On-orbit multifunctional integration and convenient operation oil supplement mechanism of spacecraft

Abstract

The application discloses a spacecraft on-orbit multifunctional integration and convenient operation oil supplement mechanism, which comprises a wiping oil module, an oil delivery pipeline module, an operating hand wheel module, a transmission module, an oil storage module, a clamping module and a base; the operating hand wheel module, the transmission module, the oil storage module and the clamping module are respectively installed on the base; the oil storage module is connected with the wiping oil module through the oil delivery pipeline module; the wiping oil module is installed on the base through the clamping module; and the operating hand wheel module is connected with the clamping module through the transmission module. The application realizes multifunctional integration of double ball valve start / stop and wiping oil module clamping / detaching, and under the intervention of astronauts, lubricating oil can be conveniently delivered to the contact surface of a movable part at a proper time to compensate for long-term on-orbit evaporation loss, thereby laying a foundation for realizing regular maintenance, fault repair and service life extension of the spacecraft.

Description

Technical Field

[0001] This invention belongs to the field of on-orbit lubrication technology for spacecraft, and particularly relates to a multi-functional integrated and convenient-to-operate on-orbit lubrication mechanism for spacecraft. Background Technology

[0002] The spacecraft on-orbit multi-functional integrated and convenient operation lubrication mechanism is an important component for replenishing the lubricating oil of the spacecraft's moving parts under astronaut intervention conditions, and it is also a key mechanism for realizing the on-orbit storage of lubricating oil for spacecraft.

[0003] As spacecraft operate in orbit, the lubricating oil at the interfaces of their moving parts continuously evaporates, leading to a deterioration in the lubrication condition of these parts. This, in turn, affects their on-orbit lifespan and ultimately causes lubrication failure. Therefore, to achieve regular on-orbit maintenance or emergency maintenance under fault conditions (abnormally increased frictional torque at the moving part's location) of long-life spacecraft moving parts, it is necessary to replenish lubricating oil at the contact interfaces of the moving parts. This compensates for the evaporation of lubricating oil, thereby improving the lubrication condition of the moving parts and extending the on-orbit lifespan of long-life spacecraft.

[0004] Long-life (≥12 years) and highly reliable spacecraft such as space stations need to ensure stable and reliable operation in orbit for extended periods. Inevitably, the lubrication of their moving parts deteriorates due to lubricant evaporation. While astronauts can replace moving components in orbit to address malfunctions, this process is cumbersome, complex, and demands high levels of extravehicular activity (EVA) repair skills from astronauts, at a significant cost. To address this, a novel approach is being adopted to compensate for lubricant evaporation at the interfaces of moving components by replenishing lubricant in orbit. Since this involves EVA, the mechanism must meet ergonomic design requirements and optimize the operational process for astronauts performing EVA maintenance, ensuring convenient operation in orbit.

[0005] Those skilled in the art urgently need to design a multi-functional integrated and convenient-to-operate lubrication mechanism for spacecraft in orbit. On the one hand, it should realize multi-functional integration such as clamping / disengaging the interface of moving parts of the spacecraft and starting / stopping lubrication replenishment; on the other hand, it should enable astronauts to conveniently operate and perform on-orbit lubrication tasks. Summary of the Invention

[0006] The technical problem solved by this invention is to overcome the shortcomings of the prior art and provide a multi-functional integrated and convenient-to-operate oil replenishment mechanism for spacecraft in orbit. It realizes the multi-functional integration of starting / stopping the dual-way ball valve and clamping / unclamping the oiling module. With the intervention of astronauts, it can conveniently deliver lubricating oil to the contact surface of moving parts at opportune times to compensate for its long-term in-orbit evaporation loss, thereby laying the foundation for realizing regular maintenance, fault repair and life extension of spacecraft.

[0007] To address the aforementioned technical problems, this invention discloses a multi-functional integrated and convenient-to-operate refueling mechanism for spacecraft in orbit, comprising: an oil application module, an oil delivery pipeline module, an operating handwheel module, a transmission module, an oil storage module, a clamping module, and a base;

[0008] The operating handwheel module, transmission module, oil storage module, and clamping module are respectively mounted on the base;

[0009] The oil storage module is connected to the oil application module via the oil delivery pipeline module;

[0010] The oiling module is mounted on the base via a clamping module;

[0011] The handwheel module is connected to the clamping module via the transmission module.

