Large-scale high-load-bearing, long-life, maintainable sun-directed driving mechanism and operation method

Abstract

The present invention provides a large-scale high-load long-life maintainable sun-pointing drive mechanism and an operation method, which includes a composite material main structure, a cabin interface flange, a truss interface flange, a strap locking and releasing assembly, a slewing bearing device and a drive locking assembly; the composite material main structure is connected to the cabin interface flange; the cabin interface flange provides a connection interface for the spacecraft cabin; the truss interface flange provides a connection interface for the external load outside the cabin; the strap locking and releasing assembly tightens the composite material main structure and the truss interface flange during the launch section and releases the two during the on-orbit section; the slewing bearing device supports the truss interface flange and provides a slewing degree of freedom for the truss interface flange during the on-orbit section; the drive locking assembly drives the truss interface flange to rotate as a power source. The present invention has the advantages of strong load-bearing capacity during the launch section, large driving capacity during the on-orbit section, strong braking capacity, high transmission power, long operation life and on-orbit maintainability, and is applicable to high-power long-life spacecraft platforms.

Description

Technical Field

[0001] The present invention belongs to the technical field of spacecraft design, and particularly relates to a large-scale, high-load, long-life, and maintainable solar-orientation drive mechanism and an operation method thereof. Background Art

[0002] In the past, the power requirements of spacecraft were generally not greater than 6 kW, and the life requirements were generally 3 - 5 years in low Earth orbit. However, with the development of space technology, the requirements for power and service life of spacecraft have been increasing. The transmission power of large satellite platforms reaches more than 10 kW, and even up to 20 kW - 50 kW or more, and the life is required to reach 8 - 15 years in low Earth orbit. High power means a larger solar wing is needed, and the mass and inertia of the solar wing need to be increased significantly. This not only puts forward higher requirements for the high-power electrical transmission ability of the solar-orientation drive mechanism, but also puts forward higher requirements for the driving and load-bearing capabilities of the solar-orientation drive mechanism. Long life means that the solar-orientation drive mechanism needs to have a longer service life and a more reliable lubrication scheme for moving parts, and at the same time, it also puts forward requirements for on-orbit maintainability.

[0003] Currently, the "motor, reducer, slip ring" solar-orientation drive mechanism scheme is mostly adopted at home and abroad, and it is difficult to meet the requirements of high load, long life, and maintainability in terms of electrical transmission power, load-bearing capacity, driving ability, etc. Simply increasing the size can only improve the transmission power and load-bearing driving ability to a certain extent, but there will be problems such as large weight and low energy efficiency ratio. The International Space Station adopts a scheme of separately launching the solar wing and the solar-orientation drive mechanism and assembling them on orbit, which greatly reduces the requirements for the load-bearing capacity of the solar-orientation drive mechanism. Based on the current domestic space technology level, the scheme of launching a large solar wing and a solar-orientation drive mechanism together puts forward extremely high requirements for the load-bearing capacity of the solar-orientation drive mechanism, which has never been seen before.

[0004] In summary, with the rapid development of space science and technology, various high-power and long-life spacecraft platforms have put forward higher and greater requirements for the transmission power, load-bearing and driving capabilities, service life, on-orbit maintainability, etc. of the solar-orientation drive mechanism. The traditional form of solar-orientation drive mechanism is difficult to meet the above requirements. Therefore, a solar-orientation drive mechanism with a new mechanical structure must be adopted. Summary of the Invention

[0005] In order to overcome the deficiencies in the prior art, the inventor of the present invention has conducted intensive research and provided a large-scale, high-load, long-life, and maintainable solar-orientation drive mechanism and an operation method thereof. The solar-orientation drive mechanism has at least one of the characteristics of strong load-bearing capacity in the launch stage, large driving ability in the on-orbit stage, strong braking ability, high transmission power, long operation life, and on-orbit maintainability, and is applicable to high-power and long-life spacecraft platforms.

[0006] The technical solution provided by the present invention is as follows:

[0007] In a first aspect, a large-scale, high-load-bearing, long-life, and maintainable sun-pointing drive mechanism includes: a composite material main structure, a cabin interface flange, a truss interface flange, a strap locking and releasing assembly, a slewing bearing device, and a drive locking assembly;

[0008] The composite material main structure is connected to the cabin interface flange and is used to support the truss interface flange during the launch stage;

[0009] The cabin interface flange provides a connection interface for the spacecraft cabin;

[0010] The truss interface flange provides an external load connection interface;

[0011] The strap locking and releasing assembly clamps the composite material main structure and the truss interface flange during the launch stage and releases the composite material main structure and the truss interface flange during the on-orbit stage;

[0012] The top of the slewing bearing device is connected to the truss interface flange, and the bottom is connected to the cabin interface flange. It is used to lock and support the truss interface flange during the launch stage and the on-orbit stage, and provides a slewing freedom degree for the truss interface flange during the on-orbit stage;

[0013] The drive locking assembly is installed on the cabin interface flange or the truss interface flange and is used as a power source to cooperate with the slewing bearing device to drive the truss interface flange to rotate.

[0014] In a second aspect, an operation method for a large-scale, high-load-bearing, long-life, and maintainable sun-pointing drive mechanism includes the following steps:

[0015] During the launch stage, the composite material main structure is connected to the cabin interface flange, the strap locking and releasing assembly clamps the composite material main structure and the truss interface flange, the top of the slewing bearing device is locked and connected to the truss interface flange, the bottom is locked and connected to the cabin interface flange, both the external load-bearing link and the internal load-bearing link are in the connected state, and the slewing bearing device is in the locked support braking mode;

[0016] After entering the orbit, the strap locking and releasing assembly releases the composite material main structure and the truss interface flange, and the load-bearing mode is switched from being borne by both the external load-bearing link and the internal load-bearing link to being borne only by the internal load-bearing link;

[0017] The top of the slewing bearing device maintains the locked connection with the truss interface flange, and the bottom is rotatably connected to the cabin interface flange, or the top of the slewing bearing device is rotatably connected to the truss interface flange, and the bottom maintains the locked connection with the cabin interface flange, so that the working mode of the slewing bearing device is correspondingly switched from the locked support braking mode to the main slewing support mode or the standby slewing support mode;

[0018] Drive the motor of the locking component to rotate. Through the transmission chain, finally drive the truss interface flange to rotate together with the external load, realizing the on-orbit operation of the sun-pointing drive mechanism.

[0019] A large-scale, high-load-bearing, long-life, and maintainable sun-pointing drive mechanism and operation method provided by the present invention have the following beneficial effects:

[0020] (1) For the large-scale, high-load-bearing, long-life, and maintainable sun-pointing drive mechanism and operation method provided by the present invention, a double-launch-section load-bearing link design is adopted, which includes an external load-bearing link based on a composite material main structure and a band-lock release component, and an internal load-bearing link based on a slewing bearing device. The axial tensile and compressive stiffness of the external load-bearing link is 1.9 - 2.3×10 5 N / mm, and the axial tensile and compressive stiffness of the internal load-bearing link is 4.5 - 7.3×10 4 N / mm. It realizes that the load in the launch section of the sun-pointing drive mechanism is mainly borne by the external load-bearing link with the load-bearing form of "structural load-bearing", and the internal load-bearing link with the load-bearing form of "mechanism load-bearing" serves as an auxiliary load-bearing, having the advantages of greatly improving the load-bearing capacity of the sun-pointing drive mechanism in the launch section and avoiding excessive loads on the mechanisms in the launch section;

[0021] (2) For the large-scale, high-load-bearing, long-life, and maintainable sun-pointing drive mechanism and operation method provided by the present invention, a band-lock release component is adopted, with a volute spring as the energy storage element. The pre-tightening force moment of the volute spring can be adjusted according to requirements. Through a rope component and a roller component, etc., the strip is pulled off in an obliquely upward direction. In addition to an upward pulling force on the strip, there is also a lateral pulling force, which is more conducive to pulling off the strip. The pulling-off force can be adjusted according to needs by adjusting the initial rotation angle of the volute spring;

[0022] A buffer component is arranged below the limit bracket. The buffer component uses a stainless steel cover and a silicone rubber block. Utilizing the characteristics of good toughness and easy deformation of stainless steel and good flexibility and energy dissipation of silicone rubber, it can effectively reduce the impact generated by the band collection;

[0023] When the strip is collected below the limit bracket, there is still a part of the residual moment of the volute spring, and this part of the moment can be adjusted during the assembly process, which can firmly limit the strip below the limit bracket;

[0024] (3) A large-scale, high-load-bearing, long-life, and maintainable solar orientation drive mechanism and operation method provided by the present invention adopt a braking scheme that combines a locking support braking mode of a slewing bearing device and a drive link braking mode of a drive locking component. Among them, the braking capacity of the locking support braking mode of the slewing bearing device is better than 510 Nm, and the braking capacity of the drive link braking mode of the drive locking component is better than 290 Nm. It has the characteristic of high braking capacity and can withstand external loads generated by multiple working conditions such as on-orbit attitude adjustment and orbit transfer of spacecraft. In addition, on the basis of meeting the on-orbit load-bearing requirements, it can also meet the application requirements of different usage scenarios;

[0025] (4) A large-scale, high-load-bearing, long-life, and maintainable solar orientation drive mechanism and operation method provided by the present invention use a rolling ring electrical transmission device composed of a rolling ring module and a slip ring module to transmit power and signals. It has the characteristics of large transmission power and many signals, and can meet the requirements of high-power transmission of spacecraft and signal transmission of multiple devices outside the cabin;

[0026] (5) A large-scale, high-load-bearing, long-life, and maintainable solar orientation drive mechanism and operation method provided by the present invention, the drive locking component adopts a drive scheme of motor drive and multi-stage deceleration of "reducer + end gear pair". Among them, the driving ability of the torque motor is > 1 Nm, the transmission reduction ratio can reach more than 500, and the total output torque is better than 350 Nm after considering the transmission efficiency. It has the characteristic of high driving ability;

[0027] (6) A large-scale, high-load-bearing, long-life, and maintainable solar orientation drive mechanism and operation method provided by the present invention adopt a scheme of three drive links. Any one of the drive links can meet the service life requirement of the spacecraft in orbit for 12 years. The first drive link and the second drive link share the inner cabin side guide rail of the slewing bearing guide rail and independently use the drive locking component, while the third drive link is completely isolated from the first drive link and the second drive link. This configuration scheme can not only avoid single-point failure of the transmission chain, but also greatly reduce the mass resource requirements of the spacecraft, and can also greatly extend the on-orbit operation life of the solar orientation drive mechanism and improve the long-life reliability;

