Rigid-flexible automatic switching pressing and releasing device and assembling and using method thereof

Abstract

The invention provides a pressing and releasing device with rigidity and flexibility automatically switched and an assembling and using method of the pressing and releasing device, and belongs to the technical field of space product structure and mechanism design. The problem that in the prior art, pressing rigidity and unlocking clamping stagnation prevention are difficult to consider at the same time is solved. A pressing and releasing device is arranged at each pressing point of the solar wing base plate, each pressing and releasing device comprises a longitudinal pressing combination and a transverse reinforcing combination, each longitudinal pressing combination comprises a fixed base, a plurality of pressing sleeves, a pull rope, a fixed upper cover and a heat knife assembly, the fixed base is connected to the cabin plate, and the pull rope is connected to the fixed upper cover. The multiple pressing sleeves are stacked on the fixed base in the vertical direction, the pressing sleeves are embedded in the pressing points of the solar wing base plate of each fold, the fixed upper cover is connected to the solar wing base plate on the topmost layer, the bottom of the pull rope is connected to the fixed base, the top of the pull rope is connected to the fixed upper cover, and the hot knife assembly makes contact with the pull rope. The device is mainly used for compressing and releasing the solar wing.

Description

Technical Field

[0001] This invention belongs to the field of space product structure and mechanism design technology, and in particular relates to a pressure release device with automatic rigid-flexible switching and its assembly and usage method. Background Technology

[0002] The clamping and release mechanism has a wide range of applications in the aerospace field, including the folding and unfolding of solar panels. The process is as follows: During the satellite launch and ascent phase, the solar panels are fixed to the satellite surface through multiple clamping and release mechanisms, and the clamping effect achieves the anti-mechanical purpose of the solar panels; after the satellite enters orbit, the solar panels are released by unlocking all mechanisms, thereby achieving the purpose of on-orbit unfolding.

[0003] Currently, there are two main types of clamping and release mechanisms commonly used in solar panels: rigid clamping and release mechanisms and flexible clamping and release mechanisms.

[0004] The rigid clamping and release mechanism works by using a clamping rod that passes through the clamping holes of all solar panel substrates. The top of the rod is then fixed to the top solar panel substrate, and the bottom is fixed to the satellite module. A certain clamping force is applied to lock the solar panels in place. Once locked, the rigid clamping and release mechanism provides strong longitudinal fixation to the solar panels, effectively suppressing longitudinal vibration. Simultaneously, its lateral fixation is achieved through the rigidity of the clamping rod itself and the friction between the solar panels after clamping, which can suppress lateral vibration to a certain extent.

[0005] The rigid clamping release mechanism works as follows: after the satellite enters orbit, the clamping rod is broken by pyrotechnics or by energizing the shape memory alloy to unlock and release the clamping rod, thereby enabling the solar array to deploy. After unlocking, each solar array fold must separate from the clamping rod sequentially from beginning to end. Since there are multiple clamping points during the solar array locking process, and it is difficult to ensure complete synchronization of unlocking at each clamping point, and disturbances to the satellite itself may also cause asynchronous solar array deployment, there is a risk of the solar array getting stuck with the rigid clamping rod. The more folds of the solar array, the longer the clamping rod, and the greater the risk of sticking; the greater the clamping stiffness required for the solar array, the thicker the clamping rod, and the greater the risk of sticking.

[0006] The clamping method of the flexible clamping release mechanism is similar to that of the rigid clamping release mechanism, the difference being that it uses a flexible rope to pass through the solar array and complete the fixation. After locking, the flexible clamping release mechanism also has a strong fixing effect on the longitudinal direction of the solar array, which can effectively suppress the longitudinal vibration of the solar array; however, since the flexible rope does not have lateral stiffness, the lateral fixation of the solar array can only be achieved through friction after clamping, and the flexible clamping release mechanism has a poor effect on suppressing the lateral vibration of the solar array.

[0007] The flexible clamping release mechanism releases the solar panels by using a hot knife to melt the cable after the satellite enters orbit. Even if the solar panel clamping points unlock asynchronously or the solar panels deploy asynchronously after unlocking, the flexible cable's deformable nature prevents jamming.

[0008] In summary, there is a design contradiction in the clamping and release mechanism used for multi-fold solar arrays: high clamping stiffness results in strong mechanical resistance during launch and ascent, but also increases the risk of release jamming during orbit insertion; conversely, low clamping stiffness can prevent release jamming during orbit insertion, but weakens the mechanical resistance during ascent. Summary of the Invention

[0009] In view of this, the present invention aims to propose a clamping and releasing device with autonomous switching between rigidity and flexibility, as well as its assembly and usage method, to solve the problem that it is difficult to balance clamping rigidity and unlocking anti-jamming in existing devices.

[0010] To achieve the above objectives, the present invention adopts the following technical solution: a pressure release device with automatic switching between rigidity and flexibility, wherein each pressure point of the solar panel substrate is provided with a pressure release device, and the pressure release device comprises a longitudinal pressure assembly and a transverse reinforcement assembly. The longitudinal pressure assembly includes a fixed base, a pressure sleeve, a tension rope, a fixed top cover, and a hot knife assembly. The fixed base is connected to the cabin plate. Multiple pressure sleeves are stacked vertically on the fixed base. A pressure sleeve is embedded in each pressure point of the solar panel substrate. The fixed top cover is connected to the topmost solar panel substrate. The bottom of the tension rope is connected to the fixed base. The top of the tension rope is connected to the fixed cover. The hot knife assembly is in contact with the tension rope. The transverse reinforcement assembly includes a reinforcing bladder and a reservoir bladder. The reinforcing bladder is connected to the reservoir bladder through a conduit to form a sealed cavity. A non-Newtonian fluid is disposed in the sealed cavity. The reinforcing bladder is disposed on the fixed base. The compression sleeve is sleeved on the outside of the reinforcing bladder. The reinforcing bladder is a hollow cylindrical structure. A rope hole is opened in the center of the reinforcing bladder. The tension rope passes through the rope hole. The reinforcing bladder is made of elastic material. The reservoir bladder is a hollow corrugated cylindrical structure. The solar panel substrates are connected by inter-plate hinges. The bottom solar panel substrate is connected to the cabin plate by a root hinge.