[0012] Among the aforementioned spacecraft's multi-functional integrated and easy-to-operate refueling mechanisms,

[0013] The oil storage module is used to store lubricating oil and provide oil supply pressure to supply oil to the oiling module;

[0014] The oil delivery pipeline module is used to deliver the lubricating oil stored in the oil storage module to the oiling module;

[0015] The oiling module is used to evenly apply lubricating oil to the contact interface of the spacecraft's moving parts under the action of the clamping module, to compensate for the loss of lubricating oil evaporation during long-term on-orbit operation, thereby improving the lubrication condition and enabling on-orbit maintenance and life extension of the moving parts.

[0016] The transmission module is used to drive the clamping module to control the oiling module when the handwheel module is operated;

[0017] The handwheel module is used to respond to astronauts' on-orbit operations and provides power input;

[0018] The clamping module is used to control the opening / closing of the oil storage module and the clamping / unclamping of the oil application module under the drive of the transmission module.

[0019] In the aforementioned spacecraft's on-orbit multi-functional integrated and convenient operation refueling mechanism, the oil storage module includes: a conical seal A, a metal rigid pipe, a ball valve support, an oil storage tank, a metal bend A, and a two-way ball valve;

[0020] The oil storage tank is fixed to the lower surface of the base with M5 screws;

[0021] One end of the metal bend A is connected to the oil storage tank, and the other end is connected to one end of the metal rigid pipe through a two-way ball valve;

[0022] The other end of the metal rigid tube is equipped with a conical seal A;

[0023] The ball valve support is fixed to the upper surface of the base with M5 screws;

[0024] The two-way ball valve is mounted on the ball valve support.

[0025] In the aforementioned spacecraft's on-orbit multi-functional integrated and convenient operation refueling mechanism, the conical seal A, the metal rigid pipe, the double-way ball valve, and the metal bend A constitute a set of oil storage and output units; there are three sets of oil storage and output units, one end of which is connected to the oil storage tank, and the other end of which is connected to three oiling modules respectively through the oil delivery pipeline module.

[0026] In the aforementioned spacecraft's on-orbit multi-functional integrated and convenient operation oil replenishment mechanism, the oiling module includes: a conical seal B, a metal bend B, an oil tanker, a rotating support, a conical seal C, a cover plate, and screws.

[0027] A conical seal B is provided at one end of the metal bend B;

[0028] The other end of the metal bend B is connected to the cover plate via a rotating support, and the metal bend B and the rotating support are sealed by a conical seal C.

[0029] The oil tanker is mounted on the cover plate with screws.

[0030] In the aforementioned spacecraft's on-orbit multi-functional integrated and convenient operation refueling mechanism, the oil pipeline module includes three metal hoses; one end of the metal hose is connected to the other end of the metal rigid pipe and sealed by a conical seal A; the other end of the metal hose is connected to one end of the metal bend B and sealed by a conical seal B.

[0031] In the aforementioned spacecraft on-orbit multi-functional integrated and convenient operation refueling mechanism, the operating handwheel module includes: bevel gear A, bevel gear B, bevel gear C, mounting base, operating handwheel, marking disc, handwheel mounting rod, and input shaft A and input shaft B;

[0032] One end of the handwheel mounting rod is connected to the operating handwheel, and the other end is connected to one end of the input shaft A; the astronauts input power by rotating the operating handwheel.

[0033] The marking disc is mounted on the handwheel mounting rod to facilitate astronauts in identifying the rotation position when turning the handwheel.

[0034] Input shaft A is fixed to the mounting base in the horizontal direction, and input shaft B is fixed to the mounting base in the vertical direction; the mounting base is fixed to the base.

[0035] A bevel gear A is installed at the other end of input shaft A, and bevel gears B and C are installed at both ends of input shaft B, respectively. Bevel gear A meshes with bevel gear B.

[0036] In the aforementioned on-orbit multifunctional integrated and convenient operation refueling mechanism for spacecraft, the transmission module includes: worm A, worm B, turbine mounting shaft, and ball valve shaft system. The transmission module inputs and reverses the power from the operating handwheel module via a bevel gear pair at the right end of worm B. The input power is divided into two branches after passing through worm B. The first branch is reversed via the worm wheel on the turbine mounting shaft and input to the three ball valve shaft systems. These three ball valve shaft systems are respectively connected to the switching interfaces of the three double-way ball valves of the oil storage module. This first branch is used to control the start / stop of the three double-way ball valves. The second branch is reversed via the bevel gear pair of worm A and input to the clamping module to control the movement of the clamping module.

