A stacked satellite fixing device and control method thereof

Abstract

The present application provides a fixing device for a stacked satellite and a control method thereof, which are used to fix and separate the stacked satellites, and provide a fixing device solution that can significantly improve reliability and safety.

Description

Technical Field

[0001] The present application relates to the field of stacked satellite fixation, and in particular to a stacked satellite fixation device and a control method thereof. Background Art

[0002] In recent years, with the rapid development of commercial aerospace at home and abroad, the market demand for low-orbit small satellites has increased dramatically, and the flattened satellite configuration and the stacked assembly form have increasingly become the future development trend.

[0003] Typically, stacked satellites use explosive bolts similar to those used to connect rocket stages between the upper and lower satellites to achieve a fixed effect.

[0004] However, in the process of studying the existing related technologies, the inventors found that as the number of stacked satellites increases, if the upper and lower satellites are still connected by explosive bolts similar to the inter-stage connection of rockets, the reliability and safety of satellite separation will be greatly reduced. Summary of the invention

[0005] The present application provides a fixing device for a stacked satellite and a control method thereof, which are used to fix and separate the stacked satellites, and provide a fixing device solution that can significantly improve reliability and safety.

[0006] In a first aspect, the present application provides a fixing device for a stacked satellite, the device comprising a middle section rod 1, a first section rod 2, a tail section rod 3 and a rocket adapter 20, wherein the middle section rod 1, the first section rod 2 and the tail section rod 3 are connected and fixed by threaded connection of head and tail flanges, and the middle section rod 1, the first section rod 2 and the tail section rod 3 are used in pairs and constitute a tension rod;

[0007] A trapezoidal pressure cap 10 is installed on the two first sections of the rod 2. The middle part of the trapezoidal pressure cap 10 is concave upward to form a cylindrical groove. The pressure sensor 9 is fixedly connected to the upper trapezoidal pressure cap 10 through a threaded connection in the cylindrical groove. The pressure sensor 9 is used to fit with the lower satellite bearing column 18 and be embedded in the inner side of the flange of the satellite bearing column 18;

[0008] The bottom of the two tail section rods 3 is connected with an arched transfer beam 5, and the two ends of the arched transfer beam 5 are provided with mechanical interfaces adapted to the two slots 16 at the bottom of the tail section rod 3, and the two tail section rods 3 are clamped by threaded connection. Two first hinges 7 are installed at the arch back position of the arched transfer beam 5, and a reinforcement frame 6 is provided at the oblique lower side of the two first hinges 7. The upper and lower sides of the reinforcement frame 6 are respectively provided with two sets of hinge installation interfaces, and the upper side is connected to the two first hinges 7, and the lower side is connected to the two second hinges 8;

[0009] The rocket adapter 20 adopts a positive cone design, and a boss is provided on the upper end surface. The boss is composed of three circular bosses, one large and two small. The large boss is located in the middle for installing the satellite load-bearing column 18. The two small bosses pass through the explosive bolts 21 to fix the bottom of the tail rod 3. An L-shaped hinge bracket 22 is installed on the lower end surface of the rocket adapter 20. A through hole is provided on one side of the L-shaped hinge bracket 22 for connecting with the rocket adapter 20, and a mounting interface for the second hinge 8 is provided on the other side.

[0010] In combination with the first aspect of the present application, in a first possible implementation of the first aspect of the present application, a rubber sleeve 17 is provided between the trapezoidal pressure cap 10 and the first section rod 2 .

[0011] In combination with the first aspect of the present application, in a second possible implementation method of the first aspect of the present application, the first section rod 2 continues to pass through the disc spring 11 at the position where it passes through the trapezoidal pressure cap 10, and a flat dumbbell-shaped storage rack 14 is installed on the upper side of the two disc springs 11. The two ends of the storage rack 14 pass through the top ends of the two first section rods 2, and a spirit level 13 is provided in the middle of the storage rack 14. The top end of the first section rod 2 is locked by a nut 12 to the storage rack 14, the disc spring 11 and the trapezoidal pressure cap 10.

