Piezoelectric micro- injection active oil supplement system for space attitude control bearing assembly

Abstract

This invention provides a piezoelectric micro-jet active oil replenishment system for space attitude control bearing assemblies, comprising: at least one piezoelectric micro-jet oil replenishment component; the piezoelectric micro-jet oil replenishment component includes an oil chamber base, a piezoelectric ejector module, and a spring piston assembly; the piezoelectric ejector module includes an ejector pin, an ejector pin piston, and a piezoelectric stack, the ejector pin piston being disposed on the oil chamber base, the piezoelectric stack and the ejector pin being disposed on the ejector pin piston, the piezoelectric stack enabling deformation of the ejector pin piston, the ejector pin piston driving the ejector pin to reciprocate through its deformation; the oil chamber base is provided with micro-oil holes, the micro-oil holes corresponding to the bearing settings of the bearing assembly, the ejector pin being sealed to the oil chamber base, the ejector pin being able to seal the micro-oil holes; the oil chamber base is provided with a second through hole communicating with the micro-oil holes, the spring piston assembly being disposed within the second through hole. This invention can control the oil supply quantity, oil supply timing, and oil supply position of active oil replenishment, improving oil supply efficiency and effective lubrication rate.

Description

Technical Field

[0001] This invention relates to the field of active lubrication technology for space bearing assemblies, specifically to a piezoelectric micro-jet active lubrication system for space attitude control bearing assemblies. Background Technology

[0002] Space attitude control capabilities, characterized by high-angle, rapid maneuverability, high-precision, high-stability pointing, and long-life on-orbit service, are among the core technologies of satellites. They directly impact the completion of critical missions such as military reconnaissance, missile early warning, and Earth observation, and are a significant reflection of my country's national defense strength and aerospace technology level. Zero-momentum wheels, due to their advantages of high output torque accuracy, significant torque amplification effect, and long service life, enable space attitude control systems to possess high-torque, high-precision attitude control output capabilities, thereby meeting the control requirements of high-angle, rapid maneuverability, and high-precision, high-stability pointing.

[0003] Statistics show that approximately 37% of satellite malfunctions are caused by failures in the momentum wheel attitude control system, primarily due to deterioration in the lubrication of the bearing assembly. Limited by current research bottlenecks in bearing assembly lubrication technology, bearing assemblies in long-term on-orbit service experience decreased frictional performance and unstable frictional torque, leading to problems such as increased current output, abnormal speed response, and jamming in the momentum wheel. This poses a significant challenge to the reliable and durable lubrication required for the momentum wheel bearing assembly.

[0004] To address the challenge of reliable lubrication of momentum wheel bearing assemblies over long space lifespans, scholars both domestically and internationally have proposed two lubrication schemes: passive and active. However, due to space constraints and the limitations of passive lubrication mechanisms, this method struggles to achieve long-term effective lubrication under low-speed maneuvering conditions. Active lubrication technology offers advantages such as controllable lubrication volume, timing, and location, and enables closed-loop automatic control of lubrication, improving efficiency and effective lubrication rate. With the same oil capacity, it can increase the reliable lubrication time of the bearing assembly, extending the satellite's on-orbit service life. However, both excessive and insufficient lubrication can increase the frictional torque of the bearing assembly. Excessive lubrication can also lead to insufficient lubrication later and internal contamination. Therefore, long-term effective lubrication in space remains a critical issue that urgently needs to be addressed in the aerospace field.

[0005] Patent document CN210949567U discloses a lubricated oil-replenishing bearing, including an inner ring, an outer ring, and rollers. The inner and outer rings are combined to form a rolling cavity for the rollers to rotate. An oil replenishing ring is included. The outer ring has an annular oil replenishing groove for the oil replenishing ring to insert into, and an annular oil outlet groove is also provided on the outer ring. The annular oil outlet groove is connected to the rolling cavity. A grease reservoir is hollowly formed on the oil replenishing ring. Several oil outlet chambers, connected to the grease reservoir, are hollowly formed on the oil replenishing ring. An oil outlet block is slidably disposed within each oil outlet chamber. The oil outlet chamber has an opening for the oil outlet block to protrude or retract. An oil outlet hole for conveying grease is provided on the oil outlet block. When the oil outlet block slides to protrude from the opening, it inserts into the annular oil outlet groove, allowing grease to flow through the oil outlet hole into the annular oil outlet groove. However, the patent document still has the problem that both excessive and insufficient oil supply will lead to an increase in the frictional torque of the bearing assembly, and excessive oil supply will also lead to insufficient oil supply and internal contamination in the later stage.