[0011] Furthermore, the fixed base is provided with an upper cavity, a lower cavity, a conduit groove, and a mounting flange. The reinforcing bladder is disposed in the upper cavity, the lower cavity is connected to the bottom of the tension rope, a conduit passes through the conduit groove, and the mounting flange is connected to the cabin plate.

[0012] Furthermore, the clamping sleeve has a ring structure, with two clamping sleeves fastened together from both sides of the solar panel substrate into the through hole of the clamping point. The clamping sleeve includes a fixing ring and a contact ring. The contact ring is connected to one side of the end of the fixing ring. The fixing ring is embedded in the clamping point of the solar panel substrate, and the contact ring is close to the surface of the solar panel substrate.

[0013] Furthermore, the two ends of the tension rope are respectively provided with an internal hexagonal external thread structure and a planar limiting structure. The internal hexagonal external thread structure is pressed and connected to the fixed upper cover by a nut, and the planar limiting structure is connected to the fixed base. The tension rope is a Dyneema fiber rope.

[0014] Furthermore, the fixed top cover is provided with a hot knife groove, the tension rope is located in the hot knife groove, the hot knife assembly includes a hot knife, a mounting housing and a spring, the hot knife is connected to a power supply line, the hot knife is inserted into the hot knife groove, one end of the spring is connected to the hot knife, and the other end is connected to the inner bottom surface of the mounting housing, and the mounting housing is connected to the fixed top cover.

[0015] Furthermore, the catheter is divided into two sections, one connected to the reinforcing bladder and the other connected to the reservoir bladder, with the two sections connected by a quick connector.

[0016] Furthermore, there are two reservoirs, which are symmetrically arranged on both sides of the reinforcing bladder.

[0017] Furthermore, the reinforcing bladder is made of high tear-resistant silicone rubber, the reservoir bladder is made of polyimide membrane, the conduit is made of polytetrafluoroethylene tube, and the non-Newtonian fluid is a shear-thickening fluid.

[0018] The present invention also provides an assembly method for a clamping and releasing device that can autonomously switch between rigidity and flexibility, which includes the following steps: Step 1: After evacuating the air from the reinforcing bladder and the reservoir bladder, inject a non-Newtonian fluid. At this time, the outer diameter of the reinforcing bladder is smaller than the inner diameter of the compression sleeve, and the diameter of the rope hole is larger than the outer diameter of the tension rope. The reservoir bladder exhibits an axially elongated expansion state. Step 2: Connect the tension rope to the fixed base, and then use screws to connect the fixed base to the surface of the satellite's cabin. Step 3: Thread the tension rope through the rope hole, place the reinforcing bladder on the fixed base, and attach the liquid storage bladder to the surface of the satellite's cabin. Step 4: Connect and fold the individual solar panel substrates using the inter-plate hinges. After hoisting them above the fixed base, begin the descent. Insert the tension rope and reinforcing bladder into the compression sleeve until the bottom solar panel substrate contacts the top of the reservoir bladder. Under the compression of the solar panel substrate, the non-Newtonian fluid in the reservoir bladder is pumped into the reinforcing bladder. When the compression sleeve of the bottom solar panel substrate contacts the fixed base, the solar panel falls into place, the reservoir bladder is compressed to its minimum axial state, the non-Newtonian fluid is pumped into the reinforcing bladder, causing the reinforcing bladder to expand in volume. The outer diameter of the reinforcing bladder becomes thicker and contacts the inner wall of the compression sleeve, the diameter of the rope hole becomes thinner and contacts the tension rope, and the length of the reinforcing bladder extends upward. Step 5: Thread the tension rope into the fixed top cover, control the tension of the tension rope to make the tension of all clamping points consistent, install the hot knife assembly, and make the hot knife assembly contact the tension rope; Step 6: Use the root hinge to secure the bottom solar panel substrate to the surface of the cabin.

[0019] This invention also provides a method for using a pressure release device with autonomous switching between rigidity and flexibility. Specifically, during the launch and ascent phase, the pressure release device is in a pressure state. The longitudinal pressure applied by the tension rope suppresses the longitudinal vibration of the solar array. The liquid reservoir is in close contact with the bottom solar array substrate to further suppress longitudinal vibration. When the solar array vibrates laterally, the non-Newtonian fluid exhibits a rigid state under the shear thickening effect, suppressing the lateral vibration of the solar array. After the satellite enters orbit, the pressure release device receives an unlocking command to release the solar array. At this time, the hot knife assembly melts the tension rope, releasing the solar array. The solar array unfolds under the drive of the deployment mechanism. The non-Newtonian fluid is gradually pumped into the liquid reservoir under the contraction internal stress of the elastic material of the reinforcing bladder. The volume of the reinforcing bladder shrinks, and the reinforcing bladder is no longer in contact with the pressure sleeve. The liquid reservoir begins to elongate axially under the action of the pumped non-Newtonian fluid, assisting in pushing the solar array away from the cabin plate. After each solar array substrate separates from the reinforcing bladder and tension rope, the solar array is fully deployed under the drive of the deployment mechanism.

[0020] Compared with the prior art, the beneficial effects of the present invention are: (1) The clamping and releasing device with automatic switching between rigidity and flexibility described in this invention solves the problem that existing clamping and releasing mechanisms cannot simultaneously achieve both clamping rigidity and unlocking anti-jamming.

[0021] (2) The rigid-flexible self-switching clamping and releasing device of the present invention can provide lateral contact limiting of the solar array through the rigidification of non-Newtonian fluid during the satellite launch phase, which has a better vibration suppression effect than the traditional non-contact friction limiting.