[0012] In combination with the first aspect of the present application, in a third possible implementation of the first aspect of the present application, an arched support member 4 is provided between the two middle rods 1, and mechanical interfaces adapted to the two slots 15 of the middle rods 1 are provided at both ends of the arched support member 4, and the two middle rods 1 are clamped by a threaded connection.

[0013] In combination with the first aspect of the present application, in a fourth possible implementation of the first aspect of the present application, the middle section rod 1 is made of non-metallic material, and the first section rod 2 and the tail section rod 3 are made of alloy material.

[0014] In combination with the first aspect of the present application, in a fifth possible implementation of the first aspect of the present application, the reinforcement frame 6 adopts a flat hollow reinforced structure.

[0015] In combination with the first aspect of the present application, in the sixth possible implementation method of the first aspect of the present application, there are a total of 4 groups of middle section rods 1, first section rods 2 and tail section rods 3, and the 4 groups are evenly distributed, and each group consists of two middle section rods 1, two first section rods 2 and two tail section rods 3.

[0016] In a second aspect, the present application provides a method for controlling a fixing device of a stacked satellite, the method comprising:

[0017] Install the L-shaped hinge bracket 22 to the lower end surface of the rocket adapter 20, wherein one side of the L-shaped hinge bracket 22 is provided with a through hole connected to the rocket adapter 20, and the other side is provided with a mounting interface of the second hinge 8;

[0018] Multiple satellites are stacked on the rocket adapter 20 in sequence through the bearing column 18, wherein the rocket adapter 20 adopts a positive cone design, and a boss is provided on the upper end surface. The boss is composed of three circular bosses, one large and two small. The large boss is located in the middle for installing the satellite bearing column 18, and the two small bosses are used to pass the explosive bolts 21 to fix the bottom of the tail section rod 3;

[0019] The middle section rod 1, the first section rod 2 and the tail section rod 3 are connected and fixed by threaded connection of the head and tail flanges, used in pairs and forming a tension rod, and then the bottom of the tail section rod 3 is fixed at the small boss by an explosive bolt 21;

[0020] The trapezoidal pressure cap 10 with the pressure sensor 9 installed is passed through the two first sections of the rod 2 until the lower end surface of the pressure sensor 9 is fitted with the satellite bearing column 18 and embedded into the inner side of the flange of the satellite bearing column 18, wherein the middle part of the trapezoidal pressure cap 10 is concave upward to form a cylindrical groove, and the pressure sensor 9 is fixedly connected to the trapezoidal pressure cap 10 on the upper side through a threaded connection in the cylindrical groove;

[0021] The two pairs of first hinges 7 and the two pairs of second hinges 8 are respectively installed to the interfaces on the upper and lower sides of the reinforcement frame 6, wherein the two first hinges 7 are installed at the arch back position of the arched transfer beam 5, and the reinforcement frame 6 is installed at the oblique lower side of the two first hinges 7. The upper and lower sides of the reinforcement frame 6 are respectively provided with two sets of hinge installation interfaces, the upper side is connected to the two first hinges 7, and the lower side is connected to the two second hinges 8;

[0022] The two ends of the bow-shaped adapter beam 5 are based on mechanical interfaces that are adapted to the two slots 16 at the bottom of the tail section rod 3. The two tail section rods 3 are clamped by threaded connection, and the rotation angle of the first hinge 7 and the second hinge 8 are adjusted to simultaneously connect the bow-shaped adapter beam 5 and the L-shaped hinge bracket 22 to complete the fixation of the stacked satellite fixing device.

[0023] In conjunction with the second aspect of the present application, in a first possible implementation manner of the second aspect of the present application, the method further includes:

[0024] After the launch vehicle enters orbit, the explosive bolt 21 is controlled to be unlocked, so that the first hinge 7 and the second hinge 8 start to perform the unfolding action. During the unfolding action, the fixing device of the stacked satellite will first move obliquely upward, so that the part pressed on the uppermost satellite bearing column 18 is separated from the groove in the flange of the satellite bearing column 18. At the same time, the relative angle between the tension rod and the reinforcement frame 6 also changes accordingly. When the fixing device of the stacked satellite moves to a certain position, the first hinge 7 is locked, so that the fixing device of the stacked satellite and the reinforcement frame 6 no longer move relative to each other;

[0025] After the first hinge 7 is locked, the fixing device of the stacked satellite becomes a single-axis rotating mechanism. Under the action of the second hinge 8, it is flipped at a certain angle and then locked. It is evenly distributed around the last stage of the launch vehicle and maintains a certain safety distance from the last stage of the launch vehicle, thereby completing the deployment of the fixing device of the stacked satellite.