[0037] In the aforementioned spacecraft on-orbit multi-functional integrated and convenient operation oil replenishment mechanism, the clamping module includes: ball linear guide pair A, worm gear C, sliding pin, worm wheel-cam, ball linear guide pair B, clamping arm, and vertical ball linear guide pair;

[0038] The clamping module transmits the power of the transmission module from the worm C to the worm wheel-cam. Three sliding pins are installed in the three sliding grooves of the worm wheel-cam, and the three sliding pins are fixedly connected to the three clamping arms respectively. The three clamping arms are respectively installed on the ball linear guide pair A, the ball linear guide pair B and the vertical ball linear guide pair.

[0039] When the worm gear-cam rotates clockwise, the three clamping arms achieve the clamping function through linear motion; when the worm gear-cam rotates counterclockwise, the three clamping arms achieve the disengagement function through linear motion. The linear motion includes horizontal linear motion and vertical linear motion. The clamping arms make horizontal linear motion through ball linear guide pair A and ball linear guide pair B, and the clamping arms make vertical linear motion through the vertical ball linear guide pair.

[0040] The clamping of the three clamping arms and the opening of the three double-way ball valves are synchronized, and the disengagement of the three clamping arms and the closing of the three double-way ball valves are synchronized, thereby realizing the multi-functional integration of clamping / disengagement and ball valve start / stop of the oiling module.

[0041] In the aforementioned spacecraft on-orbit multifunctional integrated and convenient operation oil replenishment mechanism, when the double-way ball valve is closed, the oiling module disengages from the contact interface of the moving parts, and the lubricating oil in the oil storage module is reliably sealed in the oil storage tank for a long period of time, realizing the long-term reliable on-orbit storage of lubricating oil; when the double-way ball valve is opened, the oiling module clamps the contact interface of the moving parts, and the lubricating oil in the oil storage module is transported to the oiling module along the oil delivery pipeline module under the action of the oil supply pressure. Under the action of the clamping module, the oiling module evenly applies the lubricating oil to the contact interface of the spacecraft's moving parts, compensating for the lubricating oil evaporation loss of the contact interface during long-term on-orbit operation, thereby improving its lubrication condition and realizing on-orbit maintenance and life extension of the moving parts.

[0042] The present invention has the following advantages:

[0043] This invention discloses a multifunctional integrated and convenient-to-operate on-orbit lubrication replenishment mechanism for spacecraft. It enables convenient and reliable long-term on-orbit storage of lubricating oil and effective replenishment to moving interfaces, ensuring that the lubricating oil required by moving parts in orbit is compensated. When the lubrication condition of a spacecraft's moving parts deteriorates or requires periodic maintenance, astronauts can easily replenish lubricating oil by manually rotating the operating handwheel counterclockwise one turn to open the double-way ball valve. The lubrication module clamps the moving part interface. At the end of the on-orbit maintenance mission, astronauts can close the double-way ball valve by manually rotating the operating handwheel clockwise one turn, disengaging the lubrication module and reliably sealing the lubricating oil in the storage module, allowing for long-term on-orbit storage. Therefore, this mechanism achieves multifunctional integration of double-way ball valve opening / stop and lubrication module clamping / disengagement. With astronaut intervention, lubricating oil can be conveniently delivered to the contact surfaces of moving parts as needed, compensating for long-term on-orbit evaporation losses. This lays the foundation for periodic maintenance, fault repair, and life extension of spacecraft. Attached Figure Description

[0044] Figure 1 This is a schematic diagram of the structure of a spacecraft on-orbit multi-functional integrated and convenient operation refueling mechanism according to an embodiment of the present invention;

[0045] Figure 2 This is a schematic diagram of the structure of an oil storage module according to an embodiment of the present invention;

[0046] Figure 3 This is a schematic diagram of the structure of an oil pipeline module according to an embodiment of the present invention;

[0047] Figure 4 This is a schematic diagram of the structure of an oiling module in an embodiment of the present invention;

[0048] Figure 5 This is a schematic diagram of the structure of an operating handwheel module in an embodiment of the present invention;

[0049] Figure 6 This is a schematic diagram of the structure of a transmission module in an embodiment of the present invention;

[0050] Figure 7 This is a schematic diagram of the structure of a clamping module in an embodiment of the present invention. Detailed Implementation

[0051] To make the objectives, technical solutions, and advantages of the present invention clearer, the embodiments disclosed in the present invention will be described in further detail below with reference to the accompanying drawings.