[0022] (3) The rigid-flexible self-switching clamping and releasing device of the present invention can still achieve the unlocking and anti-jamming effect through the flexible deformation of non-Newtonian fluid during the orbit unlocking stage, even if the solar array exhibits severe asynchronous deployment. (4) The clamping and releasing device with automatic switching between rigidity and flexibility described in this invention can overcome the dilemma of relying on friction to suppress lateral vibration by contact-type vibration suppression, thereby reducing the high requirements for clamping force and reducing the stringent requirements for the strength of clamping parts and the difficulty of operation of the clamping and releasing device.

[0023] (5) The clamping and releasing device with automatic switching between rigidity and flexibility described in this invention adopts the hot knife unlocking method, does not use pyrotechnics and shape memory alloys, has low cost, can be reused repeatedly, and is conducive to the development of ground deployment tests; it has small impact, but the ground test environment has no special requirements, and the impact of on-orbit deployment on satellite is small.

[0024] (6) The liquid storage bladder described in this invention can longitudinally support the solar array during the launch phase and play an auxiliary role in suppressing longitudinal vibration. During the orbital unlocking phase, it plays an auxiliary role in deploying the solar array through longitudinal expansion.

[0025] (7) The components of the rigid-flexible self-switching clamping and releasing device described in this invention are independent of each other, and can be redesigned / selected according to the specific needs of the satellite, making the device highly adaptable. Attached Figure Description

[0026] The accompanying drawings, which form part of this invention, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings: Figure 1 This is a schematic diagram of a clamping and releasing device that can autonomously switch between rigidity and flexibility, as described in this invention. Figure 2 This is a schematic cross-sectional view of the longitudinal clamping assembly structure described in this invention; Figure 3 This is a schematic diagram of the transversely reinforced composite structure described in this invention; Figure 4 This is a cross-sectional view of the fixed base structure described in this invention; Figure 5 This is a schematic diagram of the installation method of the clamping sleeve according to the present invention; Figure 6 This is a schematic diagram of the tension rope structure described in this invention; Figure 7 This is a schematic diagram of the fixed top cover structure described in this invention; Figure 8 This is a schematic diagram of the hot knife assembly structure described in this invention; Figure 9 This is a schematic diagram of the cross-sectional structure of the reinforcing cyst described in this invention; Figure 10 This is a schematic diagram of the liquid storage bladder structure described in this invention; Figure 11This is a schematic diagram of the assembly process of the clamping and releasing device with automatic rigid-flexible switching as described in this invention. Figure 1 ; Figure 12 This is a schematic diagram of the assembly process of the clamping and releasing device with automatic rigid-flexible switching as described in this invention. Figure 2 ; Figure 13 This is a schematic diagram of the assembly process of the clamping and releasing device with automatic rigid-flexible switching as described in this invention. Figure 3 ; Figure 14 This is a schematic diagram of the assembly process of the clamping and releasing device with automatic rigid-flexible switching as described in this invention. Figure 4 ; Figure 15 This is a schematic diagram of the assembly process of the clamping and releasing device with automatic rigid-flexible switching as described in this invention. Figure 5 ; Figure 16 This is a schematic diagram of the assembly process of the clamping and releasing device with automatic rigid-flexible switching as described in this invention. Figure 6 ; Figure 17 This is a schematic diagram of the assembly process of the clamping and releasing device with automatic rigid-flexible switching as described in this invention. Figure 7 ; Figure 18 This is a schematic diagram of the assembly process of the clamping and releasing device with automatic rigid-flexible switching as described in this invention. Figure 8 ; Figure 19 This is a schematic diagram illustrating the working mode of the rigid-flexible autonomous switching clamping and release device described in this invention during the launch ascent phase of a carrier. Figure 20 This is a schematic diagram illustrating the unlocking and release process of the solar array using a rigid-flexible self-switching clamping and release device as described in this invention. Figure 1 ; Figure 21 This is a schematic diagram illustrating the unlocking and release process of the solar array using a rigid-flexible self-switching clamping and release device as described in this invention. Figure 2 ; Figure 22 This is a schematic diagram illustrating the unlocking and release of the solar array in full deployment using a rigid-flexible self-switching clamping and releasing device according to the present invention. Figure 23 This is a schematic diagram illustrating the unlocking and release process of the solar array using a rigid-flexible self-switching clamping and release device as described in this invention. Figure 3 .

[0027] In the picture: 1-Longitudinal clamping assembly, 2-Transverse reinforcement assembly, 3-Fixed base, 4-Clamping sleeve, 5-Tension rope, 6-Fixed top cover, 7-Hot knife assembly, 8-Reinforcing bladder, 9-Reservoir bladder, 10-Conduit, 11-Quick connector, 12-Non-Newtonian fluid, 13-Upper cavity, 14-Lower cavity, 15-Rope hole, 16-Conduit groove, 17-Mounting flange, 18-Fixing ring, 19-Contact ring, 20-Internal hexagonal thread structure, 21-Planar limiting structure, 22-Hot knife groove, 23-Hot knife, 24-Mounting housing, 25-Spring, 26-Power supply line, 27-Bucket plate, 28-Inter-plate hinge, 29-Solar wing base plate, 30-Root hinge. Detailed Implementation

[0028] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. It should be noted that, unless otherwise specified, the embodiments and features in the embodiments of the present invention can be combined with each other, and the described embodiments are only some embodiments of the present invention, not all embodiments.