[0026] In a third aspect, the present application provides a computer-readable storage medium, which stores multiple instructions, and the instructions are suitable for a processor to load to execute the method provided by the second aspect of the present application or any possible implementation of the second aspect of the present application.

[0027] From the above content, it can be concluded that the present application has the following beneficial effects:

[0028] The stacked satellite fixing device of the present application is designed with a double-link structure. While being able to effectively lock the stacked satellites and rocket adapters, it can also facilitate separation of the device from the satellite, keeping the entire device outside the safe range of satellite separation, while effectively locking it to reduce the impact on transportation, thereby significantly improving reliability and safety. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For those skilled in the art, other drawings can be obtained based on these drawings without creative work.

[0030] Figure 1 A schematic diagram of the overall structure of a fixing device for stacked satellites of the present application;

[0031] Figure 2 A schematic diagram of the structure of a set of tension rods for this application;

[0032] Figure 3 This is another structural schematic diagram of a set of tension rods of the present application;

[0033] Figure 4 A schematic diagram of the structure of a set of tension rods for this application;

[0034] Figure 5 A structural schematic diagram of a trapezoidal pressure cap of the present application;

[0035] Figure 6 This is a partial structural front view of the first section of the rod of this application;

[0036] Figure 7 A partial structural cross-sectional view of the first section of the rod;

[0037] Figure 8A schematic diagram of a partial structure of a middle section rod in this application;

[0038] Fig. 9 A schematic diagram of the structure of the tail section rod of the present application;

[0039] Fig.10 This is another structural schematic diagram of the tail section rod of the present application;

[0040] Fig.11 A schematic diagram of the structure of the rocket adapter of this application;

[0041] Fig.12 This is another structural schematic diagram of the rocket adapter of this application;

[0042] Fig.13 A schematic diagram of a partial structure of the satellite bearing column of this application;

[0043] Fig.14 This is another partial structural schematic diagram of the satellite bearing column of the present application;

[0044] Fig.15 A schematic diagram of the structure of the rocket adapter of this application;

[0045] Fig.16 A structural schematic diagram of the unfolding process of the fixing device of the stacked satellite of the present application;

[0046] Fig.17 A schematic diagram of the principle of the unfolding process of the fixing device of the stacked satellite of the present application;

[0047] Fig.18 A schematic diagram of a structure in which the fixing device of the stacked satellite of the present application is unfolded to a locked state;

[0048] Fig.19 A schematic flow chart of a control method for a fixing device of a stacked satellite according to the present application. DETAILED DESCRIPTION

[0049] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of this application.

[0050] The terms "first", "second", etc. in the specification and claims of this application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the data used in this way can be interchangeable where appropriate, so that the embodiments described here can be implemented in an order other than that illustrated or described here. In addition, the terms "including" and "having" and any of their variations are intended to cover non-exclusive inclusions, for example, a process, method, system, product or device that includes a series of steps or modules is not necessarily limited to those steps or modules clearly listed, but may include other steps or modules that are not clearly listed or inherent to these processes, methods, products or devices. The naming or numbering of steps in this application does not mean that the steps in the method flow must be executed in the time / logical sequence indicated by the naming or numbering. The process steps that have been named or numbered can change the execution order according to the technical purpose to be achieved, as long as the same or similar technical effects can be achieved.

[0051] The division of modules in this application is a logical division. There may be other division methods when it is implemented in actual applications. For example, multiple modules can be combined or integrated into another system, or some features can be ignored or not executed. In addition, the mutual coupling or direct coupling or communication connection shown or discussed can be through some interfaces, and the indirect coupling or communication connection between modules can be electrical or other similar forms, which are not limited in this application. In addition, the modules or submodules described as separate components may or may not be physically separated, may or may not be physical modules, or may be distributed in multiple circuit modules, and some or all of the modules may be selected according to actual needs to achieve the purpose of the present application.