[0052] like Figure 1In this embodiment, the spacecraft's on-orbit multifunctional integrated and convenient-to-operate refueling mechanism includes: an oil application module 1, an oil supply pipeline module 2, an operating handwheel module 3, a transmission module 4, an oil storage module 5, a clamping module 6, and a base 7. The operating handwheel module 3, transmission module 4, oil storage module 5, and clamping module 6 are respectively mounted on the base 7; the oil storage module 5 is connected to the oil application module 1 via the oil supply pipeline module 2; the oil application module 1 is mounted on the base 7 via the clamping module 6; and the operating handwheel module 3 is connected to the clamping module 6 via the transmission module 4.

[0053] In this embodiment, the oil storage module 5 stores lubricating oil and provides oil supply pressure to supply oil to the oiling module 1. The oil pipeline module 2 delivers the lubricating oil stored in the oil storage module 5 to the oiling module 1. The oiling module 1, under the action of the clamping module 6, evenly applies lubricating oil to the contact interface of the spacecraft's moving parts, compensating for the lubricating oil evaporation loss during long-term on-orbit operation, thereby improving its lubrication condition and enabling on-orbit maintenance and life extension of the moving parts. The transmission module 4, under the operation of the operating handwheel module 3, drives the clamping module 6 to control the oiling module 1. The operating handwheel module 3 provides power input in response to on-orbit operations by astronauts. The clamping module 6, driven by the transmission module 4, controls the opening / closing of the oil storage module 5 and the clamping / unclamping of the oiling module.

[0054] In this embodiment, as Figure 2 As shown, the oil storage module 5 may specifically include: a conical seal A101, a metal rigid pipe 102, a ball valve support 103, an oil storage tank 105, a metal elbow A106, and a two-way ball valve 107. The oil storage tank 105 is fixed to the lower surface of the base 7 with M5 screws. One end of the metal elbow A106 is connected to the oil storage tank 105, and the other end is connected to one end of the metal rigid pipe 102 via the two-way ball valve 107. The other end of the metal rigid pipe 102 is equipped with a conical seal A101. The ball valve support 103 is fixed to the upper surface of the base 7 with M5 screws. The two-way ball valve 107 is mounted on the ball valve support 103 and can be rotated ±90° to store / transport lubricating oil in the oil storage tank 105.

[0055] Preferably, the oil storage tank 105 has its own oil supply pressure and mainly consists of a metal diaphragm box, a spring, a spring guide rod, and a guide cylinder. The spring is mounted on the spring guide rod and is confined within the metal diaphragm box by the guide cylinder. The working principle is as follows: the metal diaphragm box stores lubricating oil, and the spring at the bottom of the metal diaphragm box provides the oil supply pressure. When the two-way ball valve 107 opens, the spring force transports the lubricating oil from the metal diaphragm box to the oil supply pipeline module, and finally to the oiling module.

[0056] Preferably, the conical seal A101, the metal rigid pipe 102, the double-way ball valve 107, and the metal elbow A106 constitute a set of oil storage and output units. There are three sets of oil storage and output units. One end of each set of oil storage and output units is connected to the oil storage tank 105, and the other end of each set of oil storage and output units is connected to three oiling modules 1 respectively through the oil pipeline module 3.

[0057] In this embodiment, as Figure 4 As shown, the oiling module 1 may specifically include: a conical seal B301, a metal bend B302, an oil wheel 303, a rotating support 304, a conical seal C305, a cover plate 306, and screws 307. One end of the metal bend B302 is equipped with the conical seal B301. The other end of the metal bend B302 is connected to the cover plate 306 via the rotating support 304, and a seal is achieved between the metal bend B302 and the rotating support 304 via the conical seal C305. The oil wheel 303 is mounted on the cover plate 306 using screws 307.

[0058] In this embodiment, as Figure 3 As shown, the oil pipeline module 2 includes three metal hoses 201. One end of the metal hose 201 is connected to the other end of the metal rigid pipe 102 and sealed by a conical seal A101; the other end of the metal hose 201 is connected to one end of the metal bend B302 and sealed by a conical seal B301.