[0029] See Figure 1-23 This embodiment describes a pressure release device with automatic rigid-flexibility switching. Each pressure point on the solar panel substrate 29 is equipped with a pressure release device. The pressure release device includes a longitudinal pressure assembly 1 and a transverse reinforcement assembly 2. The longitudinal pressure assembly 1 includes a fixed base 3, pressure sleeves 4, tension ropes 5, a fixed top cover 6, and a hot knife assembly 7. The fixed base 3 is connected to the cabin plate 27. Multiple pressure sleeves 4 are stacked vertically on the fixed base 3, with a pressure sleeve 4 embedded in each pressure point of the folded solar panel substrate 29. The fixed top cover 6 is connected to the topmost solar panel substrate 29. The bottom of the tension rope 5 is connected to the fixed base 3, and the top of the tension rope 5 is connected to the fixed base 3. On the fixed cover 6, the hot knife assembly 7 is in contact with the tension rope 5. The transverse reinforcement assembly 2 includes a reinforcement bladder 8 and a liquid storage bladder 9. The reinforcement bladder 8 is connected to the liquid storage bladder 9 through a conduit 10 to form a sealed cavity. A non-Newtonian fluid 12 is disposed in the sealed cavity. The reinforcement bladder 8 is disposed on the fixed base 3. The compression sleeve 4 is sleeved on the outside of the reinforcement bladder 8. The reinforcement bladder 8 is a hollow cylindrical structure. A rope hole 15 is opened in the center of the reinforcement bladder 8. The tension rope 5 passes through the rope hole 15. The reinforcement bladder 8 is made of elastic material. The liquid storage bladder 9 is a hollow corrugated cylindrical structure. The solar panel substrates 29 are connected to each other through inter-plate hinges 28. The bottom solar panel substrate 29 is connected to the cabin plate 27 through a root hinge 30.

[0030] In this embodiment, the fixed base 3 is provided with an upper cavity 13, a lower cavity 14, a conduit groove 16, and a mounting flange 17. The reinforcing bladder 8 is disposed in the upper cavity 13. The lower cavity 14 is connected to the bottom of the tension rope 5. The conduit 10 passes through the conduit groove 16. The mounting flange 17 is connected to the cabin plate 27. The clamping sleeve 4 has an annular structure. Two clamping sleeves 4 are fastened from both sides of the solar panel substrate 29 into the clamping point through hole. The clamping sleeve 4 includes a fixing ring 18 and a contact ring 19. The contact ring 19 is connected to one side of the end of the fixing ring 18. The fixing ring 18 is embedded in the clamping point of the solar panel substrate 29, and the contact ring 19 is close to the surface of the solar panel substrate 29. The tension rope 5 has an internal hexagonal thread structure 20 and a planar limiting structure 21 at both ends. The internal hexagonal thread structure 20 is pressed and connected to the fixed cover 6 by a nut, and the planar limiting structure 21 is connected to the fixed base 3. The tension rope 5 is a Dyneema fiber rope. The fixed cover 6 has a hot knife groove 22, and the tension rope 5 is located in the hot knife groove 22. The hot knife assembly 7 includes a hot knife 23, a mounting housing 24, and a spring 25. The hot knife 23 is connected to the power supply line 26 and is inserted into the hot knife groove 22. One end of the spring 25 is connected to the hot knife 23, and the other end is connected to the inner bottom surface of the mounting housing 24. The mounting housing 24 is connected to the fixed cover 6. The conduit 10 is divided into two sections, one connected to the reinforcing bladder 8 and the other connected to the liquid storage bladder 9. The two sections of the conduit 10 are connected by a quick connector 11. There are two liquid storage bladders 9, which are symmetrically arranged on both sides of the reinforcing bladder 8. The reinforcing bladder 8 is made of high tear-resistant silicone rubber, the reservoir bladder 9 is made of polyimide membrane, the conduit 10 is made of polytetrafluoroethylene tube, and the non-Newtonian fluid 12 is a shear-thickening fluid.

[0031] This embodiment describes an assembly method for a pressure release device that can autonomously switch between rigidity and flexibility, which includes the following steps: Step 1: After evacuating the air from the reinforcing bladder 8 and the reservoir bladder 9, inject non-Newtonian fluid 12. At this time, the outer diameter of the reinforcing bladder 8 is smaller than the inner diameter of the compression sleeve 4, the diameter of the rope hole 15 is larger than the outer diameter of the tension rope 5, and the reservoir bladder 9 exhibits an axially elongated expansion state. Step 2: Connect the tension rope 5 to the fixed base 3, and then use screws to connect the fixed base 3 to the surface of the satellite's cabin panel 27; Step 3: Thread the tension rope 5 through the rope hole 15, place the reinforcing bladder 8 on the fixed base 3, and attach the liquid storage bladder 9 to the surface of the satellite's panel 27. Step 4: Use the inter-plate hinge 28 to connect and fold up each solar panel substrate 29, hoist it above the fixed base 3 and start to fall. Insert the tension rope 5 and the reinforcing bladder 8 into the clamping sleeve 4 until the bottom solar panel substrate 29 contacts the top of the reservoir bladder 9. Under the compression of the solar panel substrate 29, the non-Newtonian fluid 12 in the reservoir bladder 9 is pumped into the reinforcing bladder 8. When the clamping sleeve 4 of the bottom solar panel substrate 29 contacts the fixed base 3, the solar panel falls into place, the reservoir bladder 9 is compressed to the minimum axial state, the non-Newtonian fluid 12 is pumped into the reinforcing bladder 8, causing the reinforcing bladder 8 to expand in volume. The outer diameter of the reinforcing bladder 8 becomes thicker and contacts the inner wall of the clamping sleeve 4, the diameter of the rope hole 15 becomes thinner and contacts the tension rope 5, and the length of the reinforcing bladder 8 extends upward. Step 5: Thread the tension rope 5 into the fixed cover 6, control the clamping force of the tension rope 5 to make the clamping force of all clamping points consistent, install the hot knife assembly 7, and make the hot knife assembly 7 contact the tension rope 5. Step 6: Use the root hinge 30 to fix the bottom solar panel substrate 29 to the surface of the cabin panel 27.