[0006] Patent document CN216280580U discloses an oil replenishment device for centrifuge bearings and a centrifuge having the same. The centrifuge has a front bearing oil replenishment port and a rear bearing oil replenishment port. The oil replenishment device includes an oil storage device, a pressurizing device, a conveying device, and a control module. The oil storage device stores the lubricating oil required by the centrifuge; the pressurizing device pressurizes the oil storage device; the conveying device includes a galvanized steel pipe, one end of which is connected to the outlet of the oil storage device, and the two outlets of the conveying device are respectively connected to the front bearing oil replenishment port and the rear bearing oil replenishment port; the control module has a timer, under the action of the timer, the pressurizing device can pressurize or depressurize the oil storage device within a preset time, thereby replenishing or stopping oil replenishment to the centrifuge. However, the technical solution of that patent document is different from the technical solution of this application. Summary of the Invention

[0007] To address the shortcomings of existing technologies, the purpose of this invention is to provide a piezoelectric micro-jet active oil replenishment system for spatial attitude control bearing assemblies.

[0008] According to the present invention, a piezoelectric micro-jet active oil replenishment system for a space attitude control bearing assembly includes: at least one piezoelectric micro-jet oil replenishment component; the piezoelectric micro-jet oil replenishment component includes an oil chamber substrate, a piezoelectric pin module, and a spring piston assembly;

[0009] The piezoelectric ejector module includes an ejector, an ejector piston, and a piezoelectric stack. The ejector piston is disposed on the oil cavity substrate. The piezoelectric stack and the ejector are disposed on the ejector piston. The piezoelectric stack can cause the ejector piston to deform. The ejector piston drives the ejector to reciprocate through its deformation.

[0010] The oil cavity substrate is provided with micro oil holes, which correspond to the bearings of the bearing assembly. The ejector pin is sealed to the oil cavity substrate and can seal the micro oil holes. The oil cavity substrate is provided with a second through hole that communicates with the micro oil holes. The spring piston assembly is disposed in the second through hole and is used to provide continuous back pressure to the lubricating oil in the second through hole.

[0011] Preferably, the piezoelectric micro-jet oil replenishment assembly is configured as two, and the bearing assembly includes two bearings respectively disposed at both ends of the connecting shaft;

[0012] Two piezoelectric micro-spraying lubrication components are mounted on the connecting shaft, and the two piezoelectric micro-spraying components are assembled in opposite directions to simultaneously provide active lubrication to the bearings at both ends.

[0013] The oil cavity substrate is mounted on the connecting shaft.

[0014] Preferably, the oil cavity substrate is provided with a first through hole;

[0015] The first through hole is connected to the second through hole and the micro oil hole. The ejector piston has one end sealed to the inner wall of the first through hole, and the ejector is disposed inside the first through hole.

[0016] Preferably, the ejector piston is provided with a first sealing ring;

[0017] The ejector piston is provided with a first annular groove, and the first sealing ring is disposed in the first annular groove.

[0018] Preferably, the ejector pin includes a conical portion and a hemispherical portion;

[0019] The hemispherical portion is disposed on the conical portion, which is disposed on the ejector piston, and the hemispherical portion is used to abut and seal the micro-oil hole.

[0020] Preferably, a first end cap and a second end cap are respectively provided at both ends of the oil cavity substrate;

[0021] The micro-oil hole is provided on the first end cap, and the end of the ejector piston away from the ejector pin is connected to the second end cap.

[0022] Preferably, the spring-piston assembly includes a piston and a spring; a second end cap is provided at one end of the oil chamber base;

[0023] The piston is provided with a first connecting post, the second end cap is provided with a second connecting post, and the two ends of the spring are respectively sleeved on the first connecting post and the second connecting post;

[0024] The first connecting post is provided with a first spring locking shaft, and the second connecting post is provided with a second spring locking shaft. The first spring locking shaft and the second spring locking shaft are used to lock and fix the spring.

[0025] The first connecting post is provided with a fifth through hole for inserting the first spring locking shaft, and the second connecting post is provided with a sixth through hole for inserting the second spring locking shaft.

