 0.001g of graphene particles, then adding the graphene particles into a 50ml beaker filled with a high-purity ethanol solution, preparing a graphene suspension with the concentration of 20g/ml, carrying out ultrasonic treatment for 20min to uniformly mix graphene and ethanol, finally uniformly spreading a graphene suspension layer on the inner wall of a bearing by using a water drop method, standing for 1min, and completely volatilizing alcohol to obtain the graphene layer.
The remaining steps are exactly the same as in example 1.
And (3) detecting: mechanical properties
The ultra-high sound speed aircraft air rudder bearing ring with the antifriction solid lubrication coating deposited in example 3 was placed in a nanoindenter for nano hardness and elastic modulus detection. The test result shows that the nano-hardness of the film is 10.67Gpa, and the elastic modulus is 107.4Gpa.
And II, detecting: high temperature tribological properties
The superhigh sound velocity aircraft air rudder bearing ring with the antifriction solid lubrication coating deposited in the embodiment 3 is placed into a high temperature friction and wear testing machine to carry out a high temperature wear test, and the test result shows that the friction coefficient is kept to be 0.03-0.06 and the minimum is 0.03 at 100-300 ℃.
And (3) detecting: morphology testing of lubricating coatings
SEM testing was performed on the ultra-high sonic aircraft air rudder bearing ring with the anti-friction solid lubrication coating deposited in example 3, to a coating thickness of 2.8 μm. The roughness of the three-dimensional white light test is 4.213nm.
The anti-friction solid lubricating coating deposited in the example 3 has the thickness of 2.8 mu m, the nano hardness of 10.67GPa, the optimal friction coefficient at the temperature of 100-300 ℃, the minimum of 0.03-0.06 and the minimum of 4.213nm. Has excellent mechanical strength and low friction performance at higher temperature. The problems of bearing seizing and failure caused by insufficient lubrication between the bearing rollers and the bearing rings and increased friction and abrasion due to local temperature rise of the high-speed aircraft air rudder bearing caused by aerodynamic heat and the like are solved.
The foregoing descriptions of specific exemplary embodiments of the present invention are presented for purposes of illustration and description. It is not intended to limit the invention to the precise form disclosed, and obviously many modifications and variations are possible in light of the above teaching. The exemplary embodiments were chosen and described in order to explain the specific principles of the invention and its practical application to thereby enable one skilled in the art to make and utilize the invention in various exemplary embodiments and with various modifications as are suited to the particular use contemplated. It is intended that the scope of the invention be defined by the claims and their equivalents.

Claims (7)