[0028] (7) A large-scale, high-load-bearing, long-life, and maintainable solar orientation drive mechanism and operation method provided by the present invention adopt the participation of astronauts and on-orbit autonomous refueling and maintenance of the on-orbit refueling component, realizing the function of regular on-orbit maintenance of the solar orientation drive mechanism. It has the advantages of on-orbit maintainability and simple and convenient operation, greatly reducing the operation difficulty of astronauts. The realization of the on-orbit maintainable function of the solar orientation drive mechanism further improves the on-orbit operation life and long-life reliability of the solar orientation drive mechanism. Description of the Drawings

[0029] Figure 1Schematic diagram of the overall structure of the initial state (launch section) of a large-scale, high-load, long-life, and maintainable solar orientation drive mechanism of the present invention;

[0030] Figure 2 Cross-sectional view of the overall structure of a large-scale, high-load, long-life, and maintainable solar orientation drive mechanism of the present invention;

[0031] Figure 3 Schematic diagram of the structure of the composite material main structure of the present invention;

[0032] Figure 4A Schematic diagram of the structure of the strap locking and releasing assembly;

[0033] Figure 4B Partial schematic diagram of the clamping and locking state of the strap locking and releasing assembly;

[0034] Figure 4C Three-dimensional view of the collection assembly in the strap locking and releasing assembly;

[0035] Figure 4D Side view (top) and top view (bottom) of the collection assembly in the strap locking and releasing assembly;

[0036] Figure 4E Schematic diagram of the structure of the coil spring assembly in the collection assembly;

[0037] Figure 4F Schematic diagram of the structure of the roller assembly in the collection assembly;

[0038] Figure 4G Schematic diagram of the structure of the buffer assembly in the collection assembly;

[0039] Figure 5A Schematic diagram of the structure of the slewing support device;

[0040] Figure 5B Three-dimensional view of the guide rail in the slewing support device;

[0041] Figure 5C Cross-sectional view of the guide rail in the slewing support device;

[0042] Figure 5D Schematic diagram of the structure of the main slewing support assembly in the slewing support device;

[0043] Figure 5E Schematic diagram of the structure of the switching and locking assembly in the slewing support device;

[0044] Figure 5F Schematic diagram of the main and backup slewing support assemblies clamping the guide rail in the slewing support device;

[0045] Figure 5G Schematic diagram of the switching and locking assembly clamping and locking and disengaging from the guide rail in the slewing support device;

[0046] Figure 6A It is a structural schematic diagram of a rolling ring electric transmission device;

[0047] Figure 6B It is a schematic diagram of the connection between the rolling ring electric transmission device and the truss interface flange;

[0048] Figure 7 It is a structural schematic diagram of a drive locking component;

[0049] Figure 8A It is a structural schematic diagram of an in-orbit refueling component;

[0050] Figure 8B It is a structural schematic diagram of an oil storage module;

[0051] Figure 8C It is a structural schematic diagram of an oil spreading module;

[0052] Figure 8D It is a structural schematic diagram of an oil transmission pipeline module;

[0053] Figure 8E It is a structural schematic diagram of an operating handwheel module;

[0054] Figure 8F It is a structural schematic diagram of a transmission module;

[0055] Figure 8G It is a structural schematic diagram of a clamping module. Specific implementation manners

[0056] The present invention will be described in detail below, and the features and advantages of the present invention will become clearer and more definite with these descriptions.

[0057] The special word "exemplary" here means "serving as an example, embodiment or illustration". Any embodiment described here as "exemplary" does not have to be construed as superior or better than other embodiments. Although various aspects of the embodiments are shown in the drawings, the drawings do not have to be drawn to scale unless otherwise specified.

[0058] During the launch phase, large overloads are generated by the external loads of the truss-side solar wings and truss-related equipment, and the sun-pointing drive mechanism needs to provide a large load-bearing capacity; while during the orbit insertion phase, after the truss-side solar wings are fully deployed, a large moment of inertia is generated, and the sun-pointing drive mechanism needs to provide a large driving capacity and braking capacity. In addition, with the development of large spacecraft in China, the requirements for high-power transmission and long-life operation are also increasing. High load-bearing, high driving, high braking, high power, and long life have become a major trend in the development of sun-pointing drive mechanisms, which has also greatly increased the design difficulty of sun-pointing drive mechanisms. Traditional sun-pointing drive mechanisms mostly adopt the driving form of motors, reducers, and output shafts. Although the structure is simple, there are problems such as small load-bearing capacity, weak driving and braking capabilities, small transmission power, and short service life. Therefore, in order to meet the development needs of large spacecraft in China, there is an urgent need for a sun-pointing drive mechanism that can meet at least one of the requirements of high load-bearing, high driving, high braking, high power, and long life.

[0059] The new requirements bring a series of technical difficulties in the load-bearing mode, driving mode, braking mode, power signal transmission mode, long-life use mode, etc. of the sun-pointing drive mechanism. Therefore, it is necessary to carry out research and development on the key technologies of the sun-pointing drive mechanism to meet the application requirements of high load-bearing, high driving, high braking, high power, long life, and maintainability of future large sun-pointing drive mechanisms. In the present invention, through the comprehensive application of five key technologies, namely the overall design and integration technology of large sun-pointing drive mechanisms, high-load slewing bearing technology, multi-mode driving and braking technology, high-power multi-signal transmission technology, and long-life maintainable technology, the objectives of strong load-bearing capacity during the launch phase, large driving capacity, strong braking capacity, high transmission power, long operating life, and on-orbit maintainability are achieved. The large high-load long-life maintainable sun-pointing drive mechanism disclosed in the present invention has obvious advantages in load-bearing during the launch phase, driving and braking during the on-orbit phase, transmission power and signal capabilities. At the same time, it can achieve on-orbit refueling maintenance with the participation of astronauts, meet the use requirements of long-life on-orbit maintainability, and has better reliability.

[0060] As Figure 1 and Figure 2 shown, a large high-load long-life maintainable sun-pointing drive mechanism provided by the present invention includes a composite material main structure 1, a cabin interface flange 2, a truss interface flange 3, a strap locking and releasing assembly 4, a slewing bearing device 5, a rolling ring electrical transmission device 6, a driving and locking assembly 7, and an on-orbit refueling assembly 8;

[0061] The truss interface flange 3 provides an interface for connecting external loads outside the cabin;

[0062] The cabin interface flange 2 provides an interface for connecting the spacecraft cabin;

[0063] The main composite structure 1 is connected to the interface flange 2 of the cabin, and is used to support the truss interface flange 3 during the launch stage;

[0064] The strap locking and releasing assembly 4 clamps the main composite structure 1 and the truss interface flange 3 during the launch stage, and releases the main composite structure 1 and the truss interface flange 3 during the on-orbit stage;

[0065] The top of the slewing bearing device 5 is connected to the truss interface flange 3, and the bottom is connected to the interface flange 2 of the cabin. It is used to lock and support the truss interface flange 3 during the launch stage and the on-orbit stage, and provides a slewing freedom degree for the truss interface flange 3 during the on-orbit stage;

[0066] The drive locking assembly 7 is installed on the interface flange 2 of the cabin or the truss interface flange 3, and is used as a power source to cooperate with the slewing bearing device 5 to drive the truss interface flange 3 to rotate;

[0067] The rotor in the rolling ring electrical transmission device 6 is fixedly connected to the truss interface flange 3, and the power cable and signal cable at the truss end are connected; the housing of the rolling ring electrical transmission device 6 is used as a stator and is fixedly connected to the interface flange 2 of the cabin. Power and signal transmission are formed between the stator and the rotor, and the power cable and signal cable are led out from the stator to the cabin, finally realizing the one-way continuous rotation of the truss interface flange 3 without cable entanglement;

[0068] The on-orbit oil replenishing assembly 8 is installed on the interface flange 2 of the cabin to lubricate the guide rail of the slewing bearing device 5 and improve the lubrication state.

[0069] As Figure 3 shown, the main composite structure 1 is a conical cylinder structure, and the large end is fixedly connected to the interface flange 2 of the cabin. The small end is connected to the truss interface flange 3 through the strap locking and releasing assembly 4 during the launch stage, playing a role in shaping and structural protection for the entire sun-pointing drive mechanism; during the on-orbit stage, it is disconnected from the truss interface flange 3 and no longer supports the truss interface flange 3. This conical design is beneficial for bearing force. Weight reduction windows are opened on the wall surface of the main composite structure 1, which is convenient for disassembly and assembly of the internal slewing bearing device 5 while reducing weight.

[0070] As Figure 4A and Figure 4B shown, the strap locking and releasing assembly 4 includes at least two straps 41, a plurality of clamping blocks 42, a plurality of explosive bolts 43 and multiple groups of collecting assemblies 44; the clamping blocks 42 are circumferentially distributed evenly, and are attached to the outer circumferential surface and the upper and lower sides of the truss interface flange 3 and the main composite structure 1 to clamp the truss interface flange 3 and the main composite structure 1; the straps 41, such as three straps, wrap all the clamping blocks 42 and are connected end to end through the explosive bolts 43; the collecting assemblies 44 are installed on the truss interface flange 3, and each collecting assembly 44 extends out a rope to fix the strap 41, which is used to pull and lift the strap 41 after the explosive bolt 43 detonates.

[0071] As Figure 4B shown, the clamping block 42 is a W-shaped clamping block, with two grooves formed on the inner side thereof for respectively mating with the outer circumferential surface of the truss interface flange 3 and the composite material main structure 1. The protrusion formed between the two grooves is embedded into the gap between the truss interface flange 3 and the outer circumferential surface of the composite material main structure 1.

[0072] As Figures 4C to 4D shown, the collecting assembly 44 includes a spiral spring assembly 441, a roller assembly 442, a buffer assembly 443, a rope assembly 444, a limit bracket 445, a rope clip 446, a slide plate 447 and a support seat 448; the spiral spring assembly 441 is installed on the support seat 448 and connected to one end of the rope of the rope assembly 444 for providing a pre-tightening moment and a pulling force; the limit bracket 445 is installed on the spiral spring assembly 441, and the roller assembly 442 and the buffer assembly 443 are respectively installed on the upper and lower sides of the limit bracket 445. The axis of the roller assembly 442 is perpendicular to the rope to guide the rope. The buffer assembly 443 is used to buffer the impact of the rope clip 446 and the slide plate 447 after the tightening strip 41; the rope clip 446 is located at the upper end of the slide plate 447 and is fixedly installed on the clamping block 42 together with the slide plate 447. The rope clip 446 and the slide plate 447 are provided with rope grooves along the set rope running direction for guiding the rope after the roller assembly 442; a strip hole allowing the strip 41 to pass through is formed between the slide plate 447 and the clamping block 42 and is circumferentially bound and fixed by the strip 41. Lugs are processed on the outer side of the slide plate 447. After the other end of the rope passes through the spiral spring assembly 441, it passes through the roller assembly 442 and the rope grooves formed on the rope clip 446 and the slide plate 447 and is connected to the lug of the slide plate 447.