[0026] The piston and the spring are disposed within the second through hole.

[0027] Preferably, the spring piston assembly further includes a second sealing ring;

[0028] The piston is provided with a second annular groove, and the second sealing ring is disposed in the second annular groove.

[0029] Preferably, the oil cavity substrate has a planar symmetrical structure and an internal U-shaped structure;

[0030] The piezoelectric pin module is located in the middle of the U-shaped structure. There are two second through holes, which are respectively located on the two symmetrical support structures of the U-shaped structure, on both sides of the piezoelectric pin module.

[0031] The oil cavity substrate is provided with an installation curved surface adapted to the connecting shaft.

[0032] Preferably, the piezoelectric pin module further includes a first connecting layer, a second connecting layer, and a fixing plate;

[0033] The first connecting layer and the second connecting layer are respectively disposed at both ends of the piezoelectric stack, and the two ends of the piezoelectric stack are respectively connected to the ejector piston through the first connecting layer and the second connecting layer;

[0034] The oil cavity substrate is provided with a first threaded hole, and the fixing plate is provided with a third through hole. The piezoelectric pin module is connected to the oil cavity substrate by screws at the positions of the first threaded hole and the third through hole.

[0035] Compared with the prior art, the present invention has the following beneficial effects:

[0036] 1. The purpose of this invention is to develop a piezoelectric micro-jet active oil replenishment system that can achieve long-term, effective and controllable oil replenishment of space attitude control bearing components, increase the reliable lubrication time of bearing components, and thus extend the on-orbit service life of satellites.

[0037] 2. The piezoelectric micro-spray active oil replenishment system of the present invention utilizes the piezoelectric ejector module to achieve the tight contact and separation of the ejector and the micro-oil hole of the front end cover. Combined with the back pressure applied to the lubricating oil in the oil chamber by the spring piston assembly, the piezoelectric micro-spray active oil replenishment system can spray lubricating oil when the ejector and the micro-oil hole of the front end cover are in a separated state, and prevent the oil from spraying out when they are in a tight contact state. The oil spray control strategy has high reliability.

[0038] 3. This invention utilizes the characteristics of piezoelectric stacks, such as fast response speed, high positioning accuracy, and resistance to electromagnetic interference, to precisely control the oil supply and timing of bearing components in a space environment, thereby improving oil supply efficiency and effective lubrication rate, and increasing the reliable lubrication time of bearing components.

[0039] 4. The piezoelectric micro-jet active oil replenishment system of the present invention includes two piezoelectric micro-jet oil replenishment components, namely a left piezoelectric micro-jet oil replenishment component and a right piezoelectric micro-jet oil replenishment component. The two components have the same structure and are both arranged in a 180-degree ring structure, and are arranged in opposite directions on the shaft surface, which can simultaneously replenish the bearing components on both sides of the piezoelectric micro-jet active oil replenishment system.

[0040] 5. The oil chamber substrate, piezoelectric ejector module and spring piston assembly of the present invention can form a sealed oil chamber with variable capacity. Each component has a sealing ring in the relative movement position, which has good sealing performance. The back pressure provided by the spring piston assembly can meet the requirements of long-term continuous oil injection.

[0041] 6. The piezoelectric micro-injection active oil replenishment system of the present invention has a compact structure, which can reduce the system design space. Attached Figure Description

[0042] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0043] Figure 1 This is a schematic diagram of the overall structure of the piezoelectric micro-jet active oil replenishment system for spatial attitude control bearing components in this invention.

[0044] Figure 2 This is an exploded view of the piezoelectric micro-jet oil replenishment component in this invention.

[0045] Figure 3 This is a schematic diagram of the structure of the oil cavity substrate in this invention.

[0046] Figure 4 This is a schematic diagram of the piezoelectric pin module in this invention.

[0047] Figure 5 This is a schematic diagram of the spring piston assembly in this invention.

[0048] Figure 6This is an exploded view of the spring-piston assembly in this invention.

