A rigid-flexible autonomous switching compression release device and methods of assembling and using the same

Abstract

The application provides a rigid-flexible autonomous switching compression release device and an assembling and using method thereof, and belongs to the technical field of space product structure and mechanism design. The compression stiffness and the unlocking anti-stuck problem are solved. The compression release device is arranged at each compression point of a solar wing base plate, the compression release device is longitudinally compressed and combined and transversely strengthened, the longitudinal compression combination comprises a fixed base, a compression sleeve, a tension rope, a fixed upper cover and a hot knife assembly, the fixed base is connected to a cabin plate, the compression sleeve is multiple, the multiple compression sleeves are stacked on the fixed base in the vertical direction, the compression point of each folded solar wing base plate is embedded with the compression sleeve, the fixed upper cover is connected to the topmost solar wing base plate, the bottom of the tension rope is connected to the fixed base, the top of the tension rope is connected to the fixed upper cover, and the hot knife assembly is in contact with the tension rope. It is mainly used for the compression release of the solar wing.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of space product structure and mechanism design, in particular to a rigid-flexible autonomous switching compression release device and its assembly and use method. BACKGROUND

[0002] The compression release mechanism has a wide range of applications in the field of aerospace technology, including the folding and unfolding of solar wings. The process is as follows: during the satellite launch ascent, the solar wings are fixed to the satellite surface through multiple compression release mechanisms, which achieve the purpose of resisting mechanics through compression; after the satellite enters the orbit, the solar wings are released by unlocking all mechanisms, thereby achieving the purpose of on-orbit deployment.

[0003] Currently, there are mainly two types of compression release mechanisms commonly used for solar wings: rigid compression release mechanisms and flexible compression release mechanisms.

[0004] The compression method of the rigid compression release mechanism is as follows: a compression rod is used to pass through all the compression holes of the solar wing base plate, and then the top is fixed to the top solar wing base plate and the bottom is fixed to the satellite cabin plate, and a certain compression force is applied, thereby achieving the locking of the solar wing. After locking, the rigid compression release mechanism has a strong fixing effect on the longitudinal direction of the solar wing, which can effectively suppress the longitudinal vibration of the solar wing; at the same time, the transverse fixation is achieved through the rigidity of the compression rod itself and the friction between the solar wings after compression, which can to some extent achieve the suppression of transverse vibration.

[0005] The release method of the rigid compression release mechanism is as follows: after the satellite enters the orbit, the compression rod is broken by using a pyrotechnic device, or the compression rod is unlocked and released by applying electricity to the memory alloy, thereby achieving the unfolding of the solar wing. After unlocking, each folded solar wing needs to be separated from the compression rod from the beginning to the end. Since there are multiple compression points during the locking of the solar wing, and it is difficult to ensure complete synchronization of unlocking at each compression point, and the disturbance of the satellite itself may also cause different synchronization during the unfolding process of the solar wing, there is a risk of jamming of the solar wing and the rigid compression rod. The more the number of solar wing folds, the longer the compression rod, and the greater the risk of jamming; the greater the compression stiffness required by the solar wing, the thicker the compression rod, and the greater the risk of jamming.

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

[0007] The release mode of the flexible compression release mechanism is that after the satellite is in orbit, the hot knife is used to melt the rope to release the solar wing. After unlocking, even if the solar wing compression point unlocking is not synchronized and the solar wing unfolding is not synchronized, based on the deformable characteristics of the flexible rope, it will not cause jamming.

[0008] In summary, the compression release mechanism for the multi-fold solar wing has a design contradiction, that is, high compression stiffness, strong anti-mechanical performance in the launch ascent stage, but high risk of jamming in the orbit release; on the contrary, low compression stiffness can avoid jamming in the orbit release, but the anti-mechanical ability in the ascent stage is weak. SUMMARY

[0009] Therefore, the present application aims to provide a rigid and flexible self-switching compression release device and its assembly and use method to solve the problem that the existing compression stiffness and unlocking anti-jamming are difficult to be considered.