[0073] As Figure 4E shown, the spiral spring assembly 441 includes a housing 4411, a scroll spring 4412, a scroll spring barrel 4413, a rotating shaft 4414, a wire rope drum 4415, a bearing 4416, a support structure 4417 and an end cover 4418;

[0074] The housing 4411 is used to provide an accommodation space; the scroll spring 4412 is placed in the scroll spring barrel 4413. The outer side of the scroll spring 4412 is connected to the scroll spring barrel 4413, and the inner side is connected to the rotating shaft 4414. Rotating the scroll spring barrel 4413 applies an initial pre-tightening moment to the scroll spring 4412; the wire rope drum 4415 is connected to the rotating shaft 4414 and rotates with the rotating shaft 4414; the bearing 4416 is sleeved on the rotating shaft 4414 and is limited in the housing 4411 through the end cover 4418 and the support structure 4417.

[0075] As Figure 4FAs shown, the roller assembly 442 includes a roller 4421, a roller bracket 4422, and a roller shaft 4423; the roller 4421 and the roller shaft 4423 of the roller assembly 442 can rotate relative to each other to change the direction of the wire rope; a U-shaped groove structure is formed in the circumferential direction of the roller 4421, with a groove in the middle and shoulders at both ends, so that the wire rope passing through the roller assembly is always located within the U-shaped groove.

[0076] As Figure 4G As shown, the buffer assembly 443 is composed of a stainless steel cover 4431 and a silicone rubber block 4432; the stainless steel cover 4431 is formed by stamping a stainless steel plate with good toughness, and the stainless steel cover is in a "return" configuration, with both the inner and outer sides protruding, completely wrapping the outer side surfaces of the silicone rubber block 4432 except the upper end surface. The buffer assembly 443 is installed on the limit bracket 445, and the upper end surface of the silicone rubber block 4432 is closed by the lower end surface of the limit bracket 445.

[0077] After the strap locking and releasing assembly is unlocked, in order not to affect the movement of the connected body, the unlocked strap locking and releasing assembly is pulled away from the separation surface and limited. It is connected to the clip and the strip through the sliding plate. One end of the wire rope assembly is connected to the sliding plate, and the other end is connected to the wire rope reel of the volute spring assembly. The strip is connected to the collection assembly. A wire rope movement path is formed through the limit bracket, the roller assembly, and the wire rope clip to realize pulling the strip obliquely upward. The volute spring applies a certain pre-tightening torque. After the strip is unlocked, the volute spring acts to drive the wire rope reel to rotate through the rotating shaft. The rotation of the wire rope reel pulls the strip obliquely upward through the wire rope assembly, and the strip disengages from the connected part. Under the continuous action of the volute spring, the strip continues to move upward. The wire rope clip and the upper end of the sliding plate penetrate into the middle square opening of the buffer assembly. The clip hits the buffer assembly at the lower end of the limit bracket. The buffer assembly deforms to absorb energy, reducing the impact, and the strip stops moving. The volute spring still has a certain residual pre-tightening torque to limit the strip at the lower end of the limit bracket.

[0078] In the launch section, the explosive bolt 43 is tightened to tighten the strip 41, which can realize the high-rigidity connection between the truss interface flange 3 and the composite main structure 1. The strap locking and releasing assembly 4 can transfer the external load at the truss end of the launch section through the truss interface flange 3 through the clip 42 of the strap locking and releasing assembly 4, the composite main structure 1, and the cabin interface flange 2 to the cabin structure, avoiding the internal mechanism from bearing excessive external loads in the launch section. At this time, it is the locking state of the strap locking and releasing assembly 4.

[0079] After being in orbit, when the explosive bolt 43 explodes, the head-to-tail connection relationship of the strip 41 is disconnected, and the impact force of the explosive bolt 43 causes the clamping block 42 to disengage from the truss interface flange 3 and the composite main structure 1. At the same time, the collection assembly 44 quickly pulls up all the strips 41 together with the clamping block 42 through the rope, lifts and disengages them from the outer circle interface of the truss interface flange 3 and the composite main structure 1, and no longer affects the relative rotational freedom between the truss interface flange 3 and the composite main structure 1. At this time, it is the unlocked state of the strap locking and releasing assembly 4.

[0080] As Figure 5A shown, the slewing bearing device 5 includes multiple sets, such as 4 sets of switching and locking assemblies 51, guide rails 52, multiple sets, such as 8 sets of main slewing bearing assemblies 53, and multiple sets, such as 8 sets of standby slewing bearing assemblies 54. The main slewing bearing assembly 53 is installed on the cabin interface flange 2, and the standby slewing bearing assembly 54 is installed on the truss interface flange 3, and they are installed circumferentially and evenly. The two ends of the guide rail 52 are respectively clamped between the main slewing bearing assembly 53 and the standby slewing bearing assembly 54; part of the switching and locking assembly is installed on the cabin interface flange 2, and part of it is installed on the truss interface flange 3, and they are arranged radially and symmetrically, and can all clamp the inner and outer sides of the guide rail 52.

[0081] As Figure 5B and Figure 5C shown, the guide rail 52 is a circular ring structure, and the cross-sections at the upper and lower ends are symmetric triangular structures, which can be divided into an inner inclined surface 521, an outer inclined surface 522, and an end surface 523. There is a straight transition section 524 between the inner inclined surface 521 and the end surface 523, and an internal gear ring structure 525 is arranged on the straight transition section 524, which is the driving torque input interface of the driving and locking assembly 7; the cross-section of the middle section of the guide rail 52 is a regular rectangle, which is divided into an inner side surface 526 and an outer side surface 527.

[0082] As Figure 5DAs shown, the main slewing support assembly 53 and the standby slewing support assembly 54 include a clamping part and a mounting part 534. The clamping parts of both have the same structure and are used to clamp both ends of the guide rail 52. The mounting parts 534 are respectively fixedly connected to the cabin interface flange 2 or the truss interface flange 3. The clamping part includes a main clamping arm 531, a secondary clamping arm 532, and a bottom clamping arm 533. The bottom clamping arm 533 is directly mounted on the mounting part 534. The main clamping arm 531 and the secondary clamping arm 532 are respectively connected to the mounting part 534 through a pin shaft 535 and can rotate around the shaft. The main clamping arm 531 and the secondary clamping arm 532 are connected through a clamping bolt 536. Each clamping arm is provided with a freely rotatable roller assembly 537, and a freely rotatable roller 538 is arranged inside the roller assembly 537. The main clamping arm 531, the secondary clamping arm 532, and the bottom clamping arm 533 respectively correspond to the outer inclined surface 522, the inner inclined surface 521, and the end surface 523 of the guide rail. By tightening the clamping bolt, the outer ring surfaces of the rollers of the main clamping arm, the secondary clamping arm, and the bottom clamping arm can respectively fit the outer inclined surface, the inner inclined surface, and the end surface at one end of the guide rail, forming a stable clamping state; loosen and disconnect the clamping bolt from the secondary clamping arm, and the secondary clamping arm can rotate around the pin shaft, making the clamping part in an open state. When the outer ring surface of the roller fits the guide rail surface, it can roll as the guide rail rotates, providing the rotational freedom of the guide rail and playing the role of clamping and supporting the guide rail. The rotational freedom of the roller assembly 537 can adapt to the slight changes in the angles of each guide rail surface during the operation process to ensure good contact between the outer ring surface of the roller and the guide rail surface.

[0083] As Figure 5E shown, the switching and locking assembly 51 includes a main locking arm 511, a secondary locking arm 512, a motor drive part 513, and a main structure part 514. The main structure part 514 provides a mechanical interface for connecting to the cabin interface flange 2 and the truss interface flange 3. The main locking arm 511 and the secondary locking arm 512 are connected to the main structure part 514 through a rotating support shaft 515 and can rotate around the rotating support shaft. A locking piece 516 is installed at the end of each of the main locking arm 511 and the secondary locking arm 512. The locking pieces 516 of the main locking arm 511 and the secondary locking arm 512 respectively fit or separate from the outer side surface 527 and the inner side surface 526 of the guide rail 52. The motor drive part 513 is installed on the main structure part 514 and is connected to the main locking arm 511 and the secondary locking arm 512 to form a linkage mechanism. When the motor drive part 513 acts, it can drive the main locking arm 511 and the secondary locking arm 512 to lock or unlock the guide rail 52 together. Each set of switching and locking assembly 51 can independently lock and unlock the guide rail.

[0084] As Figure 2 , Figure 5A , Figure 5F and Figure 5GAs shown, the slewing support device is provided with three working modes. When the guide rail 52 can only rotate relative to the main slewing support assembly 53 on the cabin side, it is the main slewing support mode. When the guide rail 52 can only rotate relative to the standby slewing support assembly 54 on the truss side, it is the standby slewing support mode. When the guide rail 52 cannot rotate relative to both slewing support assemblies on both sides, it is the locking support braking mode. In the main slewing support mode, the truss-side switching and locking assembly 51 clamps and locks the guide rail 52, and the cabin-side switching and locking assembly 51 disengages from the guide rail. The guide rail 52 can rotate freely within the main slewing support assembly 53 on the cabin side, and the standby slewing support assembly 54 on the truss side remains stationary relative to the guide rail 52. If the truss interface flange end is the rotating body and the cabin interface flange end is the stationary body, when the main slewing support mode is running, the cabin interface flange 2 and the switching and locking assembly 51 and the main slewing support assembly 53 installed thereon remain stationary, while the guide rail 52, the truss interface flange 3 and the switching and locking assembly 51 and the standby slewing support assembly 54 installed thereon can rotate, realizing the mutual rolling transmission between the main slewing support assembly 53 and the guide rail against the guide rail surface at the cabin interface flange end.