[0049] The diagram shows:

[0050] Bearing assembly 1 First annular groove 2341

[0051] Bearing 101, Fixing plate 235

[0052] Piezoelectric micro-injection oil replenishment component 2 Third through hole 2351

[0053] First end cap 21 First connecting layer 236

[0054] Micropores 211 Second connecting layer 237

[0055] Oil chamber base 22 Spring piston assembly 24

[0056] First threaded hole 221 Piston 241

[0057] First through hole 222 Second annular groove 2411

[0058] Second through hole 223 Fourth through hole 2412

[0059] Second threaded hole 224 First connecting post 2413

[0060] Piezoelectric ejector module 23 Second sealing ring 242

[0061] Ejector pin 231, Spring 243

[0062] First external thread 2311 First spring locking shaft 244

[0063] Hemispherical part 2312 Second spring locking shaft 245

[0064] Conical part 2313 Second end cap 25

[0065] Ejector piston 232, fifth through hole 251

[0066] Third threaded hole 2321, sixth through hole 252

[0067] piezoelectric stack 233 Second connecting post 253

[0068] First sealing ring 234 Detailed Implementation

[0069] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0070] Example 1:

[0071] like Figures 1-6 As shown, this embodiment provides a piezoelectric micro-jet active oil replenishment system for a space attitude control bearing assembly, including: at least one piezoelectric micro-jet oil replenishment component 2. The piezoelectric micro-jet oil replenishment component 2 includes an oil chamber substrate 22, a piezoelectric ejector module 23, and a spring piston assembly 24. The piezoelectric ejector module 23 includes an ejector pin 231, an ejector piston 232, and a piezoelectric stack 233. The ejector piston 232 is disposed on the oil chamber substrate 22, and the piezoelectric stack 233 and the ejector pin 231 are disposed on the ejector piston 232. The piezoelectric stack 233 enables the ejector piston to... 232 deforms, and the ejector piston 232 drives the ejector pin 231 to reciprocate through its deformation. The oil cavity base 22 is provided with a micro oil hole 211, which corresponds to the bearing 101 of the bearing assembly 1. The ejector pin 231 is sealed to the oil cavity base 22, and the ejector pin 231 can seal the micro oil hole 211. The oil cavity base 22 is provided with a second through hole 223 that communicates with the micro oil hole 211. The spring piston assembly 24 is disposed in the second through hole 223 to provide continuous back pressure to the lubricating oil in the second through hole 223.

[0072] The ejector pin 231 includes a conical portion 2313 and a hemispherical portion 2312. The hemispherical portion 2312 is disposed on the conical portion 2313, which is disposed on the ejector piston 232. The hemispherical portion 2312 is used to abut against the sealing micro-oil hole 211. The oil chamber base 22 has a first end cap 21 and a second end cap 25 respectively disposed at both ends. The micro-oil hole 211 is disposed on the first end cap 21, and the end of the ejector piston 232 away from the ejector pin 231 is connected to the second end cap 25.

[0073] The oil cavity substrate 22 is provided with a first through hole 222, which is connected to a second through hole 223 and a micro oil hole 211. One end of the ejector piston 232 with an ejector pin 231 is sealed to the inner wall of the first through hole 222, and the ejector pin 231 is disposed in the first through hole 222. The ejector piston 232 is provided with a first sealing ring 234 and a first annular groove 2341, and the first sealing ring 234 is disposed in the first annular groove 2341.

[0074] The spring-piston assembly 24 includes a piston 241 and a spring 243. A second end cap 25 is provided at one end of the oil chamber base 22. A first connecting post 2413 is provided on the piston 241, and a second connecting post 253 is provided on the second end cap 25. The two ends of the spring 243 are respectively sleeved on the first connecting post 2413 and the second connecting post 253. A first spring locking shaft 244 is provided on the first connecting post 2413, and a second spring locking shaft 245 is provided on the second connecting post 253. The first spring locking shaft 244 and the second spring locking shaft 245 are used to lock and fix the spring 243. A fourth through hole 2412 for inserting the first spring locking shaft 244 is provided on the first connecting post 2413, and a sixth through hole 252 for inserting the second spring locking shaft 245 is provided on the second connecting post 253. The piston 241 and the spring 243 are disposed in the second through hole 223. The spring piston assembly 24 also includes a second sealing ring 242. The piston 241 is provided with a second annular groove 2411, and the second sealing ring 242 is disposed in the second annular groove 2411.