[0032] This embodiment describes the use of a pressure release device that can autonomously switch between rigidity and flexibility. Specifically, during the launch and ascent phase, the pressure release device is in a pressure-pressed state. The longitudinal pressure applied by the tension rope 5 suppresses the longitudinal vibration of the solar array. The liquid reservoir 9 is in close contact with the bottom solar array substrate 29, further suppressing longitudinal vibration. When the solar array vibrates laterally, the non-Newtonian fluid 12 exhibits a rigid state under the shear thickening effect, suppressing the lateral vibration of the solar array. After the satellite enters orbit, the pressure release device receives an unlocking command and releases the solar array. At this time, the hot knife assembly 7 melts the tension rope 5, releasing the solar array. Driven by the deployment mechanism, the solar array unfolds. The non-Newtonian fluid 12 is gradually pumped into the reservoir bladder 9 under the contraction internal stress of the elastic material of the reinforcing bladder 8. The volume of the reinforcing bladder 8 shrinks, and the reinforcing bladder 8 no longer contacts the clamping sleeve 4. The reservoir bladder 9 begins to elongate axially under the action of the pumped non-Newtonian fluid 12, which helps to push the solar array away from the cabin plate 27. After each solar array base plate 29 is separated from the reinforcing bladder 8 and the tension rope 5, the solar array is fully deployed under the drive of the deployment mechanism.

[0033] The following will describe this embodiment in detail with reference to the accompanying drawings.

[0034] like Figure 1 As shown, a clamping and releasing device that can switch between rigidity and flexibility includes: a longitudinal clamping assembly 1 and a transverse reinforcing assembly 2.

[0035] like Figure 2 As shown, the longitudinal clamping assembly 1 includes a fixed base 3, a clamping sleeve 4, a tension rope 5, a fixed top cover 6, a hot knife assembly 7, and a nut.

[0036] like Figure 3As shown, the transverse reinforcement assembly 2 includes a reinforcement bladder 8, a reservoir bladder 9, a conduit 10, a quick connector 11, and a non-Newtonian fluid 12. Two reservoir bladders 9 are symmetrically arranged on both sides of the reinforcement bladder 8. The reinforcement bladder 8 is connected to the reservoir bladder 9 through the conduit 10 to form a sealed cavity. The conduit 10 is divided into two sections, one connected to the reinforcement bladder 8 and the other connected to the reservoir bladder 9. The two sections of the conduit 10 are connected by the quick connector 11. The non-Newtonian fluid 12 is disposed in the sealed cavity.

[0037] like Figure 4 As shown, the fixed base 3 has an upper cavity 13, a lower cavity 14, a conduit groove 16, and a mounting flange 17. The upper cavity 13 is used to place the reinforcing bladder 8, and the lower cavity 14 is used to fix the bottom of the tension rope 5. A tension rope insertion hole is provided between the upper cavity 13 and the lower cavity 14 for the tension rope 5 to pass through from the lower cavity 14 into the upper cavity 13. The conduit groove 16 is used for the conduit 10 to pass through from the upper cavity 13. The mounting flange 17 is used to fix the fixed base 3 on the cabin plate 27.

[0038] like Figure 5 As shown, the clamping sleeve 4 has a ring-shaped structure, including a fixing ring 18 and a contact ring 19. The fixing ring 18 is embedded in the clamping point of the solar panel substrate 29 for fixing to the solar panel substrate 29. The contact ring 19 is close to the surface of the solar panel substrate 29. The contact rings 19 stack on each other when the solar panel is retracted to clamp the solar panel substrate 29. The bottom clamping sleeve 4 also has a guide groove 16. The guide groove 16 on the clamping sleeve 4 and the guide groove 16 on the fixing base 3 are matched with each other to allow the guide tube 10 to pass through the upper cavity 13. The clamping sleeve 4 is installed when the solar panel substrate 29 is formed. The installation method is as follows: two clamping sleeves 4 are fastened into the through holes of the clamping point from both sides of the solar panel substrate 29 and bonded with expanding foam.

[0039] like Figure 6 As shown, the two ends of the tension rope 5 are respectively equipped with an internal hexagonal thread structure 20 and a planar limiting structure 21, which are used for clamping and fixing the upper and lower sides of the clamping and releasing device. After the tension rope 5 passes through the tension rope insertion hole, the internal hexagonal thread structure 20 is clamped and connected to the fixed upper cover 6 by a nut. The main rope of the tension rope 5 is preferably Dyneema fiber rope, which has excellent tensile strength, with a single strand tensile strength reaching the kilonewton level, which can effectively achieve the longitudinal clamping effect of the solar panel.

[0040] like Figure 7 As shown, a hot knife groove 22 is provided on the fixed top cover 6, and the tension rope 5 is located in the hot knife groove 22. The fixed top cover 6 is connected to the top solar panel substrate 29.

[0041] like Figure 8As shown, the hot knife assembly 7 includes a hot knife 23, a mounting housing 24, and a spring 25. The hot knife 23 is connected to a power supply line 26 and is inserted into a hot knife slot 22. One end of the spring 25 is connected to the hot knife 23, and the other end is connected to the inner bottom surface of the mounting housing 24. The mounting housing 24 is connected to the fixed top cover 6. Under the push of the spring 25, the hot knife 23 is pressed tightly against the tension rope 5. When the hot knife assembly 7 is energized through the power supply line 26 and the hot knife 23 is heated, the tension rope 5 can be melted, thereby achieving the effect of releasing the solar panels.

[0042] like Figure 9 As shown, the reinforcing bladder 8 is a hollow cylindrical structure with a rope hole 15 in the center. The reinforcing bladder 8 is made of a highly elastic material and is formed into a sealed inner cavity through injection molding and bonding. The inner cavity can be injected with a non-Newtonian fluid 12. The reinforcing bladder 8 can change with the volume of the injected non-Newtonian fluid 12. The conduit 10 is made of a moderately flexible material and can be bent and swing to a certain extent as needed, but the inner diameter of the conduit does not change much. Therefore, it is only a conduit for the conduction of the non-Newtonian fluid 12. The reinforcing bladder 8 and the conduit 10 are fixed by sealing and bonding.