[0085] In the standby slewing support mode, the truss-side switching and locking assembly 51 disengages from the guide rail, and the cabin-side switching and locking assembly 51 clamps and locks the guide rail. The guide rail 52 rotates relative to the standby slewing support assembly 54 on the truss side, and the main slewing support assembly 53 on the cabin side remains stationary relative to the guide rail 52. If the truss interface flange end is the rotating body and the cabin interface flange end is the stationary body, when the standby slewing support mode is running, the guide rail 52, the cabin interface flange 2 and the switching and locking assembly 51 and the main slewing support assembly 53 installed thereon remain stationary, while the truss interface flange 3 and the switching and locking assembly 51 and the standby slewing support assembly 54 installed thereon can rotate, realizing the mutual rolling transmission between the standby slewing support assembly 54 and the guide rail against the guide rail surface at the truss interface flange end.

[0086] In the locking support braking mode, both the truss-side switching and locking assembly and the cabin-side switching and locking assembly clamp and lock the guide rail. The guide rail 52 cannot rotate freely within the standby slewing support assembly 54 on the truss side and the main slewing support assembly 53 on the cabin side, and the three remain stationary relative to each other.

[0087] In the main slewing support mode and the standby slewing support mode, the slewing support device can only bear the axial load and radial load outside the truss interface flange and cannot directly bear the torque load. In the locking support braking mode, the slewing support device can not only bear the axial load and radial load outside the truss interface flange but also bear the torque load to realize the braking function.

[0088] Such as Figure 2 and Figure 6AAs shown in the figure, the rolling ring electrical transmission device 6 includes a rolling ring module 61 and a slip ring module 62. The rolling ring module 61 is used to transmit the electrical energy generated by the extravehicular solar wing panels into the cabin, and the slip ring module 62 is used for signal transmission and interaction between the equipment inside and outside the cabin. The stator of the rolling ring module 61 is connected to the stator of the slip ring module 62 to form the stator of the rolling ring electrical transmission device 6. The rotor of the rolling ring module 61 is connected to the rotor of the slip ring module 62 to form the rotor of the rolling ring electrical transmission device 6, generating coaxial rotation.

[0089] As Figure 6B shown in the figure, the rotor of the rolling ring electrical transmission device 6 is connected to the truss interface flange 3 through the rolling ring truss connector 63. When the truss interface flange 3 rotates relative to the cabin interface flange 2, the rotors of the rolling ring module 61 and the slip ring module 62 rotate synchronously with the truss interface flange 3. During the rotation process, the power and electrical signals generated outside the spacecraft are transmitted to the inside of the spacecraft. The rolling ring electrical transmission device 6 can not only avoid the cable winding problem during the continuous rotation of the rotating end, but also achieve the function of high-power transmission.

[0090] An upper mounting flange 611 is arranged on the upper periphery of the rolling ring module 61, and a lower mounting flange 621 is arranged on the lower periphery of the slip ring module 62. Opposite conical barrel sections are arranged on the upper and lower sides of the cabin interface flange 2. The large ends of the two conical barrel sections are fixed on the cabin interface flange 2, and the small ends form interface flanges, which are respectively docked with the upper mounting flange 611 and the lower mounting flange 621.

[0091] Preferably, the rolling ring module of the rolling ring electrical transmission device 6 has 16 rings. Each single ring can transmit a current of 60A, and the total power is better than 50kW. The slip ring module has 206 rings, among which 30 rings are used to transmit 10 channels of 1553B signals, 2 rings are used to transmit 10A squib current, and 2 rings are used to transmit 20A squib current. It has the characteristics of large transmission power and many signals, and can meet the requirements of high-power transmission of spacecraft and signal transmission of multiple extravehicular devices.

[0092] As Figure 2 and Figure 7 shown in the figure, the drive locking assembly 7 includes a motor 71, a clutch 72, a brake 73, a gear 74 and a speed reducer 75. The brake 73 performs braking control on the motor 71. The output shaft of the motor 71 is connected to the input shaft of the speed reducer 75. The output shaft of the speed reducer 75 is connected to the input flange of the clutch 72. The output flange of the clutch 72 is connected to the gear 74 through the output shaft of the drive locking assembly 7. The gear 74 meshes with the internal tooth ring structure 525 of the guide rail 52 to output torque, serving as the driving torque output interface of the drive locking assembly 7, and the motor 71 serves as the driving source.

[0093] There are three sets of driving and locking components 7, namely the first driving and locking component 710, the second driving and locking component 720, and the third driving and locking component 730. The first driving and locking component 710 and the second driving and locking component 720 are installed on the cabin interface flange 2, and the third driving and locking component 730 is installed on the truss interface flange 3, which is used in cooperation with the slewing bearing device 5 as a power source.

[0094] The driving and locking component 7 has a total of three working modes. Among them, when the clutch 72 is engaged and the brake 73 is disengaged, it is the driving link connection mode; when the clutch 72 is disengaged, it is the driving link disconnection mode; when both the clutch 72 and the brake 73 are engaged, it is the driving link braking mode. The driving link connection mode can transmit and output the driving torque generated by the motor. The driving link braking mode can transmit and resist the externally input torque to achieve the braking of the transmission chain. The driving link disconnection mode can not only timely disconnect the transmission chain when the external load abnormally increases to avoid the overload damage of each transmission element on the transmission chain, but also isolate the faulty unit when a jamming fault occurs in the motor and reducer inside the driving and locking component to avoid the mutual influence between different transmission chains.

[0095] As Figure 1 and Figure 8A shown, the in-orbit oil replenishment component 8 includes an oil spreading module 81, an oil pipeline module 82, an operating handwheel module 83, a transmission module 84, an oil storage module 85, a clamping module 86, and a base 87. Among them, the operating handwheel module 83, the transmission module 84, the oil storage module 85, and the clamping module 86 are respectively installed on the base 87; the oil storage module 85 is connected to the oil spreading module 81 through the oil pipeline module 82; the oil spreading module 81 is installed on the base 87 through the clamping module 86; the operating handwheel module 83 is connected to the clamping module 86 through the transmission module 84.

[0096] The oil storage module 85 is used to store lubricating oil and provide oil supply pressure to supply oil to the oil spreading module 81. The oil pipeline module 82 is used to transport the lubricating oil stored in the oil storage module 85 to the oil spreading module 81. The oil spreading module 81 is used to evenly apply the lubricating oil to the contact interface of the spacecraft moving parts (the inner inclined surface 521, the outer inclined surface 522, and the end surface 523 of the guide rail surface) under the action of the clamping module 86 to compensate for the volatilization loss of the lubricating oil on the contact interface during long-term operation in orbit, so as to improve its lubrication state and achieve the in-orbit maintenance and life extension of the moving parts. The transmission module 84 is used to drive the clamping module 86 to control the oil spreading module 81 under the operation of the operating handwheel module 83. The operating handwheel module 83 is used to provide power input in response to the on-orbit operation of the astronaut. The clamping module 86 is used to control the opening / closing of the oil storage module 85 and the clamping / disengagement of the oil spreading module 81 under the drive of the transmission module 84.

[0097] As Figure 8BAs shown in the figure, the oil storage module 85 specifically includes: a conical seal A851, a metal hard pipe 852, a ball valve support 853, an oil storage tank 855, a metal elbow A856, and a two-way ball valve 857. Among them, the oil storage tank 855 is fixed to the lower surface of the base 87 by threaded connectors. One end of the metal elbow A856 is connected to the oil storage tank 855, and the other end is connected to one end of the metal hard pipe 852 through the two-way ball valve 857. A conical seal A851 is provided at the other end of the metal hard pipe 852. The ball valve support 853 is fixed to the upper surface of the base 87 by threaded connectors. The two-way ball valve 857 is installed on the ball valve support 853, and the storage / transportation of lubricating oil in the oil storage tank 855 can be realized by rotating the two-way ball valve 857 by ±90°.

[0098] The oil storage tank 855 has its own oil supply pressure and is mainly composed of a metal bellows, a spring, a spring guide rod, a guide cylinder, etc. Among them, the spring is sleeved on the spring guide rod and is limited in the metal bellows by the guide cylinder. The working principle is as follows: Lubricating oil is stored in the metal bellows, and the spring at the bottom of the metal bellows provides the oil supply pressure. When the two-way ball valve 857 is opened, the elastic force of the spring transports the lubricating oil in the metal bellows to the oil pipeline module and finally reaches the oiling module.

[0099] The conical seal A851, the metal hard pipe 852, the two-way ball valve 857, and the metal elbow A856 form a set of oil storage output units. There are three groups of oil storage output units. One end of the three groups of oil storage output units is connected to the oil storage tank 855, and the other end of the three groups of oil storage output units is respectively connected to three oiling modules 81 through the oil pipeline module 82.

[0100] As Figure 8C shown in the figure, the oiling module 81 specifically includes: a conical seal B811, a metal elbow B812, an oil tanker 813, a rotating support 814, a conical seal C815, a cover plate 816, and threaded connectors 817. Among them, a conical seal B811 is provided at one end of the metal elbow B812, the other end of the metal elbow B812 is connected to the cover plate 816 through the rotating support 814, and the metal elbow B812 and the rotating support 814 are sealed through the conical seal C815. The oil tanker 813 is installed on the cover plate 816 through the threaded connectors 817.

[0101] As Figure 8D shown in the figure, the oil pipeline module 82 includes three metal hoses 821. Among them, one end of the metal hose 821 is connected to the other end of the metal hard pipe 852 and is sealed through the conical seal A851; the other end of the metal hose 821 is connected to one end of the metal elbow B812 and is sealed through the conical seal B811.

[0102] As Figure 8EAs shown in the figure, the operating handwheel module 83 may specifically include: bevel gear A8311, bevel gear B8312, bevel gear C8313, mounting base 832, operating handwheel 833, identification disc 834, handwheel mounting rod 835, input shaft A8361, and input shaft B8362. Among them, one end of the handwheel mounting rod 835 is connected to the operating handwheel 833, and the other end is connected to one end of the input shaft A8361; the astronaut inputs power by rotating the operating handwheel 833. The identification disc 834 is mounted on the handwheel mounting rod 835 to facilitate the astronaut to identify the rotation position when rotating the operating handwheel 833. The input shaft A8361 is fixed on the mounting base 832 in the horizontal direction, and the input shaft B8362 is fixed on the mounting base 832 in the vertical direction; the mounting base 832 is fixed on the base 87. The other end of the input shaft A8361 is equipped with bevel gear A8311, and both ends of the input shaft B8362 are respectively equipped with bevel gear B8312 and bevel gear C8313, and bevel gear A8311 meshes with bevel gear B8312.