[0075] The piezoelectric ejector module 23 also includes a first connecting layer 236, a second connecting layer 237, and a fixing plate 235. The first connecting layer 236 and the second connecting layer 237 are respectively disposed at both ends of the piezoelectric stack 233. The two ends of the piezoelectric stack 233 are connected to the ejector piston 232 through the first connecting layer 236 and the second connecting layer 237, respectively. The oil cavity substrate 22 is provided with a first threaded hole 221, and the fixing plate 235 is provided with a third through hole 2351. The piezoelectric ejector module 23 and the oil cavity substrate 22 are connected by screws at the positions of the first threaded hole 221 and the third through hole 2351.

[0076] The oil cavity base 22 has a planar symmetrical structure and an internal U-shaped structure. The piezoelectric ejector module 23 is located in the middle of the U-shaped structure. There are two second through holes 223, which are respectively located on the two symmetrical support structures of the U-shaped structure, on both sides of the piezoelectric ejector module 23. The oil cavity base 22 has an installation curved surface that is adapted to the connecting shaft.

[0077] Two piezoelectric micro-spraying oil replenishment components 2 are provided. The bearing assembly 1 includes two bearings 10 respectively set at both ends of the connecting shaft. The two piezoelectric micro-spraying oil replenishment components 2 are set on the connecting shaft. The two piezoelectric micro-spraying components are arranged in opposite directions to actively replenish oil to the bearings 101 at both ends at the same time. The oil chamber base 22 is set on the connecting shaft.

[0078] Example 2:

[0079] Those skilled in the art can understand this embodiment as a more specific description of Embodiment 1.

[0080] This embodiment provides a piezoelectric micro-jet active oil replenishment system for spatial attitude control bearing assemblies, including a left piezoelectric micro-jet oil replenishment component and a right piezoelectric micro-jet oil replenishment component.

[0081] The left and right piezoelectric micro-jet oil replenishment components have identical structures, both including an oil chamber substrate, a piezoelectric ejector module, a spring piston assembly, a front end cover, and a rear end cover. The inner surfaces of both components are cylindrical, allowing them to be mounted on a shaft surface. The left and right piezoelectric micro-jet oil replenishment components are arranged in opposite directions, enabling simultaneous active oil replenishment to the spatial attitude control bearing assemblies on both sides.

[0082] The front end of the oil cavity substrate is connected to the front end cover, and the rear end of the oil cavity substrate is connected to the rear end cover.

[0083] The piezoelectric ejector module includes a piezoelectric stack, a fixing plate, an ejector pin, an ejector pin piston, and a first sealing ring. The piezoelectric ejector module is connected to the oil cavity substrate through the fixing plate. Under voltage excitation, the piezoelectric stack can deform along the axial direction of the ejector pin piston, thereby driving the ejector pin to reciprocate along the axial direction of the ejector pin piston, realizing the tight contact and separation between the ejector pin and the micro-oil hole on the front end cover.

[0084] The spring-piston assembly includes a piston, a spring, a first spring locking shaft, a second spring locking shaft, and a second sealing ring. The spring-piston assembly can continuously provide back pressure to the lubricating oil in the oil chamber matrix.

[0085] The oil cavity substrate has a planar symmetrical structure and is provided with a first through hole, a second through hole, a first threaded hole, and a second threaded hole. The interior of the oil cavity substrate has a U-shaped structure.

[0086] The micro-oil hole has a diameter of 0.4 mm and is coaxial with the ejector piston. The front end of the oil chamber substrate is connected to the rear end of the front end cover by welding.

[0087] The rear end cover has a fifth through hole and a sixth through hole. The oil cavity base and the rear end cover are connected by screws at the positions of the fifth through hole and the second threaded hole. The sixth through hole is used to insert the second spring locking shaft and is welded to the rear end cover at the position of the sixth through hole.

[0088] A first annular groove is provided near the front end of the ejector piston to accommodate a first sealing ring, which seals the oil cavity base at the contact point with the ejector piston.

[0089] A rectangular cavity is provided in the middle of the ejector piston for placing the piezoelectric stack.

[0090] The front end of the ejector piston has a third threaded hole, and the rear end of the ejector pin has a first external threaded surface for connecting the ejector pin and the ejector piston.

[0091] The front end of the piezoelectric stack is coated with a first epoxy resin AB adhesive for connecting the fixing plate, and the rear end of the piezoelectric stack is coated with a second epoxy resin AB adhesive for connecting the inner side of the rectangular cavity of the ejector piston.