[0052] First, see Figure 1 FIG. 1 is a schematic diagram showing an overall structure of a fixing device for stacked satellites of the present application. Figure 1 The stacked satellite fixing device shown is in a working state of fixing the stacked satellite. Figure 1 It is easy to see that the fixing device of the stacked satellite provided in the present application includes a middle section rod 1, a first section rod 2, a tail section rod 3 and a rocket adapter 20, and other components are configured around these four.

[0053] Among them, Figure 2 , Figure 3 A schematic structural diagram of a group of tension rods of the present application shown from different aspects. In the present application, the middle section rod 1, the first section rod 2 and the tail section rod 3 are fixed by head and tail flange threaded connections. The middle section rod 1, the first section rod 2 and the tail section rod 3 are used in pairs and constitute a tension rod.

[0054] from Figure 2, 3 It can also be seen that the head of the first section rod 2 of the present application is designed with an external thread, and a suitable number of threaded holes are designed on the tapered flange at the tail; the head of the tail section rod 3 adopts the same design as the tail of the first section rod 2, the diameter of the tail is increased, and threaded holes are designed; the middle section rod 1 is slender, and a matching number of through holes are designed on the tapered flanges at both ends.

[0055] In this case, as a practical implementation method, considering that the first section rod 2 and the tail section rod 3 have more design features, it is appropriate to use metal materials such as alloy steel for processing, while the middle section rod 1 is longer in size and has fewer design features, and it is appropriate to use non-metallic materials such as carbon fiber for processing.

[0056] Furthermore, the following content is simply divided based on the middle section rod 1, the first section rod 2, the tail section rod 3 and the rocket adapter 20, so as to provide a detailed description of the stacked satellite fixing device provided in the present application.

[0057] (1) First section 2

[0058] See also Figure 4 A partial structural diagram of the first section of the present application is shown, Figure 5 A structural schematic diagram of a trapezoidal pressure cap of the present application is shown, Figure 6 A partial structural front view of the first section of the present application is shown. Figure 7 A partial structural cross-sectional view of the first section of the rod of the present application is shown.

[0059] For the relevant components at the first section of the rod in this application, Figure 4 , 5 As can be seen in Figures 6 and 7, trapezoidal pressure caps 10 are installed on the two first sections of the rods 2. The trapezoidal pressure caps 10 are designed with a certain number of threaded holes for installing the pressure sensor 9. The middle part of the trapezoidal pressure cap 10 is concave upward to form a cylindrical groove. The pressure sensor 9 is fixedly connected to the upper trapezoidal pressure cap 10 in the cylindrical groove through a threaded connection (screws). The pressure sensor 9 is used to fit (tightly fit, but not connected) with the lower satellite bearing column 18 and be embedded in the inner side of the flange of the satellite bearing column 18.

[0060] It can be understood that, in the locked state, the middle of the trapezoidal pressure cap 10 will be subjected to a large upward pressure, and the two sides will be subjected to a large downward pulling force, that is, the trapezoidal pressure cap 10 needs to bear a large pressure and bending moment at the same time, so the present application designs it to be relatively solid.

[0061] In addition, as another specific implementation, a rubber sleeve 17 may be provided between the trapezoidal pressure cap 10 and the first section rod 2 .

[0062] It can be understood that a rubber sleeve 17 installed from bottom to top is designed between the trapezoidal pressure cap 10 and the first section rod 2 to fill the gap between the two and prevent the violent vibration generated during the flight of the rocket from causing collision damage to the two; at the same time, during the application of the locking force, the first section rod 2 will have a small upward displacement relative to the trapezoidal pressure cap 10. The use of soft materials such as rubber for filling can effectively reduce the friction between the trapezoidal pressure cap 10 and the first section rod 2, thereby facilitating the application of the locking force and achieving a better fixing effect.