1. The bearing applied to the air rudder of the ultra-high sound velocity aircraft is characterized by comprising a bearing outer ring, a bearing inner ring, balls and a metal rubber lubrication ring;
annular grooves are formed in the ball contact surfaces corresponding to the outer ring and the inner ring of the bearing along the circumferential direction;
the surfaces of the ball contact surfaces with the annular grooves and the metal rubber lubrication rings are respectively and completely covered with the self-lubricating composite coating; the self-lubricating composite coating has a three-layer structure, and is sequentially provided with a Ti layer and a MoS layer from the surface of the substrate to the outside 2 -a Ni layer and a graphene layer;
the metal rubber lubrication ring is arranged in the annular groove;
a plurality of medium filling grooves are formed in the surface, facing the balls, of the metal rubber lubrication ring, and lubrication medium is filled in the grooves; the medium filling groove is of a trapezoid structure with small surface opening and large inner opening.
2. The bearing applied to the air rudder of the ultra-high sound velocity aircraft according to claim 1, wherein the annular grooves are formed in two on the same bearing ring surface and are symmetrically distributed on two sides of the annular wall.
3. The bearing applied to the air rudder of the ultra-high sound velocity aircraft according to claim 1, wherein the thickness of the self-lubricating composite coating is 2.7-2.8 μm, the overall hardness of the coating is more than 10GPa, the elastic modulus is more than 107GP, the plastic deformation resistance is 0.09, the surface roughness of the surface graphene layer is 4-5nm, and the friction coefficient is 0.03-0.06 in the range of 100-300 ℃.
4. A method of manufacturing a bearing for use in an air rudder of an ultra high sound speed aircraft according to any one of claims 1-3, comprising the steps of:
machining grooves: annular grooves are formed in the ball contact surfaces corresponding to the inner surface of the outer ring of the bearing and the outer surface of the inner ring of the bearing along the circumferential direction;
and (3) equipment installation: an arc-shaped target, an arc-shaped cathode seat, permanent magnet steel and an air rudder bearing clamp are arranged on magnetron sputtering coating equipment;
preparing a self-lubricating composite coating: preparing composite coatings on the inner surface of the outer ring of the bearing, the outer surface of the inner ring of the bearing, the surface of the groove and the surface of the metal rubber lubrication ring respectively;
processing a metal rubber lubrication ring: a plurality of medium filling grooves are formed in the surface of the metal rubber lubrication ring facing the ball, and the interior of the metal rubber lubrication ring is filled with lubrication medium;
and (3) assembling: and embedding the metal rubber ring into the groove covered with the self-lubricating composite coating, and keeping the opening of the trapezoid medium filling groove towards the ball.
5. The method for preparing the bearing applied to the air rudder of the ultra-high sound velocity aircraft according to claim 4, wherein the self-lubricating composite coating is prepared by the following steps:
s1, preparing a Ti layer: after polishing the surface of the material, cleaning the surface with acetone and absolute ethyl alcohol in sequence; carrying out bombardment etching pretreatment; finally, sputtering and depositing to obtain a Ti layer;
s2 preparation of MoS 2 -Ni layer: on the Ti layer obtained, pure metal Ni target and MoS were used 2 Target double-target co-sputtering deposition to obtain MoS 2 -a Ni layer;
s3, preparing a graphene layer: mixing multilayer graphene powder with ethanol, performing ultrasound to obtain graphene ethanol suspension, and uniformly spreading the graphene ethanol suspension on the obtained MoS 2 And (3) standing the surface of the Ni layer until the ethanol volatilizes to obtain a graphene layer.
6. The method for preparing the bearing applied to the air rudder of the ultra-high sound speed aircraft according to claim 5, wherein in the step S1, the etching pretreatment conditions are as follows: setting bias voltage of an unbalanced magnetron sputtering deposition coating system to 450-500V, introducing high-purity argon gas to 15-20sccm, and carrying out corrosion pretreatment for 15-20min, wherein the Ti target current is 0.1-0.3A;
the conditions for obtaining the Ti layer by sputtering deposition are as follows: the bias voltage of a deposition coating system is 90-100V, high-purity argon is introduced for 15-20sccm, ti target current is 1-3A, and sputtering deposition time is 10-15min;
in the step S2, moS is obtained by sputter deposition 2 The Ni layer conditions were: the bias voltage of the deposition coating system is 40-60V, high-purity argon gas is introduced for 10-15sccm, moS 2 Target current is 0.7-1A, ni target current is 0.1-0.3A, and sputtering deposition time is 120-130min;
in the step S3, the purity of the multilayer graphene powder is more than 90wt%, the concentration of ethanol is 97wt%, the concentration of graphene ethanol suspension is 20mg/L, and the ultrasonic time is 10-15min.
7. The method for preparing the bearing applied to the air rudder of the ultra-high sound velocity aircraft according to claim 6, wherein the prepared graphene layer is formed by stacking 4-6 layers of graphene particles, the thickness of the graphene layer is 5-8nm, the carbon content is more than or equal to 98%, and the specific surface area is 50-150m 2 /g。
CN202210909075.6A 2022-07-29 2022-07-29 Bearing applied to air rudder of ultra-high sound velocity aircraft and preparation method thereof Active CN115261794B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202210909075.6A CN115261794B (en) 2022-07-29 2022-07-29 Bearing applied to air rudder of ultra-high sound velocity aircraft and preparation method thereof