[0092] The fixing plate has a third through hole at both ends, and the fixing plate and the oil cavity base are connected by screws at the third through hole and the first threaded hole.

[0093] A second annular groove is provided near the front end of the piston to accommodate a second sealing ring, which seals the contact point between the second through hole of the oil chamber substrate and the piston. A fourth radial through hole is provided at the rear end of the piston to insert the first spring locking shaft, which is then welded to the piston at the fourth through hole.

[0094] The front end of the spring is pressed by the first spring locking shaft, and the rear end of the spring is pressed by the second spring locking shaft.

[0095] This embodiment provides a piezoelectric micro-jet active oil replenishment system for space attitude control bearing assemblies, including an oil chamber substrate, a piezoelectric ejector module, a spring piston assembly, a front end cover, and a rear end cover. The front and rear ends of the oil chamber substrate are respectively connected to the front end cover and the rear end cover. The piezoelectric ejector module is connected to the oil chamber substrate via a fixing plate. One end of the spring in the spring piston assembly is connected to the rear end cover. The piezoelectric ejector module includes a piezoelectric stack, an ejector pin, an ejector pin piston, and a first sealing ring. Under voltage excitation, the piezoelectric stack can deform along the axial direction of the ejector pin piston, driving the ejector pin to reciprocate along the axial direction of the ejector pin piston, realizing the tight contact and separation between the ejector pin and the micro-oil hole on the front end cover, thereby achieving the goal of precise lubrication oil replenishment. The spring piston assembly uses a spring to continuously provide back pressure to the lubricating oil in the oil chamber substrate. The structure of this embodiment can control the oil supply quantity, timing, and position of active oil replenishment, improving oil supply efficiency and effective lubrication rate.

[0096] Example 3:

[0097] Those skilled in the art can understand this embodiment as a more specific description of Embodiment 1.

[0098] like Figure 1As shown, this embodiment proposes a piezoelectric micro-jet active lubrication system for spatial attitude control bearing assemblies, mainly comprising two piezoelectric micro-jet lubrication components: a left piezoelectric micro-jet lubrication component and a right piezoelectric micro-jet lubrication component. The left and right piezoelectric micro-jet lubrication components have identical structures, and their inner surfaces are cylindrical. They are mounted on the shaft surface in a reverse assembly arrangement, enabling simultaneous active lubrication of the spatial attitude control bearing assemblies 1 on both sides.

[0099] Figure 2 This is an exploded view of the piezoelectric micro-jet oil replenishment assembly 2, including an oil chamber base 22, a piezoelectric ejector module 23, a spring piston assembly 24, a first end cap 21, and a second end cap 25. The front end of the oil chamber base 22 is welded to the first end cap 21, and the oil chamber base 22 and the second end cap 25 are connected by screws at the second threaded hole 224. The piezoelectric ejector module 23 is connected to the oil chamber base 22 by screws at the first threaded hole 221, and after the screws are tightened, the ejector 231 and the first end cap 21 are tightly fitted at the micro-oil hole 211. The spring piston assembly 24 can use the elastic force of the spring 243 to provide a continuous and powerful pressure to the lubricating oil in the oil chamber base 22, and can push the lubricating oil out at the moment the piezoelectric ejector module 23 separates from the micro-oil hole 211 to achieve lubrication of the bearing assembly 1 for spatial attitude control. The first end cap 21 is the front end cap, and the second end cap 25 is the rear end cap.

[0100] Figure 3 This is a schematic diagram of the oil cavity substrate 22. The oil cavity substrate 22 has a planar symmetrical structure and an internal U-shaped structure. The front end of the oil cavity substrate 22 is welded to the first end cap 21. The oil cavity substrate 22 is sealed with the piezoelectric pin module 23 at the first through hole 222 using the first sealing ring 234. The oil cavity substrate 22 is sealed with the spring piston assembly 24 at the second through hole 223 using the second sealing ring 242. A variable capacity sealed cavity is formed between the oil cavity substrate 22, the piezoelectric pin module 23 and the spring piston assembly 24.