[0059] In this embodiment, as Figure 5 As shown, the operating handwheel module 3 specifically includes: bevel gear A4011, bevel gear B4012, bevel gear C4013, mounting base 402, operating handwheel 403, marking disc 404, handwheel mounting rod 405, and input shafts A4061 and B4062. One end of the handwheel mounting rod 405 is connected to the operating handwheel 403, and the other end is connected to one end of the input shaft A4061; the astronaut inputs power by rotating the operating handwheel 403. The marking disc 404 is mounted on the handwheel mounting rod 405 to facilitate the astronaut's identification of the rotation position when rotating the operating handwheel 403. Input shaft A4061 is fixed horizontally to the mounting base 402, and input shaft B4062 is fixed vertically to the mounting base 402; the mounting base 402 is fixed to the base 7. The other end of the input shaft A4061 is equipped with a bevel gear A4011, and the two ends of the input shaft B4062 are equipped with bevel gears B4012 and C4013 respectively. Bevel gear A4011 meshes with bevel gear B4012.

[0060] In this embodiment, as Figure 6As shown, the transmission module 4 specifically includes: worm A501, worm B502, turbine mounting shaft 503, and ball valve shaft system 504. The transmission module 4 inputs and reverses the power from the operating handwheel module 3 via the bevel gear pair at the right end of worm B502. The input power is divided into two branches after passing through worm B502. The first branch is reversed by the worm wheel of the turbine mounting shaft 503 and input to the three ball valve shaft systems 504. The three ball valve shaft systems 504 are respectively connected to the switching interfaces of the three double-way ball valves 107 of the oil storage module 5. This first branch is used to control the start / stop of the three double-way ball valves 107. The second branch is reversed by the bevel gear pair of worm A501 and input to the clamping module 6 to control the movement of the clamping module 6.

[0061] In this embodiment, as Figure 7 As shown, the clamping module 6 may specifically include: a ball linear guide pair A601, a worm gear C602, a sliding pin 603, a worm wheel-cam 604, a ball linear guide pair B605, a clamping arm 606, and a vertical ball linear guide pair. The clamping module 6 transmits the power of the transmission module 4 from the worm gear C602 to the worm wheel-cam 604. Three sliding pins 603 are installed in the three grooves of the worm wheel-cam 604, and the three sliding pins 603 are fixedly connected to the three clamping arms 606 respectively. The three clamping arms 606 are respectively installed on the ball linear guide pair A601, the ball linear guide pair B605, and the vertical ball linear guide pair. When the worm gear-cam 604 rotates clockwise, the three clamping arms 606 achieve clamping function through linear motion; when the worm gear-cam 604 rotates counterclockwise, the three clamping arms 606 achieve disengagement function through linear motion. The linear motion includes horizontal and vertical linear motion. The clamping arms 606 move horizontally via ball linear guide pairs A601 and B605, and vertically via the ball linear guide pairs. The clamping of the three clamping arms 606 is synchronized with the opening of the three double-way ball valves 107, and the disengagement of the three clamping arms 606 is synchronized with the closing of the three double-way ball valves 107, thereby achieving the multi-functional integration of clamping / disengagement and ball valve start / stop of the oiling module 1.

[0062] In this embodiment, the oiling module uses a follow-up oiling method, meaning the oil wheel inside the oiling module rotates with the guide rail of the sun-aligning device, carrying internal lubricating oil to coat the guide rail surface during rotation. The lubricating oil stored in the oil storage module is supplied to the oil chamber of the oiling module under pressure through the oil pipeline module. The oil wheel has strong lubricating oil adhesion, adsorbing the lubricating oil in the oil chamber onto its outer surface. As the oil wheel rotates with the guide rail, it coats the lubricating oil in the oil chamber onto the guide rail surface. The function of the double-way ball valve is to control the oil supply from the oil storage module to the oiling module; the rotation angle of the double-way ball valve is 90°, and the inner diameter of the double-way ball valve is 4.75mm; the rotation switch of the double-way ball valve is connected to a bevel gear, which opens / closes the double-way ball valve by rotating the bevel gear.