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202210909075.6A CN115261794B (en) 2022-07-29 2022-07-29 Bearing applied to air rudder of ultra-high sound velocity aircraft and preparation method thereof

Publications (2)

Publication Number Publication Date
CN115261794A CN115261794A (en) 2022-11-01
CN115261794B true CN115261794B (en) 2023-05-05

Family

ID=83747556

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202210909075.6A Active CN115261794B (en) 2022-07-29 2022-07-29 Bearing applied to air rudder of ultra-high sound velocity aircraft and preparation method thereof

Country Status (1)

Country Link
CN (1) CN115261794B (en)

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4630998A (en) * 1984-05-14 1986-12-23 Aerospatiale Societe Nationale Industrielle Apparatus for control of collective and cyclic pitch of the blades of a rotor
JP2009150256A (en) * 2007-12-19 2009-07-09 Ntn Corp Rolling bearing for aircraft
CN102016302A (en) * 2008-02-29 2011-04-13 湘电达尔文有限责任公司 Windturbine comprising a bearing seal
EP2840272A2 (en) * 2013-07-12 2015-02-25 Roller Bearing Company of America, Inc. Electrical conductor for bearing used on actuation system for aircraft lift assisting devices
EP3002211A1 (en) * 2014-09-30 2016-04-06 Messier-Dowty Limited Aircraft landing gear assembly
CN106757012A (en) * 2017-01-18 2017-05-31 燕山大学 A kind of graphene-containing and titanium carbide self-lubricating wear-resistant coating
CN211474684U (en) * 2019-10-17 2020-09-11 广东农工商职业技术学院 Bearing with good lubricating property

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6575631B2 (en) * 1999-05-31 2003-06-10 Nsk Ltd. Rolling bearing and rolling bearing device
EP1719812B1 (en) * 2004-02-09 2018-04-04 NTN Corporation Grease
CN100371496C (en) * 2005-07-07 2008-02-27 浙江大学 Self-lubricated composite plating in multiple layers and preparation method
CN101818332B (en) * 2010-03-23 2012-07-04 中国地质大学（北京） Super-hard self-lubricating diamond/diamond-like composite laminated coating material and preparation method thereof
WO2013108638A1 (en) * 2012-01-19 2013-07-25 日本精工株式会社 Self-lubricating composite material and rolling bearing, linear motion device, ball screw device, linear motion guide device, and transport device using same
FR3004972B1 (en) * 2013-04-26 2018-01-05 Liebherr-Aerospace Toulouse Sas PROCESS FOR MANUFACTURING A WORKPIECE WITH A LUBRICATING SURFACE COATING, PIECE PROVIDED WITH SUCH COATING AND TURBOMACHINE
ES1134261Y (en) * 2014-11-04 2015-02-23 Bolexp Normalizados S L U BEARING FOR LINEAR GUIDANCE
CN107939840A (en) * 2017-12-18 2018-04-20 江苏持华轴承有限公司 A kind of seamless interior surface treatment self-lubricating plain bearing
CN211009566U (en) * 2019-11-10 2020-07-14 新昌金汇关节轴承有限公司 Wear-resisting type bearing
CN112760607B (en) * 2020-12-07 2022-09-02 上海航天设备制造总厂有限公司 Long-life nano multilayer composite solid lubricating film layer under space irradiation and preparation thereof
CN215567258U (en) * 2020-12-22 2022-01-18 浙江双诺轴承科技股份有限公司 Steel-elastic-base PTFE self-lubricating bearing
CN113621912B (en) * 2021-07-28 2023-07-25 重庆文理学院 Gradient self-lubricating composite coating and preparation method thereof
CN114107906B (en) * 2021-11-18 2022-07-15 中国地质大学（北京） Low-friction film for inner wall of solar panel driving bearing and preparation method thereof