[0010] To achieve the above-mentioned purpose, the following technical scheme is adopted: a rigid and flexible self-switching compression release device is provided, each compression point of the solar wing base plate is provided with a compression release device, the compression release device is longitudinally compressed and combined and transversely reinforced, the longitudinal compression combination includes a fixed base, a compression sleeve, a tension rope, a fixed upper cover and a hot knife assembly, the fixed base is connected to the cabin plate, the number of compression sleeves is multiple, the multiple compression sleeves are stacked in the vertical direction on the fixed base, the compression point of each fold of the solar wing base plate is embedded with a compression sleeve, the fixed upper cover is connected to the topmost solar wing base plate, the bottom of the tension rope is connected to the fixed base, the top of the tension rope is connected to the fixed upper cover, the hot knife assembly is in contact with the tension rope, the transverse reinforcement combination includes a reinforcement capsule and a liquid storage capsule, the reinforcement capsule is communicated with the liquid storage capsule through a conduit to form a sealed cavity, the sealed cavity is provided with a non-Newtonian fluid, the reinforcement capsule is arranged on the fixed base, the compression sleeve is sleeved outside the reinforcement capsule, the reinforcement capsule is a hollow cylindrical structure, a rope penetrating hole is formed in the center of the reinforcement capsule, the tension rope penetrates through the rope penetrating hole, the reinforcement capsule is made of elastic material, the liquid storage capsule is a hollow corrugated cylindrical structure, the solar wing base plates are connected through inter-plate hinges, and the bottommost solar wing base plate is connected to the cabin plate through 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 reinforcement capsule is arranged in the upper cavity, the lower cavity is connected to the bottom of the tension rope, the conduit groove penetrates through the conduit, and the mounting flange is connected to the cabin plate.

[0012] Further, the compression sleeve is a ring structure, two compression sleeves are buckled in the compression point through hole from both sides of the solar wing base plate, the compression sleeve comprises a fixed ring and a contact ring, the contact ring is connected to one side of the end of the fixed ring, the fixed ring is embedded in the compression point of the solar wing base plate, and the contact ring is attached to the surface of the solar wing base plate.

[0013] Further, the two ends of the tension rope are respectively provided with an internal hexagon external thread structure and a plane limiting structure, the internal hexagon external thread structure is connected to the fixed upper cover through a nut, and the plane limiting structure is connected to the fixed base, and the tension rope is a Dacron fiber rope.

[0014] Further, the fixed upper cover is provided with a hot knife groove, the tension rope is located in the hot knife groove, and the hot knife assembly comprises a hot knife, a mounting shell and a spring, the hot knife is connected to a power supply wire, 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 shell, and the mounting shell is connected to the fixed upper cover.

[0015] Further, the catheter is divided into two sections, one section is connected to the reinforcing capsule, and the other section is connected to the liquid storage capsule, and the two sections of the catheter are connected through a quick connector.

[0016] Further, the number of the liquid storage capsules is two, and the two liquid storage capsules are symmetrically arranged on the two sides of the reinforcing capsule.

[0017] Further, the material of the reinforcing capsule is high-anti-tear silicon rubber, the material of the liquid storage capsule is polyimide film, the material of the catheter is polytetrafluoroethylene tube, and the non-Newtonian fluid is a shear thickening fluid.

[0018] The application also provides an assembly method of the rigid-flexible self-switching compression release device, which comprises the following steps:

[0019] Step 1: after the air in the reinforcing capsule and the liquid storage capsule is exhausted, the non-Newtonian fluid is injected, at this time, the outer diameter of the reinforcing capsule is smaller than the inner diameter of the compression sleeve, the diameter of the rope penetrating hole is greater than the outer diameter of the tension rope, and the liquid storage capsule shows an axial elongation expansion state;

[0020] Step 2: the tension rope is connected to the fixed base, and then the fixed base is connected to the cabin plate surface of the satellite through a screw;

[0021] Step 3: the tension rope is inserted into the rope penetrating hole, the reinforcing capsule is placed on the fixed base, and the liquid storage capsule is bonded to the cabin plate surface of the satellite;

[0022] Step 4: Connect each foldable solar wing base plate using an inter-panel hinge, and hoist to above the fixed base, then start to drop, pass the tensioning rope and the reinforcing bag into the compression sleeve until the bottommost solar wing base plate contacts the top of the liquid storage bag, under the extrusion of the solar wing base plate, the non-Newtonian fluid in the liquid storage bag is pumped into the reinforcing bag, when the compression sleeve of the bottommost solar wing base plate contacts the fixed base, the solar wing is dropped into place, the liquid storage bag is compressed to the minimum axial state, the non-Newtonian fluid is pumped into the reinforcing bag, the volume of the reinforcing bag expands, the outer diameter of the reinforcing bag becomes thick and contacts the inner wall of the compression sleeve, the diameter of the rope passing hole becomes thin and contacts the tensioning rope, and the length of the reinforcing bag extends upward;

[0023] Step 5: Pass the tensioning rope into the fixed upper cover, control the compression force of the tensioning rope, so that the compression forces of all compression points are consistent, install the hot knife assembly, and make the hot knife assembly contact the tensioning rope;

[0024] Step 6: Fix the bottommost solar wing base plate to the surface of the cabin plate using a root hinge.