[0063] In this embodiment, the clamping module functions to enable the oiling module to contact and disengage from the guide rail surface. Its working principle is as follows: the turbine is equipped with corresponding guide grooves, and the three clamping arms of the clamping device are equipped with sliding pins. When the turbine rotates, the sliding pins move under the action of the guide grooves, thereby driving the three clamping arms of the oiling device to move together, causing the oiling device located at the end of the clamping arms to contact or disengage from the guide rail surface. The two side clamping arms move horizontally, contacting and disengaging from the guide rail, guided by linear bearings and the turbine; the bottom clamping arm moves vertically, contacting and disengaging from the guide rail, guided by a straight guide rail and the turbine.

[0064] In this embodiment, the function of the transmission module is to enable simultaneous on-orbit oil replenishment maintenance on three guide rail surfaces when the astronaut intervenes to operate the handwheel. This requires the simultaneous operation of three clamping components and three oil valve switches. Therefore, the mechanism needs to be configured with six transmission chains to ensure that the six actions are completed simultaneously, achieving multi-functional integration of clamping release and oil valve opening and closing. The astronaut's power input is split into two: one drive drives the opening and closing of the oil valves in the three oil supply lines, and the other drive the clamping arm of the clamping device to engage and disengage from the guide rail surface. The working principle is as follows: when the astronaut rotates the operating handle, the transmission mechanism transmits the power to the clamping device and oil valves, simultaneously driving the clamping mechanism to clamp the guide rail surface and open the oil valve. Conversely, when the astronaut rotates the operating handle in the opposite direction, the transmission mechanism transmits the power to the clamping mechanism and oil valves, simultaneously driving the clamping mechanism to release the guide rail surface and close the oil valve.

[0065] In this embodiment, the operating handwheel module provides a human-machine interface and markings between the refueling mechanism and the astronaut. The astronaut can hold the operating handle with their bare hands and rotate it at a certain angle. The internal transmission device of the mechanism converts this action into the movement of the mechanism's clamping device and the oil delivery pipeline. The handwheel is designed to meet ergonomic requirements and is equipped with relevant markings to ensure that the astronaut can easily operate the refueling mechanism without maintenance tools.

[0066] In this embodiment, when the double-way ball valve 107 is closed, the oiling module 1 disengages from the contact interface of the moving part, and the lubricating oil in the oil storage module 5 is reliably sealed in the oil storage tank 105 for a long period of time, realizing the long-term reliable on-orbit storage of the lubricating oil; when the double-way ball valve 107 is opened, the oiling module 1 clamps the contact interface of the moving part, and the lubricating oil in the oil storage module 5 is transported to the oiling module 1 along the oil delivery pipeline module 2 under the action of the oil supply pressure. Under the action of the clamping module 6, the oiling module 1 evenly applies the lubricating oil to the contact interface of the spacecraft's moving part, compensating for the long-term on-orbit lubricating oil evaporation loss of the contact interface, so as to improve its lubrication status and realize on-orbit maintenance and life extension of the moving part.

[0067] In this embodiment, the astronaut rotates the operating handwheel counterclockwise 4031 times, opening the double-way ball valve 107. The lubricating oil in the oil storage module 5 is transported to the oiling module 1 along the metal bend A106, metal rigid pipe 102, metal flexible hose 201, and metal bend B302. The oiling module 1 clamps the contact interface of the moving parts under the action of the clamping arm 606, facilitating the replenishment of lubricating oil. The astronaut rotates the operating handwheel clockwise 4031 times, closing the double-way ball valve 107, enabling long-term on-orbit storage of the lubricating oil in the oil storage module 5. The oiling module 1 then disengages from the contact interface of the moving parts under the action of the clamping arm 606. This multi-functional integrated mechanism for starting / stopping ball valves and clamping / unclamping oil application modules not only facilitates the timely replenishment of lubricating oil required for the periodic maintenance of spacecraft moving parts, but also allows for convenient operation by only one astronaut without the need for maintenance tools. It evenly applies the lubricating oil to the contact interface of the spacecraft moving parts, compensating for the long-term evaporation loss of lubricating oil on the contact interface during orbit, thereby improving its lubrication condition and achieving on-orbit maintenance and life extension of the moving parts.