[0043] like Figure 10 As shown, the reservoir 9 is a hollow corrugated cylinder structure, made of a low-elasticity flexible material, and formed into a sealed inner cavity through injection molding and bonding. The inner cavity can be filled with a non-Newtonian fluid 12. The corrugated structure of the reservoir 9 can change the volume of the injected non-Newtonian fluid 12 through axial expansion and contraction, while the radial direction remains largely unchanged. The reservoir 9 and the conduit 10 are fixed together by a sealed adhesive connection.

[0044] The reinforcing bladder 8 is made of high tear-resistant silicone rubber, which has extremely high tear resistance, high elasticity, high mechanical strength and toughness, and can meet the functional requirements of the reinforcing bladder 8. At the same time, high tear-resistant silicone rubber also has environmental adaptability advantages such as high temperature resistance, weather resistance and radiation resistance, which can meet the needs of space environment use.

[0045] The liquid reservoir 9 is preferably made of polyimide membrane, which has advantages such as low elasticity, high strength, high modulus and high toughness, which can meet the functional requirements of the liquid reservoir 9. At the same time, the polyimide membrane also has advantages such as extremely high temperature resistance and radiation resistance, which can meet the requirements of space environment use.

[0046] The conduit 10 is preferably made of polytetrafluoroethylene (PTFE). PTFE tubing offers moderate flexibility and possesses hydrophobic and oleophobic properties, strong non-stick properties, and an extremely low coefficient of friction, making it suitable for conducting non-Newtonian fluids 12. This effectively prevents tubing deformation and blockage caused by conduction. Furthermore, PTFE tubing exhibits excellent environmental adaptability, including high temperature resistance and radiation resistance, meeting the requirements of various space environments.

[0047] Non-Newtonian fluid 12 is selected as shear-thickening fluid, which is characterized by: the viscosity increases with the increase of extrusion or impact speed. That is, when shear-thickening fluid is rapidly impacted or extruded, it becomes viscous, hard, and even exhibits properties similar to solids; when the external force is removed or the impact or extrusion is changed to a slow speed, it will exhibit a flowing, flexible liquid state.

[0048] An assembly method for a clamping and releasing device that can autonomously switch between rigidity and flexibility is as follows: like Figure 11 As shown, a vacuum pump is used to evacuate the gas from the interior of the reinforcing bladder 8 and the reservoir bladder 9 through the conduit 10, and a non-Newtonian fluid 12 is injected. Then, a quick connector 11 is used to seal the reinforcing bladder 8 and the two reservoir bladders 9 together, forming an internally sealed transversely reinforced assembly 2. The total volume of the injected non-Newtonian fluid 12 is calculated based on the launch requirements. At this time, the reinforcing bladder 8 exhibits a smaller volume; its outer diameter is smaller than the inner diameter of the clamping sleeve 4, and the diameter of the rope hole 15 is larger than the outer diameter of the tension rope 5, and its length is also shorter. The reservoir bladder 9 exhibits an axially elongated, inflated state.

[0049] like Figure 12 As shown, thread the tension rope 5 into the fixed base 3, and then use screws to fix the assembly to the surface of the satellite's cabin 27. Complete the assembly fixing of all clamping points by following the above operations.

[0050] like Figure 13 As shown, thread the tension rope 5 through the rope hole 15, place the reinforcing bladder 8 in the upper cavity 13 of the fixed base 3, pass the conduit 10 through the conduit groove 16 of the fixed base 3, and then place the liquid storage bladder 9 on the surface of the satellite's cabin plate 27 and fix it with adhesive. Complete the fixation of the transverse reinforcing assembly 2 at all clamping points by following the above operations.

[0051] like Figure 14 As shown, the solar panel base plates 29 are connected and folded together using inter-plate hinges 28, and then hoisted above the fixed base 3 before falling. During the fall, all the tension ropes 5 and reinforcing bladders 8 are threaded into the compression sleeve 4 and the solar panel continues to fall until the bottommost solar panel base plate 29 contacts the top of the liquid reservoir bladder 9. At this point, the falling speed is further slowed down, and under the squeezing action of the solar panel, the non-Newtonian fluid 12 inside the liquid reservoir bladder 9 is pumped into the reinforcing bladder 8.

[0052] like Figure 15 As shown, the solar panel continues to fall until the bottom of the lowest folded solar panel substrate 29 contacts the bottom clamping sleeve 4 and the fixed base 3. The solar panel falls into place. At this time, the liquid storage bladder 9 is compressed to the minimum axial state, and a large amount of non-Newtonian fluid 12 is pumped into the reinforcing bladder 8, causing the reinforcing bladder 8 to expand in volume.

[0053] like Figure 16As shown, the outer diameter of the reinforcing bladder 8 becomes thicker and contacts the compression sleeve 4, the rope hole 15 becomes thinner and contacts the tension rope 5, and the length of the reinforcing bladder 8 increases and extends upward. At this time, the transverse reinforcing assembly 2 is in the firing state.

[0054] like Figure 17 As shown, the tension rope 5 is threaded into the fixed cover 6, so that the tension rope 5 is located in the hot knife groove 22, and the internal hexagonal external thread structure 20 is brought out and tightened with a nut. The tightening torque of the nut can control the clamping force of the tension rope 5 and ensure that the clamping force of all clamping points is consistent. Then, glue is applied to seal the nut and the internal hexagonal external thread structure 20 to the surface of the fixed cover 6. The hot knife assembly 7 is fixed to one side of the fixed cover 6 with screws, and the hot knife 23 extends into the hot knife groove 22 and contacts the tension rope 5. The above operation is repeated to complete the fixing of all clamping points, thereby achieving the clamping and fixing of the solar panel.

[0055] like Figure 18 As shown, the bottommost solar panel substrate 29 is fixed to the surface of the satellite's cabin panel 27 using the root hinge 30, thus completing the clamping and fixing of the solar panel.