[0025] The application also provides a use method of the rigid-flexible self-switching compression release device, specifically: in the launch ascending stage of the carrier, the compression release device is in a compression state, the tensioning rope longitudinally applied compression force inhibits the longitudinal vibration of the solar wing, the liquid storage bag is closely attached to the bottommost solar wing base plate to assist in inhibiting the longitudinal vibration, when the solar wing vibrates laterally, the non-Newtonian fluid exhibits a rigid state under the shear thickening effect to inhibit the lateral vibration of the solar wing; after the satellite enters an orbit, the compression release device receives an unlocking instruction to release the solar wing, at this time, the hot knife assembly melts the tensioning rope to release the solar wing, the solar wing is unfolded under the driving of the unfolding mechanism, the non-Newtonian fluid is gradually pumped into the liquid storage bag under the contraction internal stress of the elastic material of the reinforcing bag, the volume of the reinforcing bag shrinks, the reinforcing bag no longer contacts the compression sleeve, the liquid storage bag starts to axially elongate under the action of the pumped non-Newtonian fluid to assist in pushing the solar wing away from the cabin plate, after the solar wing base plates are separated from the reinforcing bag and the tensioning rope, the solar wing is completely unfolded under the driving of the unfolding mechanism.

[0026] Compared with the prior art, the application has the following beneficial effects:

[0027] (1) The rigid-flexible self-switching compression release device solves the problem that the compression stiffness and unlocking anti-jamming are difficult to be considered in the existing compression release mechanism.

[0028] (2) The rigid-flexible self-switching compression release device can provide lateral contact type limiting for the solar wing through the rigidization of the non-Newtonian fluid in the satellite launch stage, and has a better vibration inhibition effect compared with the traditional non-contact friction limiting.

[0029] (3) The rigid-flexible self-switching compression release device can still realize the unlocking anti-stuck effect through the flexible deformation of the non-Newtonian fluid even if the solar wing appears serious asynchronous unfolding in the orbiting unlocking stage.

[0030] (4) The rigid-flexible self-switching compression release device can jump out of the dilemma of depending on friction for transverse vibration suppression through contact type vibration suppression, thereby reducing the high requirement for compression force, reducing the stringent requirement of the compression release device on the strength of the compression part and the operation difficulty.

[0031] (5) The rigid-flexible self-switching compression release device adopts the hot knife unlocking mode, does not use the pyrotechnics and memory alloy, has low cost and can be repeatedly used, is beneficial to the development of ground deployment test, has small impact, and has no special requirement for the ground test environment, and has small impact on the satellite in the orbit deployment.

[0032] (6) The liquid storage bag can longitudinally support the solar wing in the launching stage, assists in longitudinal vibration suppression, and assists in solar wing unfolding through longitudinal expansion in the orbiting unlocking stage.

[0033] (7) The rigid-flexible self-switching compression release device has independent parts, and can be secondarily designed / selected according to the specific requirement of the satellite, and has strong adaptability. DETAILED DESCRIPTION

[0034] The accompanying drawings, which form a part of the present application, are used to provide further understanding of the present application, and the illustrative embodiments of the present application and their description serve the purpose of explaining the present application, and do not constitute improper limitation of the present application. In the drawings:

[0035] Figure 1 It is a structure schematic view of the rigid-flexible self-switching compression release device;

[0036] Figure 2 It is a longitudinal compression combined sectional view structure schematic view;

[0037] Figure 3 It is a transverse reinforcement combined sectional view structure schematic view;

[0038] Figure 4 It is a fixed base sectional view structure schematic view;

[0039] Figure 5 It is a compression sleeve installation form schematic view;

[0040] Figure 6 It is a tension rope structure schematic view;

[0041] Figure 7The fixed upper cover structure of the application is shown in the schematic diagram;

[0042] Figure 8 The hot knife assembly structure of the application is shown in the schematic diagram;

[0043] Figure 9 The reinforcing bag cross-section structure of the application is shown in the schematic diagram;

[0044] Figure 10 The liquid storage bag structure of the application is shown in the schematic diagram;

[0045] Figure 11 The assembly process of the rigid-flexible self-switching compression release device of the application is shown in the schematic diagram Figure 1 ;

[0046] Figure 12 The assembly process of the rigid-flexible self-switching compression release device of the application is shown in the schematic diagram Figure 2 ;