[0068] Based on the above embodiments, the following further describes the convenient operation process of the oil replenishment mechanism for astronauts without maintenance tools: Astronauts, wearing spacesuits, are positioned at the operation point; facing the operating handwheel and rotating it counterclockwise 354°, the three oiling modules clamp the contact surfaces of the moving parts, and the three oil supply pipeline modules begin supplying lubricating oil to the oiling modules, initiating oil replenishment; facing the operating handwheel and rotating it clockwise 354°, the three oiling modules disengage from the contact surfaces of the moving parts, and the three oil supply pipeline modules stop supplying lubricating oil to the oiling modules, ending oil replenishment; through reasonable and ingenious design and layout of the transmission links and structural optimization, a single power source drives six transmission links, enabling simultaneous oil replenishment and maintenance of three guide rail surfaces. The only human-machine interface is the operating handwheel, which is designed to meet ergonomic requirements and is equipped with relevant markings, ensuring that astronauts can conveniently operate the oil replenishment mechanism without maintenance tools and without needing to carry any.

[0069] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

[0070] The contents not described in detail in this specification are common knowledge to those skilled in the art.

Claims

1. A multi-functional integrated and convenient-to-operate refueling mechanism for spacecraft in orbit, characterized in that, include: Oiling module (1), oil pipeline module (2), operating handwheel module (3), transmission module (4), oil storage module (5), clamping module (6) and base (7); The handwheel module (3), transmission module (4), oil storage module (5) and clamping module (6) are respectively installed on the base (7); The oil storage module (5) is connected to the oil application module (1) through the oil pipeline module (2); The oiling module (1) is mounted on the base (7) via the clamping module (6); The handwheel module (3) is connected to the clamping module (6) via the transmission module (4); The oil storage module (5) includes: a conical seal A (101), a metal rigid pipe (102), a ball valve support (103), an oil storage tank (105), a metal elbow A (106), and a two-way ball valve (107); wherein, the oil storage tank (105) is fixed to the lower surface of the base (7) with M5 screws; one end of the metal elbow A (106) is connected to the oil storage tank (105), and the other end is connected to one end of the metal rigid pipe (102) through the two-way ball valve (107); the other end of the metal rigid pipe (102) is provided with a conical seal A (101); the ball valve support (103) is fixed to the upper surface of the base (7) with M5 screws; the two-way ball valve (107) is installed on the ball valve support (103); When the double-way ball valve (107) is closed, the oiling module (1) is disengaged from the contact interface of the moving part, and the lubricating oil in the oil storage module (5) is reliably sealed in the oil storage tank (105) for a long time, realizing the long-term reliable on-orbit storage of the lubricating oil; when the double-way ball valve (107) is opened, the oiling module (1) clamps the contact interface of the moving part, and the lubricating oil in the oil storage module (5) is transported to the oiling module (1) along the oil pipeline module (2) under the action of the oil supply pressure. The oiling module (1) evenly applies the lubricating oil to the contact interface of the spacecraft's moving part under the action of the clamping module (6), compensating for the loss of lubricating oil evaporation during the long-term on-orbit operation of the contact interface, so as to improve its lubrication status and realize the on-orbit maintenance and life extension of the moving part.

2. The spacecraft on-orbit multi-functional integrated and convenient-to-operate refueling mechanism according to claim 1, characterized in that, The oil storage module (5) is used to store lubricating oil and provide oil supply pressure to supply oil to the oiling module (1); The oil pipeline module (2) is used to transport the lubricating oil stored in the oil storage module (5) to the oiling module (1). The oiling module (1) is used to apply lubricating oil evenly to the contact interface of the spacecraft's moving parts under the action of the clamping module (6), to compensate for the loss of lubricating oil evaporation during long-term on-orbit operation, so as to improve its lubrication status and realize on-orbit maintenance and life extension of the moving parts. The transmission module (4) is used to drive the clamping module (6) to control the oiling module (1) under the operation of the handwheel module (3); The handwheel module (3) is used to respond to astronauts' on-orbit operations and provide power input; The clamping module (6) is used to control the opening / closing of the oil storage module (5) and the clamping / unclamping of the oil application module under the drive of the transmission module (4).

3. The spacecraft on-orbit multi-functional integrated and convenient-to-operate refueling mechanism according to claim 1, characterized in that, A set of oil storage and output units is composed of a conical seal A (101), a metal hard pipe (102), a double-way ball valve (107) and a metal elbow A (106); there are three sets of oil storage and output units. One end of the three sets of oil storage and output units is connected to the oil storage tank (105), and the other end of the three sets of oil storage and output units is connected to three oiling modules (1) respectively through the oil pipeline module (2).