[0103] As Figure 8F shown in the figure, the transmission module 84 may specifically include: worm A841, worm B842, turbine mounting shaft 843, and ball valve shaft system 844. Among them, the transmission module 84 inputs and reverses the power of the operating handwheel module 83 through the bevel gear pair at the right end of the worm B842. After the input power passes through the worm B842, it is divided into two branch powers. The first branch power is reversed through the worm gear of the turbine mounting shaft 843 and then input to the three ball valve shaft systems 844. The three ball valve shaft systems 844 are respectively connected to the switch interfaces of the three two-way ball valves 857 of the oil storage module 85. This first branch power is used to control the start / stop of the three two-way ball valves 857; the second branch power is reversely input to the clamping module 86 through the bevel gear pair of the worm A841 to control the movement of the clamping module 86.

[0104] As Figure 8GAs shown in the figure, the clamping module 86 may specifically include: a ball linear guide pair A861, a worm C862, a sliding pin 863, a worm gear-cam 864, a ball linear guide pair B865, a clamping arm 866, and a vertical ball linear guide pair. Among them, the clamping module 86 transmits the power of the transmission module 84 from the worm C862 to the worm gear-cam 864. Three sliding pins 863 are installed in the three chutes of the worm gear-cam 864, and the three sliding pins 863 are respectively fixedly connected to the three clamping arms 866; the three clamping arms 866 are respectively installed on the ball linear guide pair A861, the ball linear guide pair B865, and the vertical ball linear guide pair. When the worm gear-cam 864 rotates clockwise, the three clamping arms 866 realize the clamping function through linear motion; when the worm gear-cam 864 rotates counterclockwise, the three clamping arms 866 realize the releasing function through linear motion; among them, the linear motion includes horizontal linear motion and vertical linear motion. The clamping arm 866 makes horizontal linear motion through the ball linear guide pair A861 and the ball linear guide pair B865, and the clamping arm 866 makes vertical linear motion through the vertical ball linear guide pair. The clamping of the three clamping arms 866 reaches synchronously with the opening of the three two-way ball valves 857, and the releasing of the three clamping arms 866 reaches synchronously with the closing of the three two-way ball valves 857, thereby realizing the multi-functional integration of the oiling module 81 for clamping / releasing and the starting / stopping of the ball valve.

[0105] The oil outlet mode of the oiling module is follow-up oil outlet, that is, the oil wheel in the oiling module rotates with the rotation of the guide rail of the sun orientation mechanism, and the internal lubricating oil is taken out and smeared on the guide rail surface during the rotation process. The lubricating oil stored in the oil storage module is transported to the oil cavity of the oiling module through the oil pipeline module under the action of the oil supply pressure. The oil wheel has a strong affinity for the lubricating oil, and can adsorb the lubricating oil in the oil cavity on the outer circle surface of the oil wheel. The oil wheel rotates with the rotation of the guide rail, and then smears the lubricating oil in the oil cavity on the guide rail surface. The function of the two-way ball valve is to control the on / off of the oil supply from the oil storage module to the oiling module; the rotary switch of the two-way ball valve is connected to the bevel gear, and the two-way ball valve is opened / closed by the rotation of the bevel gear.

[0106] The function of the clamping module is to realize the contact and separation between the oiling module and the guide rail surface. Its working principle is as follows: Corresponding guide grooves are provided on the turbine, and sliding pins are provided on the three clamping arms of the clamping device. When the turbine rotates, the sliding pins move under the action of the guide grooves, and then drive the three clamping arms of the oiling device to move together, so that the oiling device located at the end of the clamping arm fits or separates from the guide rail surface. The two side clamping arms move horizontally to contact and separate from the guide rail through the guidance of the linear bearing and the turbine; the bottom clamping arm moves vertically to contact and separate from the guide rail through the guidance of the straight guide rail and the turbine.

[0107] The function of the transmission module is: when the astronauts intervene to operate the handwheel, the three guide rail surfaces can be simultaneously refueled and maintained on the track. The three clamping components and the three oil valve switches need to act at the same time. Therefore, the mechanism needs to be equipped with 6 transmission chains to ensure that the 6 actions are completed at the same time, and the multifunctional integration of clamping disengagement and oil valve opening and closing is realized. The power input of the astronauts is divided into two parts, one to drive the oil valves of the three oil pipelines to open and close, and the other to drive the clamping arm of the clamping device to fit and disengage from the guide rail surface. The working principle is: the astronauts rotate the mechanism operating handle, which is transmitted to the clamping device and the oil valve through the transmission mechanism, and the clamping mechanism is driven to clamp the guide rail surface and open the oil valve. Conversely, the astronauts rotate the operating handle in the opposite direction, which is transmitted to the clamping mechanism and the oil valve through the transmission mechanism, and the clamping mechanism is driven to loosen the guide rail surface and close the oil valve.

[0108] When the two-way ball valve is closed, the oiling module is separated from the contact interface of the moving parts, and the lubricating oil in the oil storage module is sealed reliably in the oil storage tank for a long time, thereby realizing long-term reliable storage of the lubricating oil in orbit; when the two-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 pipeline module under the action of the oil supply pressure, and the oiling module evenly applies the lubricating oil to the contact interface of the spacecraft moving parts under the action of the clamping module, thereby compensating for the volatilization loss of the lubricating oil on the contact interface for a long time in orbit, so as to improve its lubrication state and realize the on-orbit maintenance and life extension of the moving parts.

[0109] In the present invention, in order to achieve the goal of being able to withstand the overload of the launch section and bear the load of the on-track section while reducing the demand for mass resources, multiple load-bearing links are set. Among them, the composite material main structure 1 is connected to the cabin interface flange 2, and the wrapping belt locking and releasing assembly 4 clamps the composite material main structure 1 and the truss interface flange 3. The external load can be transferred from the truss interface flange 3 to the cabin through the wrapping belt locking and releasing assembly 4, the composite material main structure 1, and the cabin interface flange 2, forming an external load-bearing link. The slewing support device 5 is connected to the truss interface flange 3 at the top and the cabin interface flange 2 at the bottom. The external load can be transferred from the truss interface flange 3 to the cabin through the slewing support device 5 and the cabin interface flange 2, forming an internal load-bearing link.

[0110] In the launch section, the external load-bearing link and the internal load-bearing link together constitute the launch section load-bearing link, in which the external load-bearing link is much larger than the internal load-bearing link, and the axial tensile and compressive stiffness is 1.9~2.3×10 5 N / mm, as the main load-bearing link of the launch section, the axial tensile and compressive stiffness of the internal load-bearing link is 4.5~7.3×10 4 N / mm, as an auxiliary load-bearing link. After entering the track, the external load-bearing link is disconnected as the strapping locking release assembly is unlocked and no longer carries any load. The internal load-bearing link serves as the only link that carries the load in the on-track section.

[0111] In the present invention, in order to achieve high-reliability transmission of the mechanism, three drive links are provided. Specifically, the cabin interface flange 2, the drive locking assembly 7, the slewing bearing device 5, and the truss interface flange 3 form a drive link. Among them, the cabin interface flange 2 serves as the fixed end, the truss interface flange 3 serves as the rotating end, the drive locking assembly 7 serves as the power output assembly, and the external load installed on the upper part of the truss interface flange 3 serves as the drive load. Among them, the first drive locking assembly 710 and the main slewing mode of the slewing bearing device form the first drive link, the second drive locking assembly 720 and the main slewing mode of the slewing bearing device form the second drive link, and the third drive locking assembly 730 and the standby slewing mode of the slewing bearing device form the third drive link.

[0112] The first drive link and the second drive link share the main slewing mode of the slewing bearing device 5, and are not completely independent. The third drive link uses the standby slewing mode alone and is completely isolated from the first drive link and the second drive link. This not only realizes the full utilization of limited resources, but also avoids single-point failure, and can greatly extend the in-orbit operation life of the sun-pointing drive mechanism, and further improve the long-life reliability of the mechanism.

[0113] After considering the transmission efficiency, the total output torque of each drive link is better than 350 Nm, which has the characteristic of high driving ability.

[0114] In the present invention, in order to adapt to the braking requirements of different loads and different durations, two braking modes, namely locking support braking and drive link braking, are provided. Specifically, the locking support braking mode is that both the truss-side switching locking component and the cabin-side switching locking component of the slewing bearing device clamp and lock the guide rail, and the guide rail cannot rotate freely inside the truss-side main slewing support component 53 and the cabin-side standby slewing support component 54, and always maintains a relatively static braking mode. The drive link braking mode is that the clutch 72 and the brake 73 at the drive locking component 7 in the drive link are both engaged, and the entire drive link is in a connected but non-rotating braking mode. In both braking modes, the sun-pointing drive mechanism cannot rotate.

[0115] Preferably, the locking support braking mode forms braking through structural rigid connection, and has a relatively strong braking ability, with a braking ability better than 510 Nm, and is suitable for long-term static and short-term large-load braking. The drive link braking mode forms braking on the low-speed end by locking the high-speed end of the transmission chain. Its braking ability is slightly weaker than the former, with a braking ability better than 290 Nm, but the braking operation is convenient and it is suitable for short-term medium and small-load braking.

[0116] In the present invention, the working mode of the slewing bearing device 5 can be switched autonomously. Specifically:

[0117] The locking support braking mode is switched to the main slewing bearing mode: the switching and locking component 51 on the truss side does not act and still maintains the state of clamping and locking the guide rail, while the switching and locking component 51 on the cabin side acts and adjusts from the state of clamping and locking the guide rail to the state of disengaging from the guide rail. The process of switching from the main slewing bearing mode to the locking support braking mode is the reverse of the above process and will not be elaborated here.

[0118] The locking support braking mode is switched to the standby slewing bearing mode: the switching and locking component 51 on the cabin side does not act and still maintains the state of clamping and locking the guide rail, while the switching and locking component 51 on the truss side acts and adjusts from the state of clamping and locking the guide rail to the state of disengaging from the guide rail. The process of switching from the standby slewing bearing mode to the locking support braking mode is the reverse of the above process and will not be elaborated here.

[0119] The main slewing bearing mode is switched to the standby slewing bearing mode: first, it needs to be switched from the main slewing bearing mode to the locking support braking mode, and then from the locking support braking mode to the standby slewing bearing mode. The switching and locking components act according to the corresponding mode switching. The process of switching from the standby slewing bearing mode to the main slewing bearing mode is the reverse of the above process and will not be elaborated here.