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4630998A (en) * 1984-05-14 1986-12-23 Aerospatiale Societe Nationale Industrielle Apparatus for control of collective and cyclic pitch of the blades of a rotor
JP2009150256A (en) * 2007-12-19 2009-07-09 Ntn Corp Rolling bearing for aircraft
CN102016302A (en) * 2008-02-29 2011-04-13 湘电达尔文有限责任公司 Windturbine comprising a bearing seal
EP2840272A2 (en) * 2013-07-12 2015-02-25 Roller Bearing Company of America, Inc. Electrical conductor for bearing used on actuation system for aircraft lift assisting devices
EP3002211A1 (en) * 2014-09-30 2016-04-06 Messier-Dowty Limited Aircraft landing gear assembly
CN106757012A (en) * 2017-01-18 2017-05-31 燕山大学 A kind of graphene-containing and titanium carbide self-lubricating wear-resistant coating
CN211474684U (en) * 2019-10-17 2020-09-11 广东农工商职业技术学院 Bearing with good lubricating property

Also Published As

Publication number Publication date
CN115261794A (en) 2022-11-01

Similar Documents

Publication Publication Date Title
Wang et al. Rolling contact silicon nitride bearing technology: a review of recent research
Yuan et al. Effect of laser surface texturing (LST) on tribological behavior of double glow plasma surface zirconizing coating on Ti6Al4V alloy
JPH01279119A (en) Mechanical member
US6764219B2 (en) Full complement antifriction bearing
EP2554866B1 (en) Anti-friction bearing
Fox et al. Hard lubricating coatings for cutting and forming tools and mechanical components
WO2013042765A1 (en) Hard film, hard film formed body, and rolling bearing
CN112760610B (en) High-entropy nitride coating for surface protection of aviation bearing and preparation method thereof
Zhao et al. Friction and wear behavior of different seal materials under water-lubricated conditions
Miao et al. Investigation on the lubricity of self-lubricating ball bearings for cryogenic turbine pump
CN115261794B (en) Bearing applied to air rudder of ultra-high sound velocity aircraft and preparation method thereof
US20210317877A1 (en) Rolling bearing, wheel support device, and wind power generation rotor shaft support device
JP5938321B2 (en) Hard film and film forming method thereof, hard film forming body and manufacturing method thereof
WO2020045455A1 (en) Double-row self-aligning roller bearing and main shaft support device for wind generation equipped with same
JP7373341B2 (en) Rolling bearings and main shaft support devices for wind power generation
Stephan et al. Investigation of the coating of hydrodynamic plain bearing contact surfaces by means of Extreme High-Speed Laser Material Deposition (EHLA)
CN206738167U (en) Rotary compressor and its pump housing
WO2020067334A1 (en) Rolling bearing, and main shaft support device for wind power generation
Cao et al. Preparation of a Self‐Lubricating Cu/h‐BN Coating on Cemented Carbide
JP5620860B2 (en) Rolling bearing
Spath et al. Kinematics, frictional characteristics and wear reduction by PVD coating on ball screw drives
JP2024014629A (en) rolling bearing
CN111271372B (en) Inverted sliding bearing with three-oil-blade mandrel structure
Li et al. Vacuum tribological properties in Cr-doped H-DLC self-lubricating radial spherical plain bearings
JP2008151264A (en) Cage for roller bearing

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
TR01 Transfer of patent right

Effective date of registration: 20230718

Address after: 100083 No. 29, Haidian District, Beijing, Xueyuan Road

Patentee after: China University of Geosciences (Beijing)

Patentee after: INSTITUTE OF FLEXIBLE ELECTRONICS TECHNOLOGY OF THU, ZHEJIANG

Patentee after: Zhengzhou Research Institute China University of Geosciences (Beijing)

Address before: 100083 No. 29, Haidian District, Beijing, Xueyuan Road

Patentee before: China University of Geosciences (Beijing)

Patentee before: Zhengzhou Research Institute China University of Geosciences (Beijing)

TR01 Transfer of patent right