[0047] Figure 13 The assembly process of the rigid-flexible self-switching compression release device of the application is shown in the schematic diagram Figure 3 ;

[0048] Figure 14 The assembly process of the rigid-flexible self-switching compression release device of the application is shown in the schematic diagram Figure 4 ;

[0049] Figure 15 The assembly process of the rigid-flexible self-switching compression release device of the application is shown in the schematic diagram Figure 5 ;

[0050] Figure 16 The assembly process of the rigid-flexible self-switching compression release device of the application is shown in the schematic diagram Figure 6 ;

[0051] Figure 17 The assembly process of the rigid-flexible self-switching compression release device of the application is shown in the schematic diagram Figure 7 ;

[0052] Figure 18 The assembly process of the rigid-flexible self-switching compression release device of the application is shown in the schematic diagram Figure 8 ;

[0053] Figure 19 The working mode of the rigid-flexible self-switching compression release device of the application in the ascending stage of launch is shown in the schematic diagram;

[0054] Figure 20 The unlocking and releasing process of the solar wing of the rigid-flexible self-switching compression release device of the application is shown in the schematic diagram Figure 1 ;

[0055] Figure 21 Unlocked release of solar wing process schematic for a rigid-flexible autonomous switching compression release device according to the present application Figure 2 ;

[0056] Figure 22 Unlocked release of solar wing process schematic for a rigid-flexible autonomous switching compression release device according to the present application

[0057] Figure 3 Unlocked release of solar wing process schematic for a rigid-flexible autonomous switching compression release device according to the present application Figure 23 .

[0058] Figure:

[0059] 1-Longitudinal compression combination, 2-Lateral reinforcement combination, 3-Fixed base, 4-Compression sleeve, 5-Tension rope, 6-Fixed upper cover, 7-Thermal knife assembly, 8-Reinforcement bag, 9-Fluid storage bag, 10-Catheter, 11-Quick connector, 12-Non-Newtonian fluid, 13-Upper cavity, 14-Lower cavity, 15-Rope passing hole, 16-Catheter groove, 17-Mounting flange, 18-Fixed ring, 19-Contact ring, 20-Internal hexagonal external thread structure, 21-Plane limiting structure, 22-Thermal knife groove, 23-Thermal knife, 24-Mounting shell, 25-Spring, 26-Power supply wire, 27-Cabin plate, 28-Plate hinge, 29-Solar wing base plate, 30-Root hinge. DETAILED DESCRIPTION

[0060] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. It should be noted that the embodiments in the present application and the features in the embodiments can be combined with each other without conflict, and the described embodiments are only part of the embodiments of the present application, not all the embodiments.

[0061] See Figures 1-23To illustrate the embodiment, a rigid-flexible self-switching compression release device is provided at each compression point of the solar wing base plate 29, which comprises a longitudinal compression combination 1 and a transverse strengthening combination 2. The longitudinal compression combination 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 in the vertical direction on the fixed base 3, and each compression point of the solar wing base plate 29 is embedded with a 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, and 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 combination 2 comprises a strengthening capsule 8 and a liquid storage capsule 9. The strengthening capsule 8 is in communication with the liquid storage capsule 9 through a conduit 10, forming a sealed cavity. The sealed cavity is provided with a non-Newtonian fluid 12. The strengthening capsule 8 is provided on the fixed base 3, and the compression sleeve 4 is sleeved outside the strengthening capsule 8. The strengthening capsule 8 is a hollow cylindrical structure. A rope passing hole 15 is provided in the center of the strengthening capsule 8, and the tension rope 5 penetrates through the rope passing hole 15. The strengthening capsule 8 is made of elastic material. The liquid storage capsule 9 is a hollow corrugated cylindrical structure. The solar wing base plates 29 are connected through inter-plate hinges 28, and the bottommost solar wing base plate 29 is connected to the cabin plate 27 through a root hinge 30.