[0120] In the present invention, the drive link can be autonomously switched. Specifically:

[0121] When first switched from the locking support braking mode to the first drive link after entering the orbit: first, the working mode of the slewing bearing device 5 is switched from the locking support braking mode to the main slewing bearing mode, and then the clutch of the first drive locking component 710 is powered on and attracted to realize the connection of the first drive link;

[0122] The first drive link is switched to the second drive link: the working mode of the slewing bearing device remains unchanged in the main slewing bearing mode, the clutch of the first drive locking component 710 is powered off and disengaged, and the clutch of the second drive locking component 720 is powered on and attracted to realize the disconnection of the first drive link and the connection of the second drive link;

[0123] The first drive link or the second drive link is switched to the third drive link: first, the clutch of the first drive locking component 710 or the second drive locking component 720 is powered off and disengaged to realize the disconnection of the first drive link 710 or the second drive link 720; then the working mode of the slewing bearing device 5 is switched from the main slewing bearing mode to the standby slewing bearing mode; finally, the clutch of the third drive locking component 730 is powered on and attracted to realize the connection of the third drive link.

[0124] The present invention realizes the function of regular on-orbit maintenance for the sun-pointing drive mechanism, which has the advantages of being maintainable on orbit and having simple and convenient operation, greatly reducing the operation difficulty for astronauts. The realization of the on-orbit maintainable function of the sun-pointing drive mechanism further improves the on-orbit operation life and long-life reliability of the sun-pointing drive mechanism. The specific steps of on-orbit refueling maintenance are as follows:

[0125] First step, the working mode of the slewing bearing device 5 is set to the main slewing bearing mode, the working mode of the first drive locking assembly 710 is set to the drive link braking mode, and the sun-pointing drive mechanism stops rotating;

[0126] Second step, the astronaut performs an extravehicular walk to above the on-orbit refueling assembly 8, and manually rotates the operating handwheel 833 of the on-orbit refueling assembly 8 counterclockwise for one week. Then the astronaut performs an extravehicular walk to the safe area. At this time, the three oiling modules of the on-orbit refueling assembly 8 clamp the three guide rail surfaces, and the three oil delivery pipeline modules start to deliver lubricating oil to the oiling modules, and refueling begins;

[0127] Third step, the first drive locking assembly 710 switches from the drive link braking mode to the drive link connected mode and drives the sun-pointing drive mechanism to rotate. At this time, the guide rail surface on the cabin side of the slewing bearing device 5 slides in the oiling module of the on-orbit refueling assembly 8, and the lubricating oil is continuously transferred from the oiling module of the on-orbit refueling assembly 8 to the guide rail surface, realizing on-orbit refueling maintenance;

[0128] Fourth step, after the on-orbit refueling amount is sufficient, the first drive locking assembly 710 stops driving the sun-pointing drive mechanism to rotate and switches from the drive link connected mode to the drive link braking mode. The astronaut performs an extravehicular walk to above the on-orbit refueling assembly 8 again and manually rotates the operating handwheel of the on-orbit refueling assembly clockwise for one week. At this time, the oiling module of the on-orbit refueling assembly 8 disengages from the guide rail surface, and the three oil delivery pipeline modules stop delivering lubricating oil to the oiling modules. The astronaut returns to the cabin, and the on-orbit refueling maintenance task ends.

[0129] In the present invention, in order to realize the stable, orderly and reliable use of the large-scale, high-load and long-life maintainable sun-pointing drive mechanism, a method from launch to on-orbit operation is provided. The specific steps are as follows:

[0130] First step, during the launch stage, both the external load-bearing link and the internal load-bearing link are in the connected state, and the working mode of the slewing bearing device 5 is set to the locking support braking mode. At this time, the strap locking and releasing assembly 4 is in the locked state, and the switching locking assemblies on the truss side and the cabin side of the slewing bearing device 5 are both in the state of clamping and locking the guide rails.

[0131] Second step, after entering orbit, first the load-bearing mode switches from being simultaneously borne by the external load-bearing link and the internal load-bearing link to being borne only by the internal load-bearing link. At this time, the explosive bolts detonate, and the strap locking and releasing assembly 4 is in the unlocked state.

[0132] In the third step, the working mode of the slewing bearing device 5 is switched from the locking support braking mode to the main slewing bearing mode. At this time, the truss side switching and locking assembly of the slewing bearing device 5 remains in the state of clamping and locking the guide rail, and the cabin side switching and locking assemblies are all disengaged from the contact guide rail state.

[0133] In the fourth step, the clutch of the first drive locking assembly 710 is energized and attracted, realizing the connection of the first drive link. At this time, the first drive locking assembly 710 is in the state of clutch attraction and brake disconnection.

[0134] In the fifth step, the motor driving the first drive locking assembly 710 rotates. Through the transmission chain (gear 74 - internal tooth ring structure 525 of the guide rail), finally drive the truss interface flange 3 to rotate together with the external load, realizing the on-orbit operation of the sun-pointing drive mechanism.

[0135] Among them, the above five steps describe the process of the large-scale, high-load, long-life and maintainable sun-pointing drive mechanism from launch to operation. During the operation process, braking is also required according to mission requirements, and different braking modes are selected and implemented.

[0136] If the locking support braking mode is selected and implemented, the specific steps are as follows:

[0137] In the first step, the motor driving the first drive locking assembly 710 stops rotating. Through the transmission chain, finally drive the truss interface flange together with the external load to stop rotating, realizing the overall stop of the sun-pointing drive mechanism.

[0138] In the second step, the first drive locking assembly 710 is set to the drive link disconnection mode, that is, the clutch is disconnected;

[0139] In the third step, the slewing bearing device 5 is switched from the main slewing bearing mode to the locking support braking mode, realizing the overall braking of the sun-pointing drive mechanism.

[0140] If the drive link braking mode is selected and implemented, the specific steps are as follows:

[0141] In the first step, the motor driving the first drive locking assembly 710 stops rotating. Through the transmission chain, finally drive the truss interface flange together with the external load to stop rotating, realizing the overall stop of the sun-pointing drive mechanism.

[0142] In the second step, the first drive locking assembly 710 is set to the drive link braking mode, that is, the clutch maintains the attracted state unchanged, and the attracted brake is used to realize the overall braking of the sun-pointing drive mechanism;

[0143] The process of the large-scale, high-load, long-life and maintainable sun-pointing drive mechanism switching from the braking mode to the on-orbit operation mode is the reverse process of the above process, which will not be elaborated here.

[0144] The present invention has been described in detail in conjunction with specific embodiments and exemplary examples. However, these descriptions should not be construed as limiting the present invention. Those skilled in the art understand that without departing from the spirit and scope of the present invention, various equivalent substitutions, modifications or improvements can be made to the technical solutions of the present invention and their implementation manners, and these all fall within the scope of the present invention. The protection scope of the present invention shall be subject to the appended claims.

[0145] The content not described in detail in the specification of the present invention belongs to the well-known technology of those skilled in the art.

Claims

1. A large-scale, high-load, long-life, maintainable sun-directing drive mechanism, characterized in that: Comprising: A composite material main structure (1), a cabin interface flange (2), a truss interface flange (3), a strap locking and releasing assembly (4), a slewing bearing device (5) and a drive locking assembly (7); The composite material main structure (1) is connected to the cabin interface flange (2) and is used to support the truss interface flange (3) during the launch stage; The cabin interface flange (2) provides a spacecraft cabin connection interface; The truss interface flange (3) provides an extravehicular load connection interface; The strap locking and releasing assembly (4) clamps the composite material main structure (1) and the truss interface flange (3) during the launch stage and releases the composite material main structure (1) and the truss interface flange (3) during the on-orbit stage; The top of the slewing bearing device (5) is connected to the truss interface flange (3), and the bottom is connected to the cabin interface flange (2). It is used to lock and support the truss interface flange (3) during the launch stage and the on-orbit stage, and provides a slewing freedom degree for the truss interface flange (3) during the on-orbit stage; The drive locking assembly (7) is installed on the cabin interface flange (2) or the truss interface flange (3) and is used as a power source to cooperate with the slewing bearing device (5) to drive the truss interface flange (3) to rotate; The strap locking and releasing assembly (4) includes at least two straps (41), a plurality of clamping blocks (42), a plurality of explosive bolts (43) and multiple sets of collecting assemblies (44). The clamping blocks (42) are circumferentially distributed evenly and fit the outer circumferential surfaces and the upper and lower sides of the truss interface flange (3) and the composite material main structure (1) to clamp the truss interface flange (3) and the composite material main structure (1); The straps (41) wrap around all the clamping blocks (42) and are connected end to end through the explosive bolts (43); The collecting assemblies (44) are installed on the truss interface flange (3), and each collecting assembly (44) extends a rope to fix the strap (41) and is used to pull and lift the strap (41) after the explosive bolts (43) detonate; The collection component (44) includes a coil spring component (441), a first roller component (442), a buffer component (443), a rope component (444), a limit bracket (445), a rope clamp (446), a sliding plate (447), and a support seat (448); the coil spring component (441) is installed on the support seat (448) and is connected to one end of the rope of the rope component (444) for providing a pre-tightening moment and tensile force; the limit bracket (445) is installed on the coil spring component (441); the first roller component (442) and the buffer component (443) are respectively installed on the upper and lower sides of the limit bracket (445). The axis of the first roller component (442) is perpendicular to the rope to guide the rope, and the buffer component (443) is used to buffer the impact of the rope clamp (446) and the sliding plate (447) after the strip (41) is tightened; the rope clamp (446) is located at the upper end of the sliding plate (447) and is fixedly connected to the sliding plate (447) on the clamping block (42). The rope clamp (446) and the sliding plate (447) are provided with rope grooves along the set rope running direction for guiding the rope after the first roller component (442); a strip hole allowing the strip (41) to pass through is formed between the sliding plate (447) and the clamping block (42) and is fixed by circumferential binding of the strip (41). Lugs are machined on the outer side of the sliding plate (447). After the other end of the rope passes through the coil spring component (441), it passes through the first roller component (442) and the rope grooves formed on the rope clamp (446) and the sliding plate (447) and is then connected to the lug of the sliding plate (447).

2. The large-scale, high-load, long-life, maintainable sun-directing drive mechanism according to claim 1 is characterized in that: The composite material main structure (1) is a conical cylinder section structure, and its large end is fixedly connected to the cabin interface flange (2), and its small end is connected to the truss interface flange (3) through a strap locking and releasing component (4) during the launch section, serving as the prototype of the entire sun-pointing drive mechanism; during the on-orbit section, it is disconnected from the truss interface flange (3) and no longer supports the truss interface flange (3).