[0063] In addition, as another specific implementation method, the top of the trapezoid can continue to be configured with other components to enhance the fixing effect. Specifically, the first section rod 2 can continue to pass through the disc spring 11 at the position passing through the trapezoidal pressure cap 10 (the two ends of the trapezoidal pressure cap 10 are designed with stepped cylindrical through holes from top to bottom, and the upper side has a larger diameter for installing the disc spring 11 with appropriate stiffness that can pass through the first section rod 2, and the lower side has a smaller diameter for passing through the first section rod 2). On the upper side of the two disc springs 11, a flat dumbbell-shaped storage rack 14 is installed (circular through holes are designed at the larger areas at both ends, which can pass through the two first section rods 2 at the same time, and a suitable mechanical interface is designed in the middle, which can install a spirit level 13). The two ends of the storage rack 14 pass through the top ends of the two first section rods 2, and a spirit level 13 (a small high-precision spirit level) is arranged in the middle of the storage rack 14. The top end of the first section rod 2 is locked by a nut 12 to the storage rack 14, the disc spring 11 and the trapezoidal pressure cap 10.

[0064] Since the disc spring 11 can carry a huge load in a small space and has the characteristics of variable rigidity, the disc spring 11 here can play two roles. On the one hand, the middle rod 1 is relatively long and is under the action of the locking force for a long time, which may cause creep and stress relaxation. The disc spring 11 in a compressed state can make up for the lost preload force to a certain extent, thereby preventing the nut 12 from loosening due to the disappearance of the preload force and causing a dangerous situation. On the other hand, in the initial stage of unlocking the fixing device of the stacked satellite, the locking force of the tension rod is released instantly, and the impact energy will cause the tension rod to bend and shake, causing uncertain risks to the satellite product. The disc spring 11 itself has good buffering and shock absorbing capabilities, so the disc spring 11 can absorb impact and dissipate energy.

[0065] (2) Middle section rod 1

[0066] The main function of the middle section rod 1 is to provide support and also to adjust the tension rod to match the thickness of the stacked satellite.

[0067] See also Figure 8A partial structural schematic diagram of the middle section rod of the present application is shown. For further reinforcement, as another practical implementation method, in a group of tension rods, an arch support member 4 is provided between the two middle section rods 1, and mechanical interfaces adapted to the two slots 15 of the middle section rod 1 are provided at both ends of the arch support member 4. The two middle section rods 1 are clamped by threaded connection, thereby improving the overall stiffness of the tension rod and suppressing the torsional movement that may occur during the launch phase of the carrier rocket and the deployment of the device.

[0068] (3) Tail section rod 3

[0069] See also Fig. 9 , 10 The structural schematic diagram of the tail section rod of the present application shown from different angles, the tail section rod 3 of the present application is used to connect the rocket adapter 20 and the tension rod. Specifically, in a group of tension rods, the bottoms of the two tail section rods 3 are connected with a bow-shaped transition beam 5 at a specified position, and the two ends of the bow-shaped transition beam 5 are provided with a mechanical interface adapted to the two slots 16 at the bottom of the tail section rod 3. The two tail section rods 3 are clamped by threaded connection. On the one hand, the bow-shaped transition beam 5 can play a reinforcing role similar to the upper support member 4, and contribute to the overall stiffness of the tension rod. On the other hand, the back of the bow-shaped transition beam 5 is designed with an installation interface for the first hinge 7, so that two first hinges 7 can be installed at the back of the bow-shaped transition beam 5, and a reinforcement frame 6 is provided at the oblique lower side of the two first hinges 7, and two groups of hinge installation interfaces are respectively provided on the upper and lower sides of the reinforcement frame 6, the upper side is connected to the two first hinges 7, and the lower side is connected to the two second hinges 8. In this way, by adopting different torsion spring force designs for the first hinge 7 and the second hinge 8, the movement form of the locking and unfolding device can be adjusted.

[0070] Among them, as another specific implementation method, the reinforcement frame 6 here can specifically adopt a flat hollow reinforced structure. Under this design, the reinforcement frame 6 can maintain good rigidity on the basis of weight reduction to suppress the torsional movement of the entire device during the deployment process.