[0056] The method of using a clamping and releasing device that can automatically switch between rigidity and flexibility is as follows: like Figure 19 As shown, during the launch and ascent phase, the clamping and release device is in a clamped state, at which time it provides excellent vibration suppression for the solar array. Vibration suppression effects include: 1. The tension rope 5 tightens the fixed base 3 and the fixed top cover 6, as well as the several clamping sleeves 4 sandwiched between them, thereby achieving longitudinal fixation of the multi-fold solar array on the surface of the cabin plate 27. The clamping force applied during longitudinal clamping can effectively suppress the longitudinal vibration of the solar array and reduce the response under mechanical environment.

[0057] Second, the reinforcing bladder 8 penetrates all solar panel substrates 29 and is in close contact with each layer of clamping sleeves 4. Under the lateral high-frequency vibration environment, the non-Newtonian fluid 12 exhibits a rigid state under the shear thickening effect, which effectively suppresses the lateral displacement of each layer of clamping sleeves 4, thereby reducing the lateral vibration of the solar panel and reducing the response under mechanical environment.

[0058] Third, the liquid reservoir 9 is in close contact with the bottom fold of the solar panel substrate 29, which plays an auxiliary role in suppressing longitudinal vibration.

[0059] After the satellite enters orbit, the clamping release device receives an unlocking command and releases the solar panels, which then deploy. The specific process is as follows: The hot knife assembly 7 is energized to heat the hot knife 23. Under the push of the spring 25, the hot knife 23 melts the tension rope 5, thereby releasing the solar panel. like Figure 20 and 21As shown, the solar array unfolds under the drive of the unfolding mechanism. The bottom fold of the solar array substrate 29 begins to move away from the satellite's cabin panel 27. The non-Newtonian fluid 12 is gradually pumped into the liquid storage bladder 9 under the contraction internal stress of the elastic material of the reinforcing bladder 8. The volume of the reinforcing bladder 8 shrinks, which is manifested as the outer diameter gradually becoming thinner, the rope hole 15 gradually becoming thicker, and the length gradually shortening. The reinforcing bladder 8 no longer contacts the clamping sleeve 4 and will not hinder the unfolding of the solar array. At the same time, the liquid storage bladder 9 begins to elongate axially under the action of the pumped non-Newtonian fluid 12, which helps to push the bottom fold of the solar array away from the satellite's cabin panel 27. like Figure 22 As shown, after each solar panel substrate 29 is detached from the reinforcing bladder 8 and the tension rope 5, the solar panel is fully deployed under the drive of the deployment mechanism.

[0060] In actual operating conditions, the deployment process of the solar panels is often not ideal. Asynchronous unlocking of the solar panel clamping points or different driving forces for each fold can cause asynchronous deployment of the solar panels. A clamping and releasing device with automatic stiffness-flexibility switching can effectively prevent jamming. The specific process is as follows: like Figure 23 As shown, when the solar arrays deploy asynchronously, the relative positions of the clamping sleeves 4 on each solar array substrate 29 become irregular. In this case, the non-Newtonian fluid 12, under mild mechanical conditions, exhibits a flexible liquid state and can change shape with the reinforcing bladder 8 and tension rope 5 to adapt to the solar array deployment, thus preventing jamming. Even if a solar array rapidly deploys and impacts the reinforcing bladder 8 due to special circumstances, activating the rigid state of the local non-Newtonian fluid 12, after the impact is buffered, the non-Newtonian fluid 12 will return to a flexible liquid state, thus changing shape again with the deployment drive, and still preventing jamming during solar array deployment.

[0061] The specific embodiments of the present invention disclosed above are merely illustrative of the invention. These embodiments do not exhaustively describe all details, nor do they limit the invention to the specific embodiments described. Many modifications and variations can be made based on the content of this specification. This specification selects and specifically describes these embodiments to better explain the principles and practical applications of the invention, thereby enabling those skilled in the art to better understand and utilize the invention.

Claims

1. A rigid-flex autonomous switching pinch release device, characterized by: Each compression point of the solar wing base plate (29) is provided with a compression release device, which comprises a longitudinal compression assembly (1) and a transverse strengthening assembly (2), the longitudinal compression assembly (1) comprises a fixed base (3), a compression sleeve (4), a tension rope (5), a fixed upper cover (6) and a hot knife assembly (7), the fixed base (3) is connected to the cabin plate (27), the compression sleeve (4) is stacked on the fixed base (3) in the vertical direction, each compression point of the solar wing base plate (29) is embedded with the compression sleeve (4), the fixed upper cover (6) is connected to the topmost solar wing base plate (29), the bottom of the tension rope (5) is connected to the fixed base (3), the top of the tension rope (5) is connected to the fixed upper cover (6), the hot knife assembly (7) is in contact with the tension rope (5), the transverse strengthening assembly (2) comprises a strengthening bag (8) and a liquid storage bag (9), the strengthening bag (8) is in communication with the liquid storage bag (9) through a conduit (10) to form a sealed cavity, a non-Newtonian fluid (12) is arranged in the sealed cavity, the strengthening bag (8) is arranged on the fixed base (3), the compression sleeve (4) is sleeved outside the strengthening bag (8), the strengthening bag (8) is a hollow cylindrical structure, a rope penetrating hole (15) is formed in the center of the strengthening bag (8), the tension rope (5) penetrates through the rope penetrating hole (15), the strengthening bag (8) is made of elastic material, the liquid storage bag (9) is a hollow corrugated cylindrical structure, the solar wing base plates (29) are connected through inter-plate hinges (28), the bottommost solar wing base plate (29) is connected to the cabin plate (27) through a root hinge (30).

2. A rigid-flexible self-switching pinch release device according to claim 1, characterized in that: The fixed base (3) is provided with an upper cavity (13), a lower cavity (14), a conduit groove (16) and a mounting flange (17), the strengthening bag (8) is arranged in the upper cavity (13), the lower cavity (14) is connected to the bottom of the tension rope (5), the conduit (10) penetrates through the conduit groove (16), and the mounting flange (17) is connected to the cabin plate (27).