3. The large-scale, high-load, long-life, maintainable sun-directing drive mechanism according to claim 1 is characterized in that: The clamping block (42) is a W-shaped clamping block, and two grooves respectively mating with the outer circular surface of the truss interface flange (3) and the composite material main structure (1) are provided on the inner side. The protrusion formed between the two grooves is embedded in the gap between the outer circular surfaces of the truss interface flange (3) and the composite material main structure (1).

4. The large-scale, high-load, long-life, maintainable sun-directing drive mechanism according to claim 1 is characterized in that: The coiled spring assembly (441) includes a housing (4411), a volute spring (4412), a coiled spring cylinder (4413), a rotating shaft (4414), a wire rope drum (4415), a bearing (4416), a support structure (4417) and an end cover (4418); the housing (4411) is used to provide an accommodation space; the volute spring (4412) is placed inside the coiled spring cylinder (4413), the outer side of the volute spring (4412) is connected to the coiled spring cylinder (4413), and the inner side is connected to the rotating shaft (4414). Rotating the coiled spring cylinder (4413) applies an initial pre-tightening torque to the volute spring (4412); the wire rope drum (4415) is connected to the rotating shaft (4414) and rotates with the rotating shaft (4414); the bearing (4416) is sleeved on the rotating shaft (4414), and is limited in the housing (4411) through the end cover (4418) and the support structure (4417).

5. The large-scale, high-load, long-life, maintainable sun-directing drive mechanism according to claim 1 is characterized in that: The first roller assembly (442) includes a first roller (4421), a roller bracket (4422) and a roller shaft (4423); the first roller (4421) and the roller shaft (4423) can rotate relative to each other and are used to change the wire rope direction; a U-shaped groove structure is formed in the circumferential direction of the first roller (4421), with a groove in the middle and shoulders at both ends, so that the wire rope passes through the roller assembly and is always in the U-shaped groove.

6. The large-scale, high-load, long-life, maintainable sun-directing drive mechanism according to claim 1 is characterized in that: The slewing support device (5) includes multiple sets of switching and locking components (51), a guide rail (52), multiple sets of main slewing support components (53) and multiple sets of standby slewing support components (54); the main slewing support components (53) are installed on the cabin interface flange (2), and the standby slewing support components (54) are installed on the truss interface flange (3), both are circumferentially and evenly distributed; both ends of the guide rail (52) are respectively clamped between the main slewing support components (53) and the standby slewing support components (54); part of the switching and locking components are installed on the cabin interface flange (2), and part are installed on the truss interface flange (3), radially symmetrically arranged, and can all clamp the inner and outer sides of the guide rail (52).

7. The large-scale, high-load, long-life, maintainable sun-directing drive mechanism according to claim 6 is characterized in that: The guide rail (52) is a circular ring structure, and the cross-sections at the upper and lower ends are symmetric triangular structures, which are divided into an inner inclined surface (521), an outer inclined surface (522) and an end surface (523). There is a straight transition section (524) between the inner inclined surface (521) and the end surface (523). An internal gear ring structure (525) is arranged on the straight transition section (524), which is the driving torque input interface of the driving and locking component (7); the middle cross-section of the guide rail (52) is a regular rectangle, which is divided into an inner side surface (526) and an outer side surface (527).

8. The large-scale, high-load, long-life, maintainable sun-directing drive mechanism according to claim 6 is characterized in that: Both the main slewing support component (53) and the standby slewing support component (54) include a clamping part and a mounting part (534). The clamping parts of the two are of the same structure and are used to clamp both ends of the guide rail (52). The mounting parts (534) are respectively fixedly connected to the cabin interface flange (2) or the truss interface flange (3).

9. The large-scale, high-load, long-life, maintainable sun-directing drive mechanism according to claim 8 is characterized in that: The clamping part includes a main clamping arm (531), a secondary clamping arm (532) and a bottom clamping arm (533). The bottom clamping arm (533) is directly mounted on the mounting part (534). The main clamping arm (531) and the secondary clamping arm (532) are respectively connected to the mounting part (534) through a pin shaft (535) and can rotate around the axis. The main clamping arm (531) and the secondary clamping arm (532) are connected by a clamping bolt (536). Each clamping arm is provided with a freely rotatable second roller assembly (537), and a freely rotatable second roller (538) is arranged inside the second roller assembly (537). The main clamping arm (531), the secondary clamping arm (532) and the bottom clamping arm (533) respectively correspond to the outer inclined surface (522), the inner inclined surface (521) and the end surface (523) of the guide rail. By tightening the clamping bolt, the outer ring surfaces of the rollers of the main clamping arm, the secondary clamping arm and the bottom clamping arm can respectively fit the outer inclined surface, the inner inclined surface and the end surface at one end of the guide rail to form a stable clamping state. Loosen and disconnect the clamping bolt from the secondary clamping arm, and the secondary clamping arm can rotate around the pin shaft to make the clamping part in an open state.

10. The large-scale, high-load, long-life, maintainable sun-directing drive mechanism according to claim 6, characterized in that: The switching and locking assembly (51) includes a main locking arm (511), a secondary locking arm (512), a motor driving part (513) and a main structure part (514). The main structure part (514) provides a mechanical interface for connecting with the cabin interface flange (2) and the truss interface flange (3). The main locking arm (511) and the secondary locking arm (512) are connected to the main structure part (514) through a rotating support shaft (515) and can rotate around the rotating support shaft. A locking piece (516) is installed at the end of each of the main locking arm (511) and the secondary locking arm (512), and the locking pieces (516) respectively fit or separate from the outer side surface (527) and the inner side surface (526) of the middle section of the guide rail (52). The motor driving part (513) is mounted on the main structure part (514) and is connected with the main locking arm (511) and the secondary locking arm (512) to form a linkage mechanism. The action of the motor driving part (513) can drive the main locking arm (511) and the secondary locking arm (512) to lock or unlock the guide rail (52) together.

11. The large-scale, high-load, long-life, maintainable sun-directing drive mechanism according to claim 6 is characterized in that: The slewing bearing device has three working modes. When the guide rail (52) can only rotate relative to the main slewing bearing assembly (53) on the cabin side, it is the main slewing bearing mode. When the guide rail (52) can only rotate relative to the standby slewing bearing assembly (54) on the truss side, it is the standby slewing bearing mode. When the guide rail (52) cannot rotate relative to both sides of the slewing bearing assemblies, it is the locking support braking mode. In the main slewing bearing mode, the truss side switching and locking assembly (51) clamps and locks the guide rail (52), the cabin side switching and locking assembly (51) disengages from the guide rail, the guide rail (52) rotates freely inside the main slewing bearing assembly (53) on the cabin side, and the standby slewing bearing assembly (54) on the truss side remains relatively stationary with the guide rail (52). In the standby slewing bearing mode, the truss-side switching locking component (51) disengages from the contact guide rail, the cabin-side switching locking component (51) clamps and locks the guide rail, the guide rail (52) rotates relative to the truss-side standby slewing bearing component (54), and the cabin-side main slewing bearing component (53) remains relatively stationary with respect to the guide rail (52). In the locking support braking mode, both the truss-side switching locking component and the cabin-side switching locking component clamp and lock the guide rail. The guide rail (52) cannot rotate freely within the truss-side standby slewing bearing component (54) and the cabin-side main slewing bearing component (53), and the three remain relatively stationary.

12. The large-scale, high-load, long-life, maintainable sun-directing drive mechanism according to claim 7, characterized in that: The drive locking component (7) includes a motor (71), a clutch (72), a brake (73), a gear (74), and a reducer (75). The brake (73) performs braking control on the motor (71). The output shaft of the motor (71) is connected to the input shaft of the reducer (75). The output shaft of the reducer (75) is connected to the input flange of the clutch (72). The output flange of the clutch (72) is connected to the gear (74) through the output shaft of the drive locking component (7). The gear (74) meshes with the internal gear ring structure (525) of the guide rail (52) to output torque, serving as the driving torque output interface of the drive locking component (7), and the motor (71) serves as the drive source.

13. The large-scale, high-load, long-life, maintainable sun-directing drive mechanism according to claim 12, characterized in that: There are three sets of the drive locking component (7), namely the first drive locking component (710), the second drive locking component (720), and the third drive locking component (730). The first drive locking component (710) and the second drive locking component (720) are installed on the cabin interface flange (2), and the third drive locking component (730) is installed on the truss interface flange (3), and they are used in cooperation with the slewing bearing device (5) as the power source.

14. The large-scale, high-load, long-life, maintainable sun-directing drive mechanism according to claim 12, characterized in that: The drive locking component (7) has three working modes. Among them, when the clutch (72) is engaged and the brake (73) is disengaged, it is the drive link connected mode. When the clutch (72) is disengaged, it is the drive link disconnected mode. When both the clutch (72) and the brake (73) are engaged, it is the drive link braking mode.

15. The large-scale, high-load, long-life, maintainable sun-directing drive mechanism according to claim 1 is characterized in that: The sun-pointing drive mechanism further includes a slip ring electrical transmission device (6). The rotor in the slip ring electrical transmission device (6) is fixedly connected to the truss interface flange (3), and the power cable and signal cable at the truss end are connected. The housing of the slip ring electrical transmission device (6) is fixedly connected to the cabin interface flange (2) as the stator. Power and signal transmission are formed between the stator and the rotor, and the power cable and signal cable are led out from the stator to the cabin.

16. The large-scale, high-load, long-life, maintainable sun-directing drive mechanism according to claim 15, characterized in that: The slip ring electrical transmission device (6) includes a slip ring module (61) and a rotary joint module (62). Among them, the slip ring module (61) is used to transmit the electrical energy generated by the solar panels outside the cabin into the cabin, and the rotary joint module (62) is used for signal transmission and interaction between the equipment inside and outside the cabin. The stator of the slip ring module (61) is connected to the stator of the rotary joint module (62) to form the stator of the slip ring electrical transmission device (6). The rotor of the slip ring module (61) is connected to the rotor of the rotary joint module (62) to form the rotor of the slip ring electrical transmission device (6).

17. The large-scale, high-load, long-life, maintainable sun-directing drive mechanism according to claim 16 is characterized in that: An upper mounting flange (611) is arranged around the upper end of the rolling ring module (61), and a lower mounting flange (621) is arranged around the lower end of the slip ring module (62). Opposite conical cylinder sections are arranged on the upper and lower sides of the cabin interface flange (2). The large ends of the two conical cylinder sections are fixed on the cabin interface flange (2), and interface flanges are formed at the small ends, which are respectively connected to the upper mounting flange (611) and the lower mounting flange (621).