[0101] Figure 4This is a schematic diagram of the piezoelectric ejector module 23. The piezoelectric ejector module 23 includes a piezoelectric stack 233, a fixing plate 235, an ejector pin 231, an ejector piston 232, and a first sealing ring 234. The ejector pin 231 is connected to the ejector piston 232 through a first external thread 2311 and a third threaded hole 2321. The first sealing ring 234 is fitted onto the first annular groove 2341 of the ejector piston 232. The piezoelectric stack 233 is connected to the fixing plate 235 through a first connecting layer 236. Next, the piezoelectric stack 233 is connected to the ejector piston 232 via the second connecting layer 237. The piezoelectric ejector module 23 is connected to the oil cavity substrate 22 via screws at the third through hole 2351 of the fixing plate 235. Under voltage excitation, the piezoelectric stack 233 can deform along the axial direction of the ejector piston 232, thereby driving the ejector 231 to reciprocate along the ejector piston axis 232, realizing the tight contact and separation between the ejector 231 and the micro oil hole 211. The first connecting layer 236 and the second connecting layer 237 are both epoxy resin AB glue.

[0102] Figure 5 and Figure 6 These are a structural schematic diagram and an exploded view of the spring-piston assembly 24. The spring-piston assembly 24 includes a piston 241, a spring 243, a first spring locking shaft 244, a second spring locking shaft 245, and a second sealing ring 242. The second sealing ring 242 is fitted onto the second annular groove 2411 of the piston 241. The piston 241 and the first spring locking shaft 244 are welded together at the fourth through hole 2412. The second spring locking shaft 245 and the rear end cover 25 are welded together at the sixth through hole 252. The first spring locking shaft 244 and the second spring locking shaft 245 respectively press the front end and the rear end of the spring 243. The spring-piston assembly 24 can continuously provide back pressure to the lubricating oil in the oil chamber base 22 through the spring 243.

[0103] Working principle:

[0104] In the initial state, the piezoelectric micro-jet active oil replenishment system has the piezoelectric ejector module 23 tightly attached to the micro-oil hole 211 on the first end cap 21, and the spring piston assembly 24 provides sufficient back pressure for the lubricating oil in the oil chamber substrate 22. When the piezoelectric stack 233 is excited by voltage, it generates high-frequency vibration along the axial direction of the ejector piston 232, causing the ejector piston 232 to move axially, thereby achieving the tight contact and separation between the ejector 231 and the micro-oil hole 211. When the ejector 231 separates from the micro-oil hole 211, the lubricating oil is sprayed onto the spatial attitude control bearing assembly 1 under the action of back pressure, achieving the purpose of lubrication. The piezoelectric micro-jet active oil replenishment system utilizes the characteristics of fast response speed, high positioning accuracy, and anti-electromagnetic interference of the piezoelectric stack 233 to accurately control the oil supply quantity and timing in a space environment, improving oil supply efficiency and effective lubrication rate, and increasing the reliable lubrication time of the spatial attitude control bearing assembly 1.

[0105] This invention can control the amount of oil supplied, the timing of oil supply, and the location of oil supply for active oil replenishment, thereby improving oil supply efficiency and effective lubrication rate.

[0106] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0107] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A piezoelectric micro-jet active oil replenishment system for space attitude control bearing assemblies, characterized in that, include: At least one piezoelectric micro-jet oil replenishment component (2); the piezoelectric micro-jet oil replenishment component (2) includes an oil chamber substrate (22), a piezoelectric pin module (23), and a spring piston assembly (24); The piezoelectric ejector module (23) includes an ejector (231), an ejector piston (232), and a piezoelectric stack (233). The ejector piston (232) is disposed on the oil cavity substrate (22). The piezoelectric stack (233) and the ejector (231) are disposed on the ejector piston (232). The piezoelectric stack (233) can cause the ejector piston (232) to deform. The ejector piston (232) drives the ejector (231) to reciprocate through its deformation. The oil cavity substrate (22) is provided with micro oil holes (211), which correspond to the bearings (101) of the bearing assembly (1). The ejector pin (231) is sealed to the oil cavity substrate (22) and can seal the micro oil holes (211). The oil cavity substrate (22) is provided with a second through hole (223) communicating with the micro oil holes (211). The spring piston assembly (24) is disposed in the second through hole (223) to provide continuous back pressure to the lubricating oil in the second through hole (223). The oil cavity substrate (22) is provided with a first through hole (222); The first through hole (222) is connected to the second through hole (223) and the micro oil hole (211), and the ejector pin (231) is disposed in the first through hole (222).