3. A rigid-flexible self-switching pinch release device according to claim 1, characterized in that: The compression sleeve (4) is a ring structure, two compression sleeves (4) are buckled on the compression point through hole from both sides of the solar wing base plate (29), the compression sleeve (4) comprises a fixed ring (18) and a contact ring (19), the contact ring (19) is connected to one side of the end of the fixed ring (18), the fixed ring (18) is embedded in the compression point of the solar wing base plate (29), and the contact ring (19) is tightly attached to the surface of the solar wing base plate (29).

4. A rigid-flexible self-switching pinch release device according to claim 1, characterized in that: Both ends of the tension rope (5) are respectively provided with an inner hexagonal external thread structure (20) and a plane limiting structure (21), the inner hexagonal external thread structure (20) is tightly connected to the fixed upper cover (6) through a nut, the plane limiting structure (21) is connected to the fixed base (3), and the tension rope (5) is a Denim fiber rope.

5. A rigid-flex autonomous switching pinch release device as claimed in claim 1, wherein: The fixed upper cover (6) is provided with a hot knife slot (22), the tension rope (5) is located in the hot knife slot (22), the hot knife assembly (7) comprises a hot knife (23), a mounting shell (24) and a spring (25), the hot knife (23) is connected with a power supply wire (26), the hot knife (23) is inserted into the hot knife slot (22), one end of the spring (25) is connected with the hot knife (23), and the other end is connected with the inner bottom surface of the mounting shell (24), and the mounting shell (24) is connected with the fixed upper cover (6).

6. A rigid-flexible self-switching pinch release device according to claim 1, wherein: The conduit (10) is divided into two sections, one section is connected with the reinforcing bag (8), and the other section is connected with the liquid storage bag (9), and the two sections of the conduit (10) are connected through the quick connector (11).

7. A rigid-flexible self-switching pinch release device according to claim 1, wherein: The number of the liquid storage bag (9) is two, and the two liquid storage bags (9) are symmetrically arranged on the two sides of the reinforcing bag (8).

8. A rigid-flexible self-switching pinch release device according to claim 1, wherein: The material of the reinforcing bag (8) is high-anti-tear silicon rubber, the material of the liquid storage bag (9) is polyimide film, the material of the conduit (10) is polytetrafluoroethylene pipe, and the non-Newtonian fluid (12) is a shear thickening fluid.

9. A method of assembling a rigid-flexible self-actuating pinch release device as claimed in claim 1, characterized by: It comprises the following steps: Step 1: after the air in the reinforcing bag (8) and the liquid storage bag (9) is exhausted, the non-Newtonian fluid (12) is injected, at this time, the outer diameter of the reinforcing bag (8) is smaller than the inner diameter of the compression sleeve (4), the diameter of the rope penetrating hole (15) is larger than the outer diameter of the tension rope (5), and the liquid storage bag (9) is in an axial elongation expansion state; Step 2: connect the tension rope (5) with the fixed base (3), and then connect the fixed base (3) to the surface of the cabin plate (27) of the satellite by using a screw; Step 3: pass the tension rope (5) into the rope penetrating hole (15), place the reinforcing bag (8) on the fixed base (3), and bond the liquid storage bag (9) to the surface of the cabin plate (27) of the satellite; Step 4: connect and fold each folded solar wing base plate (29) by using an inter-plate hinge (28), hoist the folded solar wing base plate (29) to above the fixed base (3), and then start falling, pass the tension rope (5) and the reinforcing bag (8) into the compression sleeve (4), until the bottommost solar wing base plate (29) is in contact with the top of the liquid storage bag (9), under the extrusion of the solar wing base plate (29), the non-Newtonian fluid (12) in the liquid storage bag (9) is pumped into the reinforcing bag (8), when the compression sleeve (4) of the bottommost solar wing base plate (29) is in contact with the fixed base (3), the solar wing is in place, the liquid storage bag (9) is compressed to the minimum axial state, the non-Newtonian fluid (12) is pumped into the reinforcing bag (8), the reinforcing bag (8) is expanded in volume, the outer diameter of the reinforcing bag (8) is thickened and in contact with the inner wall of the compression sleeve (4), the diameter of the rope penetrating hole (15) is thinned and in contact with the tension rope (5), and the length of the reinforcing bag (8) is extended upward; Step 5: pass the tension rope (5) into the fixed upper cover (6), control the compression force of the tension rope (5), so that the compression forces of all compression points are consistent, install the hot knife assembly (7), and make the hot knife assembly (7) in contact with the tension rope (5); Step 6: fix the bottommost solar wing base plate (29) to the surface of the cabin plate (27) by using a root hinge (30).

10. A method of using the rigid-flexible self-actuating pinch release device of claim 1, wherein: During the launch ascending stage, the compacting release device is in compacting state, the compacting force applied by the tension cable (5) longitudinally restrains the longitudinal vibration of the solar wing, the liquid storage bag (9) is close to the bottom layer of the solar wing base plate (29) to assist the restraint of the longitudinal vibration, when the solar wing vibrates laterally, the non-Newtonian fluid (12) behaves as rigid state under the shear thickening effect to restrain the lateral vibration of the solar wing; after the satellite enters the orbit, the compacting release device releases the solar wing after receiving the unlocking instruction, at this time, the hot knife assembly (7) melts the tension cable (5) to release the solar wing, the solar wing is unfolded under the driving of the unfolding mechanism, the non-Newtonian fluid (12) is gradually pumped into the liquid storage bag (9) under the action of the contraction internal stress of the elastic material of the reinforcing bag (8), the reinforcing bag (8) shrinks in volume, the reinforcing bag (8) is no longer in contact with the compacting sleeve (4), the liquid storage bag (9) starts to elongate axially under the action of the pumped non-Newtonian fluid (12) to assist the pushing of the solar wing away from the cabin plate (27), after each folded solar wing base plate (29) is separated from the reinforcing bag (8) and the tension cable (5), the solar wing is completely unfolded under the driving of the unfolding mechanism.

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