4. The spacecraft on-orbit multi-functional integrated and convenient-to-operate refueling mechanism according to claim 3, characterized in that, The oiling module (1) includes: a conical seal B (301), a metal bend B (302), an oiler (303), a rotating support (304), a conical seal C (305), a cover plate (306), and screws (307); A conical seal B (301) is provided at one end of the metal bend B (302); The other end of the metal bend B (302) is connected to the cover plate (306) through the rotating support (304), and the metal bend B (302) and the rotating support (304) are sealed by the conical seal C (305); The tanker (303) is mounted on the cover plate (306) by screws (307).

5. The spacecraft on-orbit multi-functional integrated and convenient-to-operate refueling mechanism according to claim 4, characterized in that, The oil pipeline module (2) includes three metal hoses (201); one end of the metal hose (201) is connected to the other end of the metal rigid pipe (102) and sealed by a conical seal A (101); the other end of the metal hose (201) is connected to one end of the metal bend B (302) and sealed by a conical seal B (301).

6. The spacecraft on-orbit multi-functional integrated and convenient-to-operate refueling mechanism according to claim 5, characterized in that, The operating handwheel module (3) includes: bevel gear A (4011), bevel gear B (4012), bevel gear C (4013), mounting base (402), operating handwheel (403), marking disc (404), handwheel mounting rod (405), and input shaft A (4061) and input shaft B (4062). One end of the handwheel mounting rod (405) is connected to the operating handwheel (403), and the other end is connected to one end of the input shaft A (4061); the astronauts input power by rotating the operating handwheel (403); The marking disc (404) is mounted on the handwheel mounting rod (405) to facilitate the astronauts in identifying the rotation position when turning the operating handwheel (403); Input shaft A (4061) is fixed horizontally on mounting base (402), and input shaft B (4062) is fixed vertically on mounting base (402); mounting base (402) is fixed on base (7); The other end of input shaft A (4061) is equipped with bevel gear A (4011), and the two ends of input shaft B (4062) are equipped with bevel gear B (4012) and bevel gear C (4013) respectively. Bevel gear A (4011) meshes with bevel gear B (4012).

7. The spacecraft on-orbit multi-functional integrated and convenient-to-operate refueling mechanism according to claim 6, characterized in that, The transmission module (4) includes: worm A (501), worm B (502), turbine mounting shaft (503), and ball valve shaft system (504); wherein, the transmission module (4) inputs and reverses the power of the operating handwheel module (3) through the bevel gear pair at the right end of the worm B (502). The input power is divided into two branches after passing through the worm B (502). The first branch power is reversed through the worm wheel of the turbine mounting shaft (503) and input to the three ball valve shaft systems (504). The three ball valve shaft systems (504) are respectively connected to the switch interfaces of the three double-way ball valves (107) of the oil storage module (5). The first branch power is used to control the start / stop of the three double-way ball valves (107); the second branch power is reversed through the bevel gear pair of the worm A (501) and input to the clamping module (6) to control the movement of the clamping module (6).

8. The spacecraft on-orbit multi-functional integrated and convenient-to-operate refueling mechanism according to claim 7, characterized in that, The clamping module (6) includes: a ball linear guide pair A (601), a worm gear C (602), a sliding pin (603), a worm wheel-cam (604), a ball linear guide pair B (605), a clamping arm (606), and a vertical ball linear guide pair; The clamping module (6) transmits the power of the transmission module (4) to the worm wheel-cam (604) via the worm C (602). Three sliding pins (603) are installed in the three sliding grooves of the worm wheel-cam (604). The three sliding pins (603) are fixedly connected to the three clamping arms (606) respectively. The three clamping arms (606) are respectively installed on the ball linear guide pair A (601), the ball linear guide pair B (605) and the vertical ball linear guide pair. When the worm gear-cam (604) rotates clockwise, the three clamping arms (606) achieve the clamping function through linear motion; when the worm gear-cam (604) rotates counterclockwise, the three clamping arms (606) achieve the disengagement function through linear motion; wherein, the linear motion includes horizontal linear motion and vertical linear motion, the clamping arms (606) make horizontal linear motion through ball linear guide pair A (601) and ball linear guide pair B (605), and the clamping arms (606) make vertical linear motion through the vertical ball linear guide pair; The clamping of the three clamping arms (606) and the opening of the three double-way ball valves (107) are synchronized, and the disengagement of the three clamping arms (606) and the closing of the three double-way ball valves (107) are synchronized, thereby realizing the multi-functional integration of clamping / disengagement and ball valve start / stop of the oiling module (1).

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