[0062] 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 bag 8 is arranged in the upper cavity 13. The lower cavity 14 is connected to the bottom of the tension cable 5. The conduit 10 passes through the conduit groove 16. The mounting flange 17 is connected to the cabin plate 27. The compression sleeve 4 is annular. Two compression sleeves 4 are buckled on the compression point through holes 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. The contact ring 19 is tightly attached to the surface of the solar wing base plate 29. The tension cable 5 is provided with an inner hexagonal external thread structure 20 and a plane limiting structure 21 at both ends respectively. The inner hexagonal external thread structure 20 is connected to the fixed upper cover 6 through a nut. The plane limiting structure 21 is connected to the fixed base 3. The tension cable 5 is a Dymema fiber rope. The fixed upper cover 6 is provided with a hot knife groove 22. The tension cable 5 is located in the hot knife groove 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 to the power supply wire 26. The hot knife 23 is inserted into the hot knife groove 22. One end of the spring 25 is connected to the hot knife 23. The other end is connected to the inner bottom surface of the mounting shell 24. The mounting shell 24 is connected to the fixed upper cover 6. The conduit 10 is divided into two sections. One section is connected to the reinforcing bag 8. The other section is connected to the liquid storage bag 9. The two sections of the conduit 10 are connected through a quick connector 11. The number of the liquid storage bag 9 is two. The two liquid storage bags 9 are symmetrically arranged on both sides of the reinforcing bag 8. The material of the reinforcing bag 8 is high tear-resistant silicone rubber. The material of the liquid storage bag 9 is polyimide film. The material of the conduit 10 is polytetrafluoroethylene tube. The non-Newtonian fluid 12 is a shear thickening fluid.

[0063] The embodiment is a kind of rigid and soft autonomous switching compression release device assembly method, it includes the following steps:

[0064] Step 1: after the air in the reinforcing bag 8 and the liquid storage bag 9 is exhausted, 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 rope passing hole 15 diameter is greater than the outer diameter of the tension cable 5. The liquid storage bag 9 shows the axial elongation expansion state.

[0065] Step 2: connect the tension cable 5 with the fixed base 3, and then connect the fixed base 3 to the surface of the cabin plate 27 of the satellite with screws.

[0066] Step 3: pass the tension cable 5 into the rope passing 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.

[0067] 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.

[0068] 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.

[0069] Step 6: Use the root hinge 30 to fix the bottom solar panel substrate 29 to the surface of the cabin panel 27.

[0070] 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.

[0071] The following will describe this embodiment in detail with reference to the accompanying drawings.

[0072] 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.

[0073] 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.

[0074] As shown in Figure 3 , the transverse reinforcing assembly 2 comprises a reinforcing bag 8, a liquid storage bag 9, a conduit 10, a quick connector 11 and a non-Newtonian fluid 12. Two liquid storage bags 9 are symmetrically arranged on both sides of the reinforcing bag 8. The reinforcing bag 8 is in communication with the liquid storage bag 9 through the conduit 10, forming a sealed cavity. 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. The two sections of the conduit 10 are connected through the quick connector 11. The non-Newtonian fluid 12 is arranged in the sealed cavity.

[0075] As shown in Figure 4 , 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 bag 8. The lower cavity 14 is used to fix the bottom of the tension rope 5. A tension rope passing hole is arranged between the upper cavity 13 and the lower cavity 14, which is used for the tension rope 5 to pass from the lower cavity 14 to the upper cavity 13. The conduit groove 16 is used for the conduit 10 to pass out of the upper cavity 13. The mounting flange 17 is used to fix the fixed base 3 on the deck 27.

[0076] As shown in Figure 5 , the compression sleeve 4 is a ring structure. The compression sleeve 4 comprises a fixed ring 18 and a contact ring 19. The fixed ring 18 is embedded in the compression point of the solar wing base plate 29, which is used for fixing with the solar wing base plate 29. The contact ring 19 is tightly attached to the surface of the solar wing base plate 29. The contact rings 19 are stacked with each other to realize the compression of the solar wing base plate 29 when the solar wing is folded. The compression sleeve 4 located at the bottom also has a conduit groove 16. The conduit groove 16 on the compression sleeve 4 and the conduit groove 16 on the fixed base 3 are matched with each other, which together realize the passing out of the conduit 10 from the upper cavity 13. The compression sleeve 4 is installed when the solar wing base plate 29 is formed. The installation method is that two compression sleeves 4 are buckled in the compression point through hole from both sides of the solar wing base plate 29, and foaming glue is used for bonding.

[0077] As shown in Figure 6 , the two ends of the tension rope 5 are respectively provided with an inner hexagonal external thread structure 20 and a plane limiting structure 21, which are respectively used for the compression and fixation of the upper and lower sides of the compression release device. After the tension rope 5 passes through the tension rope passing hole, the inner hexagonal external thread structure 20 is connected with the fixed upper cover 6 through a nut. The main rope of the tension rope 5 is preferably a Denim fiber rope, which has excellent tensile strength, and the single tensile strength can reach kilo-newton level, which can effectively realize the longitudinal compression effect of the solar wing.

[0078] As shown in Figure 7 , a hot knife groove 22 is arranged on the fixed upper cover 6, and the tension rope 5 is located in the hot knife groove 22. The fixed upper cover 6 is connected to the solar wing base plate 29 at the top layer.