2. The piezoelectric micro-jet active oil replenishment system for space attitude control bearing assemblies according to claim 1, characterized in that, The piezoelectric micro-spray oil replenishment component (2) is configured as two, and the bearing assembly (1) includes two bearings (101) respectively disposed at both ends of the connecting shaft. Two piezoelectric micro-spraying oil replenishment components (2) are mounted on the connecting shaft. The two piezoelectric micro-spraying components are arranged in opposite directions to simultaneously replenish the bearings (101) at both ends. The oil cavity substrate (22) is mounted on the connecting shaft.

3. The piezoelectric micro-jet active oil replenishment system for space attitude control bearing assemblies according to claim 1, characterized in that, The ejector piston (232) is configured such that one end of the ejector (231) is sealed to the inner wall of the first through hole (222).

4. The piezoelectric micro-jet active oil replenishment system for space attitude control bearing assemblies according to claim 3, characterized in that, The ejector piston (232) is provided with a first sealing ring (234). The ejector piston (232) is provided with a first annular groove (2341), and the first sealing ring (234) is disposed in the first annular groove (2341).

5. The piezoelectric micro-jet active oil replenishment system for space attitude control bearing assemblies according to claim 1, characterized in that, The ejector pin (231) includes a conical portion (2313) and a hemispherical portion (2312). The hemispherical part (2312) is disposed on the conical part (2313), the conical part (2313) is disposed on the ejector piston (232), and the hemispherical part (2312) is used to abut and seal the micro oil hole (211).

6. The piezoelectric micro-jet active oil replenishment system for space attitude control bearing assemblies according to claim 1, characterized in that, The oil cavity substrate (22) is provided with a first end cap (21) and a second end cap (25) at both ends respectively; The micro-oil hole (211) is provided on the first end cap (21), and the end of the ejector piston (232) away from the ejector (231) is connected to the second end cap (25).

7. The piezoelectric micro-jet active oil replenishment system for space attitude control bearing assemblies according to claim 1, characterized in that, The spring piston assembly (24) includes a piston (241) and a spring (243); a second end cap (25) is provided at one end of the oil chamber base (22); The piston (241) is provided with a first connecting post (2413), and the second end cap (25) is provided with a second connecting post (253). The two ends of the spring (243) are respectively sleeved on the first connecting post (2413) and the second connecting post (253). The first connecting post (2413) is provided with a first spring locking shaft (244), and the second connecting post (253) is provided with a second spring locking shaft (245). The first spring locking shaft (244) and the second spring locking shaft (245) are used to lock and fix the spring (243). The first connecting post (2413) is provided with a fourth through hole (2412) for inserting the first spring locking shaft (244), and the second connecting post (253) is provided with a sixth through hole (252) for inserting the second spring locking shaft (245). The piston (241) and the spring (243) are disposed in the second through hole (223).

8. The piezoelectric micro-jet active oil replenishment system for space attitude control bearing assemblies according to claim 7, characterized in that, The spring piston assembly (24) also includes a second sealing ring (242). The piston (241) is provided with a second annular groove (2411), and the second sealing ring (242) is disposed in the second annular groove (2411).

9. The piezoelectric micro-jet active oil replenishment system for space attitude control bearing assemblies according to claim 2, characterized in that, The oil cavity substrate (22) has a planar symmetrical structure and an internal U-shaped structure; The piezoelectric pin module (23) is located in the middle of the U-shaped structure. There are two second through holes (223). The two second through holes (223) are respectively located on the two symmetrical support structures of the U-shaped structure, on both sides of the piezoelectric pin module (23). The oil cavity substrate (22) is provided with an installation curved surface adapted to the connecting shaft.

10. The piezoelectric micro-jet active oil replenishment system for space attitude control bearing assemblies according to claim 1, characterized in that, The piezoelectric pin module (23) also includes a first connecting layer (236), a second connecting layer (237), and a fixing plate (235); The first connecting layer (236) and the second connecting layer (237) are respectively disposed at both ends of the piezoelectric stack (233), and the two ends of the piezoelectric stack (233) are respectively connected to the ejector piston (232) through the first connecting layer (236) and the second connecting layer (237); The oil cavity substrate (22) is provided with a first threaded hole (221), and the fixing plate (235) is provided with a third through hole (2351). The piezoelectric pin module (23) and the oil cavity substrate (22) are connected by screws at the positions of the first threaded hole (221) and the third through hole (2351).

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