18. The large-scale, high-load, long-life, maintainable sun-directing drive mechanism according to claim 1 is characterized in that: The sun-directed driving mechanism further comprises an on-track oil replenishing assembly (8), which is mounted on the cabin interface flange (2) to provide lubrication for the guide rail of the slewing support device (5).

19. The large-scale, high-load, long-life, maintainable sun-directing drive mechanism according to claim 18 is characterized in that: The on-track oil replenishment assembly (8) comprises an oiling module (81), an oil pipeline module (82), an operating hand wheel module (83), a transmission module (84), an oil storage module (85), a clamping module (86) and a base (87); the operating hand wheel module (83), the transmission module (84), the oil storage module (85) and the clamping module (86) are respectively mounted on the base (87); the oil storage module (85) is connected to the oiling module (81) via the oil pipeline module (82); the oiling module (81) is mounted on the base (87) via the clamping module (86); the operating hand wheel module (83) is connected to the clamping module (86) via the transmission module (84); The oil storage module (85) is used to store lubricating oil and provide oil supply pressure to supply oil to the oiling module (81); the oil pipeline module (82) is used to transport the lubricating oil stored in the oil storage module (85) to the oiling module (81); the oiling module (81) is used to evenly apply the lubricating oil to the contact interface of the spacecraft movable parts under the action of the clamping module (86) to compensate for the long-term evaporation loss of the lubricating oil on the contact interface in orbit; the transmission module (84) is used to drive the clamping module (86) to control the oiling module (81) under the operation of the operating hand wheel module (83); the operating hand wheel module (83) is used to respond to the astronaut's on-orbit operation and provide power input; the clamping module (86) is used to control the opening / closing of the oil storage module (85) and the clamping / disengagement of the oiling module (81) under the drive of the transmission module (84).

20. The large-scale, high-load, long-life, maintainable sun-directing drive mechanism according to claim 1, characterized in that: The composite material main structure (1) in the sun-directed driving mechanism is connected to the cabin interface flange (2); the wrapping belt locking and releasing assembly (4) clamps the composite material main structure (1) and the truss interface flange (3); external loads can be transmitted from the truss interface flange (3) through the wrapping belt locking and releasing assembly (4), the composite material main structure (1), and the cabin interface flange (2) to the cabin, thereby forming an external load-bearing link; the slewing support device (5) is connected to the truss interface flange (3) at the top and to the cabin interface flange (2) at the bottom; external loads can be transmitted from the truss interface flange (3) through the slewing support device (5) and the cabin interface flange (2) to the cabin, thereby forming an internal load-bearing link; the external load-bearing link and the internal load-bearing link together constitute a launch segment load-bearing link; and the internal load-bearing link serves as an on-orbit segment load-bearing link.

21. The large-scale, high-load, long-life, maintainable sun-directing drive mechanism according to claim 13, characterized in that: The sun-directed driving mechanism comprises three driving links, wherein a first driving locking assembly (710) and a main slewing support mode of a slewing support device (5) constitute a first driving link, a second driving locking assembly (720) and a main slewing support mode of a slewing support device (5) constitute a second driving link, and a third driving locking assembly (730) and a backup slewing support mode of a slewing support device (5) constitute a third driving link.

22. The large-scale, high-load, long-life, maintainable sun-directing drive mechanism according to claim 1, characterized in that: The sun-directed driving mechanism includes two braking modes: locking support braking and driving link braking. The locking support braking mode has a braking capacity better than 510Nm, and the driving link braking mode has a braking capacity better than 290Nm.

23. An operating method of the large-scale, high-load, long-life, maintainable sun-directing drive mechanism according to any one of claims 1 to 22, characterized in that: The steps include: During the launch phase, the composite material main structure (1) is connected to the cabin interface flange (2), the strap locking and releasing assembly (4) clamps the composite material main structure (1) and the truss interface flange (3), the top of the slewing support device (5) is locked and connected to the truss interface flange (3), and the bottom of the slewing support device (5) is locked and connected to the cabin interface flange (2), the external load-bearing link and the internal load-bearing link are both in the connected state, and the slewing support device (5) is in the locking support braking mode; After entering the orbit, the wrapping belt locking release assembly (4) releases the composite material main structure (1) and the truss interface flange (3), and the load-bearing mode is switched from the external load-bearing link and the internal load-bearing link carrying at the same time to the internal load-bearing link carrying only; The top of the slewing support device (5) is maintained in a locked connection with the truss interface flange (3) and the bottom is rotationally connected with the cabin interface flange (2), or the top of the slewing support device (5) is rotationally connected with the truss interface flange (3) and the bottom is maintained in a locked connection with the cabin interface flange (2), so that the working mode of the slewing support device (5) is switched from the locking support braking mode to the main slewing support mode or the standby slewing support mode; The motor driving the locking assembly (7) rotates, and finally drives the truss interface flange (3) to rotate together with the external load through the transmission chain, thereby realizing the on-orbit operation of the sun-directed driving mechanism.

24. The operating method of the large-scale, high-load, long-life, maintainable sun-directing drive mechanism according to claim 23, characterized in that: When running on track, if the locking support braking mode is selected and implemented, it is implemented in the following ways: The motor driving the locking assembly stops rotating, and through the transmission chain, the driving truss interface flange and the external load stop rotating together, so that the entire sun-directed driving mechanism stops rotating; The clutch in the drive lock assembly is disengaged and set to a drive link disconnect mode; The slewing support device switches from the main slewing support mode or the standby slewing support mode to the locking support braking mode, thereby achieving the braking of the entire sun-directed drive mechanism.

25. The operating method of the large-scale, high-load, long-life, maintainable sun-directing drive mechanism according to claim 23, characterized in that: When running on track, if the drive link braking mode is selected and implemented, it is implemented in the following way: The motor driving the locking assembly stops rotating, and through the transmission chain, the driving truss interface flange and the external load stop rotating together, so that the entire sun-directed driving mechanism stops rotating; The clutch arranged in the driving locking assembly maintains the engaged state unchanged, and the brake is engaged to form a driving chain braking mode, thereby achieving braking of the entire sun-directing driving mechanism.

26. The operating method of the large-scale, high-load, long-life, maintainable sun-directing drive mechanism according to claim 23, characterized in that: The working modes of the slewing bearing device can be automatically switched between the locking support braking mode and the main slewing bearing mode by the following method: the switching and locking assembly on the truss side does not operate and still maintains the state of clamping and locking the guide rail, while the switching and locking assembly on the cabin side operates and adjusts from the state of clamping and locking the guide rail to the state of disengaging from the guide rail; the process of switching from the main slewing bearing mode to the locking support braking mode is the reverse of the above process; and / or The working mode of the slewing bearing device is switched from the locking support braking mode to the standby slewing bearing mode by the following method: the switching and locking assembly on the cabin side does not operate and still maintains the state of clamping and locking the guide rail, while the switching and locking assembly on the truss side operates and adjusts from the state of clamping and locking the guide rail to the state of disengaging from the guide rail; the process of switching from the standby slewing bearing mode to the locking support braking mode is the reverse of the above process; and / or The working mode of the slewing bearing device is switched from the main slewing bearing mode to the standby slewing bearing mode by the following method: first, it needs to be switched from the main slewing bearing mode to the locking support braking mode, and then from the locking support braking mode to the standby slewing bearing mode, and the switching and locking assembly operates according to the corresponding mode switching; the process of switching from the standby slewing bearing mode to the main slewing bearing mode is the reverse of the above process.

27. The operating method of the large-scale, high-load, long-life, maintainable sun-directing drive mechanism according to claim 23, characterized in that: The drive link of the sun-pointing drive mechanism can be automatically switched. When it is first switched from the locking support braking mode to the first drive link after entering orbit, it is implemented by the following method: first, the working mode of the slewing bearing device is switched from the locking support braking mode to the main slewing bearing mode, and then the clutch of the first drive locking assembly is powered on and attracted to realize the connection of the first drive link; and / or The first drive link is switched to the second drive link by the following method: the working mode of the slewing bearing device remains unchanged in the main slewing bearing mode, the clutch of the first drive locking assembly is powered off and disengaged, and the clutch of the second drive locking assembly is powered on and attracted to realize the disconnection of the first drive link and the connection of the second drive link; and / or The first drive link or the second drive link is switched to the third drive link by the following method: first, the clutch of the first drive locking assembly or the second drive locking assembly is powered off and disengaged to realize the disconnection of the first drive link or the second drive link; then the working mode of the slewing bearing device is switched from the main slewing bearing mode to the standby slewing bearing mode; finally, the clutch of the third drive locking assembly is powered on and attracted to realize the connection of the third drive link.

28. The operating method of the large-scale, high-load, long-life, maintainable sun-directing drive mechanism according to claim 23, characterized in that: The in-orbit oil replenishment and maintenance of the sun-pointing drive mechanism is implemented by the following method: The working mode of the slewing bearing device is set to the main slewing bearing mode, the working mode of the drive locking assembly is set to the drive link braking mode, and the sun-pointing drive mechanism stops rotating; The astronaut walks outside the cabin to above the in-orbit oil replenishment component and manually rotates the operating handwheel of the in-orbit oil replenishment component counterclockwise for one week, and then the astronaut walks outside the cabin to the safe area. At this time, the three oil wiping modules of the in-orbit oil replenishment component clamp the three guide rail surfaces, and the three oil delivery pipeline modules start to deliver lubricating oil to the oil wiping modules, and the oil replenishment starts; The drive locking assembly switches from the drive link braking mode to the drive link connection mode and drives the sun-pointing drive mechanism to rotate. At this time, the cabin side guide rail surface of the slewing bearing device slides within the oiling module of the on-orbit oil replenishment assembly, and the lubricating oil continuously transfers from the oiling module of the on-orbit oil replenishment assembly to the guide rail surface, realizing on-orbit oil replenishment maintenance; After the on-orbit oil replenishment amount is sufficient, the drive locking assembly stops driving the sun-pointing drive mechanism to rotate and switches from the drive link connection mode to the drive link braking mode; the astronaut walks out of the cabin again to above the on-orbit oil replenishment assembly and manually rotates the operation handwheel of the on-orbit oil replenishment assembly clockwise for one week. At this time, the oiling module of the on-orbit oil replenishment assembly disengages from the guide rail surface, and the three oil delivery pipeline modules stop delivering lubricating oil to the oiling module. The astronaut returns to the cabin, and the on-orbit oil replenishment maintenance task ends.

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