[0079] As shown in Figure 8As shown, the hot knife assembly 7 includes 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. The hot knife 23 is tightly attached to the tension cable 5 under the pushing of the spring 25, when the hot knife assembly 7 is powered through the power supply wire 26 to heat the hot knife 23, the tension cable 5 can be melted to achieve the effect of releasing the solar wing.

[0080] As shown in Figure 9 The reinforcing bag 8 is a hollow cylindrical structure with a rope passing hole 15 in the center. The reinforcing bag 8 is formed by injection molding and adhesive forming to form a sealed inner cavity. The inner cavity can be filled with non-Newtonian fluid 12. The reinforcing bag 8 can change with the volume of the injected non-Newtonian fluid 12. The conduit 10 is made of a flexible material with moderate flexibility. It can bend and swing to a certain extent as needed, but the inner diameter of the pipeline does not change much. Therefore, it is only a non-Newtonian fluid 12 conducting pipeline. The reinforcing bag 8 and the conduit 10 are fixed by sealing and bonding.

[0081] As shown in Figure 10 The liquid storage bag 9 is a hollow corrugated cylinder structure. It is made of a low-elastic flexible material by injection molding and adhesive forming to form a sealed inner cavity. The inner cavity can be filled with non-Newtonian fluid 12. The corrugated structure of the liquid storage bag 9 can change the volume of the non-Newtonian fluid 12 in the inner cavity by axial expansion and contraction, and the radial direction will not change significantly. The liquid storage bag 9 and the conduit 10 are fixed by sealing and bonding.

[0082] The material of the reinforcing bag 8 is preferably high-anti-tear silicone rubber. High-anti-tear silicone rubber has extremely high tear resistance, high elasticity, high mechanical strength and toughness, which can meet the functional requirements of the reinforcing bag 8. At the same time, high-anti-tear silicone rubber also has high temperature resistance, weather resistance, radiation resistance and other environmental adaptability advantages, which can meet the space environment use requirements.

[0083] The material of the liquid storage bag 9 is preferably polyimide film. Polyimide film has the advantages of low elasticity, high strength, high modulus and high toughness, which can meet the functional requirements of the liquid storage bag 9. At the same time, polyimide film also has extremely high temperature resistance, radiation resistance and other environmental adaptability advantages, which can meet the space environment use requirements.

[0084] The material of the conduit 10 is preferably polytetrafluoroethylene pipe. The polytetrafluoroethylene pipe has moderate flexibility, hydrophobic and oleophobic, extremely strong non-stickness and extremely low friction coefficient characteristics, which is suitable for the conduction of non-Newtonian fluid 12, and can effectively avoid the pipeline deformation and blockage caused by conduction. At the same time, the polytetrafluoroethylene pipe has extremely high temperature resistance, radiation resistance and other environmental adaptability advantages, which can meet the space environment use requirements. Extremely high temperature resistance, high stability and other environmental adaptability advantages can meet the space environment use requirements.

[0085] The non-Newtonian fluid 12 is selected as a shear thickening fluid, which has the characteristic that its viscosity increases with the increase of the impact or extrusion speed, that is, when the shear thickening fluid is rapidly impacted or extruded, it appears thick and hard, and even exhibits the properties of a solid; when the external force is removed or the impact or extrusion speed is changed to be slow, the shear thickening fluid exhibits the properties of a flexible liquid.

[0086] An assembly method of a rigid-flexible self-switching compression release device is as follows:

[0087] As shown in Figure 11 , the gas in the cavities of the reinforcing bags 8 and the liquid storage bags 9 is pumped out through the conduits 10 by using air pumps, the non-Newtonian fluid 12 is injected, and then the reinforcing bags 8 and the liquid storage bags 9 are sealed and connected by using the quick couplings 11 to form the internally sealed lateral reinforcing assemblies 2. The total volume of the injected non-Newtonian fluid 12 is calculated according to the requirements of the launch state. At this time, the reinforcing bags 8 exhibit a small volume state, the outer diameter of the reinforcing bags 8 is smaller than the inner diameter of the compression sleeves 4, the diameter of the rope passing holes 15 is larger than the outer diameter of the tension ropes 5, and the length is also relatively short. The liquid storage bags 9 exhibit an axially elongated and expanded state.

[0088] As shown in Figure 12 , the tension ropes 5 are passed into the fixed bases 3, and then the assemblies are fixed on the surface of the cabin plates 27 of the satellites by using screws. The fixing of the assemblies of all compression points is completed according to the above operations.

[0089] As shown in Figure 13 , the tension ropes 5 are passed into the rope passing holes 15, the reinforcing bags 8 are placed in the upper cavities 13 of the fixed bases 3, the conduits 10 are passed through the conduit grooves 16 of the fixed bases 3, and then the liquid storage bags 9 are arranged on the surface of the cabin plates 27 of the satellites and are fixed by adhesion. The fixing of the lateral reinforcing assemblies 2 of all compression points is completed according to the above operations.

[0090] As shown in Figure 14 , the solar wing base plates 29 are connected and folded by using the inter-plate hinges 28, and are hoisted above the fixed bases 3 and then start to fall. During the falling process, all the tension ropes 5 and the reinforcing bags 8 are passed into the compression sleeves 4 and the solar wing continues to fall, until the solar wing base plate 29 of the bottom layer is in contact with the top of the liquid storage bag 9, the falling speed is further slowed down, and under the extrusion of the solar wing, the non-Newtonian fluid 12 in the cavity of the liquid storage bag 9 is pumped into the reinforcing bag 8.

[0091] As shown in Figure 15 , the falling continues until the bottom compression sleeve 4 of the solar wing base plate 29 of the bottom layer is in contact with the fixed base 3, and the solar wing is in place. At this time, the liquid storage bag 9 is compressed to the state of the smallest axial dimension, and a large amount of non-Newtonian fluid 12 is pumped into the reinforcing bag 8 to make the reinforcing bag 8 expand in volume.

[0092] As shown in 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.

[0093] 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.

[0094] 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.

[0095] The method of using a clamping and releasing device that can automatically switch between rigidity and flexibility is as follows:

[0096] 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.

[0097] Vibration suppression effects include:

[0098] 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.

[0099] 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.

[0100] 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.

[0101] 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:

[0102] The hot knife assembly 7 is powered to heat the hot knife 23, and the hot knife 23 melts the tension cable 5 under the pushing of the spring 25, thereby releasing the solar wing;

[0103] As shown in Figure 20 and 21 , the solar wing is unfolded under the driving of the unfolding mechanism, and the bottom layer of the folded solar wing substrate 29 starts to move away from the cabin plate 27 of the satellite, and 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, which shows that the outer diameter gradually becomes thin, the rope penetrating hole 15 gradually becomes thick, and the length gradually shortens, the reinforcing bag 8 no longer contacts the compression sleeve 4, and will not hinder the unfolding of the solar wing, at the same time, the liquid storage bag 9 starts to axially elongate under the action of the pumped non-Newtonian fluid 12, and assists to push the bottom layer of the folded solar wing away from the cabin plate 27 of the satellite;

[0104] As shown in Figure 22 , after the folded solar wing substrate 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.

[0105] In actual working conditions, the unfolding process of the solar wing is often in a non-ideal state, and the unlocking of the solar wing compression points is not synchronized or the driving force of the folded solar wing is different, which will cause the unfolding of the folded solar wing to be not synchronized. A rigid-flexible self-switching compression release device can effectively avoid jamming, and the specific process is as follows:

[0106] As shown in Figure 23 , when the solar wing unfolds at different speeds, the relative positions of the compression sleeves 4 of the folded solar wing substrate 29 are irregular, at this time, the non-Newtonian fluid 12 behaves as a flexible liquid in a mild mechanical environment, and can change shape to adapt to the unfolding of the solar wing along with the reinforcing bag 8 and the tension cable 5, thereby not causing jamming. Even if a certain folded solar wing behaves as rapid unfolding and hits the reinforcing bag 8 due to special conditions, the rigid state of the local non-Newtonian fluid 12 is activated, after the impact is buffered, the non-Newtonian fluid 12 will again restore to the flexible liquid state, thereby changing the shape again along with the unfolding driving, and still will not cause the jamming of the unfolding of the solar wing.

[0107] The specific embodiments of the above disclosed application are only used to help explain the application. The specific embodiments do not describe all the details, and the application is not limited to the specific embodiments described. According to the content of the specification, many modifications and changes can be made. The specification selects and specifically describes these embodiments in order to better explain the principles and practical applications of the application, so that those skilled in the art can well understand and utilize the application.

Claims

1. A clamping and releasing device that can autonomously switch between rigidity and flexibility, characterized in that: Each clamping point of the solar panel substrate (29) is provided with a clamping release device. The clamping release device includes a longitudinal clamping assembly (1) and a transverse reinforcing assembly (2). The longitudinal clamping assembly (1) includes a fixed base (3), clamping 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). There are multiple clamping sleeves (4), and multiple clamping sleeves (4) are stacked in the vertical direction. On the fixed base (3), each fold of the solar panel substrate (29) has a clamping sleeve (4) embedded in its clamping point. 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 top 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 reservoir (9). The reinforcing bladder (8) is connected to the reservoir bladder (9) via a conduit (10) to form a sealed cavity. A non-Newtonian fluid (12) is disposed inside the sealed cavity. The reinforcing bladder (8) is mounted on a fixed base (3). The compression sleeve (4) is fitted onto the outside of the reinforcing bladder (8). The reinforcing bladder (8) is a hollow cylindrical structure. A rope hole (15) is provided in the center of the reinforcing bladder (8). The tension rope (5) passes through the rope hole (15). The reinforcing bladder (8) is elastic. Material: The liquid storage bladder (9) is a hollow corrugated cylindrical structure. The solar panel substrates (29) are connected to each other by inter-plate hinges (28). The bottom solar panel substrate (29) is connected to the cabin plate (27) by a root hinge (30). The liquid storage bladder (9) is bonded to the surface of the satellite's cabin plate (27). During the launch phase, the liquid storage bladder (9) longitudinally supports the solar panel and plays an auxiliary role in suppressing longitudinal vibration. During the orbital unlocking phase, it plays an auxiliary role in deploying the solar panel through longitudinal expansion.

2. The clamping and releasing device with automatic switching between rigidity and flexibility 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 reinforcing bladder (8) is located in the upper cavity (13). The lower cavity (14) is connected to the bottom of the tension rope (5). The conduit groove (16) is through which the conduit (10) passes. The mounting flange (17) is connected to the cabin plate (27).

3. The clamping and releasing device with automatic switching between rigidity and flexibility according to claim 1, characterized in that: The clamping sleeve (4) has a ring structure. Two clamping sleeves (4) are fastened to the clamping point through hole from both sides of the solar panel substrate (29). 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). The contact ring (19) is close to the surface of the solar panel substrate (29).

4. The clamping and releasing device with automatic switching between rigidity and flexibility according to claim 1, characterized in that: The tension rope (5) is provided with an internal hexagonal external thread structure (20) and a planar limiting structure (21) at both ends. The internal hexagonal external thread structure (20) is pressed and connected to the fixed upper cover (6) by a nut. The planar limiting structure (21) is connected to the fixed base (3). The tension rope (5) is a Dyneema fiber rope.

5. The clamping and releasing device with automatic switching between rigidity and flexibility according to claim 1, characterized in that: The fixed top 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). The hot knife (23) 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 bottom surface of the mounting housing (24). The mounting housing (24) is connected to the fixed top cover (6).

6. The clamping and releasing device with automatic switching between rigidity and flexibility according to claim 1, characterized in that: The catheter (10) is divided into two sections, one of which is connected to the reinforcing bladder (8) and the other of which is connected to the reservoir bladder (9). The two sections of the catheter (10) are connected by a quick connector (11).

7. The clamping and releasing device with automatic switching between rigidity and flexibility according to claim 1, characterized in that: The number of liquid storage bladders (9) is two, and the two liquid storage bladders (9) are symmetrically arranged on both sides of the reinforcing bladder (8).

8. The clamping and releasing device with automatic switching between rigidity and flexibility according to claim 1, characterized in that: 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.

9. An assembly method for a self-sustaining, rigid-flexible pressure release device as described in claim 1, characterized in that: It includes the following steps: Step 1: After evacuating the air from the reinforcing bladder (8) and the reservoir bladder (9), inject a 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) into 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 cabin panel (27); Step 4: Use the inter-plate hinge (28) to connect and fold the solar panel substrates (29), hoist them above the fixed base (3) and begin to fall. Insert the tension rope (5) and reinforcing bladder (8) into the compression 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 compression 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 compression 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: Insert 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).

10. A method of using the self-sustaining pressure release device with rigidity and flexibility as described in claim 1, characterized in that: During the launch and ascent phase, the clamping release device is in a clamped state. The clamping force applied longitudinally 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) to further suppress 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 clamping release device receives an unlocking command to release the solar array. At this time, the hot knife assembly (7) melts the tension rope (5) and releases the solar array. Driven by the deployment mechanism, the solar array unfolds. The non-Newtonian fluid (12) is gradually pumped into the reservoir (9) under the contraction 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 compression sleeve (4). The reservoir (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 the solar array base plates (29) are separated from the reinforcing bladder (8) and the tension rope (5), the solar array is fully deployed under the drive of the deployment mechanism.

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