[0071] In addition, it should be understood that the above two types of hinges (the first hinge 7 and the second hinge 8) are often used for the deployment of larger equipment such as sailboards and antennas in spacecraft. Their built-in torsion springs provide driving force for the entire mechanism. After the equipment is rotated to the set angle, its built-in pin will be embedded in the corresponding groove to ensure that the entire mechanism is locked. It can be understood as a mature product. Of course, the present application can continue to further optimize the design of its hinge structure in actual applications.

[0072] (4) Rocket Adapter 20

[0073] The rocket adapter 20 is located at the bottom of the stacked satellite and plays a supporting and reinforcing role from the bottom. Fig.11 , 12Two structural schematic diagrams of the rocket adapter of the present application are shown. In the present application, the rocket adapter 20 adopts a positive cone design, and a boss is provided on the upper end face. The boss design can increase the local strength under the premise of ensuring the processing accuracy. Among them, the boss is specifically composed of three circular bosses, one large and two small. The large boss (larger in area, with a cylindrical shallow groove designed inside) is located in the middle for installing the satellite load-bearing column 18 (not fixed), and the two small bosses (equal in area, and the center is designed with a through hole of the same diameter) pass through the explosive bolt 21 to fix the bottom of the tail section rod 3. It can be understood that an opening is designed at a suitable position on the conical surface of the rocket adapter 20 to facilitate the installation of the explosive bolt 21 from bottom to top. An L-shaped hinge bracket 22 is installed on the lower end face of the rocket adapter 20. One side of the L-shaped hinge bracket 22 is provided with a through hole connected to the rocket adapter 20, and the other side is provided with a mounting interface for the second hinge 8.

[0074] In addition, for the satellite bearing column 18, reference can also be made to Fig.13 , 14 The partial structural schematic diagrams of the satellite bearing columns of the present application are shown respectively. It can be seen from the figure that the bearing columns 18 are distributed around the flat satellite body 19. The satellite bearing column 18 adopts the design form of a hollow cylinder, and its upper and lower end faces are parallel. A circular ring-shaped flange is designed on the edge of the upper end face, and the inner side of the circular ring-shaped flange (parallel to each other and with a 360° ring on the upper end face) is designed with a certain inclination angle to facilitate the docking and separation of the upper and lower bearing columns. On the one hand, the flange design can ensure that the upper and lower satellites can be quickly aligned during the stacking process, thereby improving the efficiency of the overall assembly. On the other hand, after the satellite assembly is stacked and locked, it can prevent the satellite from lateral movement and side sliding, thereby resisting instability. Taking the above factors into consideration, the pressure sensor 9 in the locking and deployment device is also embedded in the inner side of the flange of the uppermost satellite bearing column 18, such as Fig.14 shown.

[0075] In addition, it can be seen from the above-mentioned drawings that in the specific application of the present application, the middle section rod 1, the first section rod 2 and the tail section rod 3 are designed as 4 groups in total, and the 4 groups are evenly distributed, each group consists of two middle section rods 1, two first section rods 2 and two tail section rods 3. Of course, in specific applications, other orders of magnitude of evenly distributed designs can also be adopted, so as to achieve a balance between the surrounding forces while fixing.

[0076] Correspondingly, the rocket adapter 20 is designed with 8 explosive bolt installation positions, 4 hinge bracket installation interfaces and 4 installation surfaces capable of bearing high pressure.

[0077] In the fixed state, the device buckles the load-bearing columns around the satellite assembly from top to bottom, connects the rocket adapter 20 to the bottom of the tension rod in the device through 8 explosive bolts, and then generates pressure between the device and the satellite load-bearing columns 18 through the locking force applying device, so as to firmly fix the satellite assembly and the rocket adapter 20.

[0078] It can be understood that the above content is the state of the stacked satellite fixing device in the present application after completing the fixation of the stacked satellite. The following can be combined with all the above structural contents (including optional implementation methods) to briefly introduce the dynamic working content involved.

[0079] See also Fig.15 A structural schematic diagram of the rocket adapter of the present application is shown, in which an L-shaped hinge bracket 22 is installed to the lower end surface of the rocket adapter 20 by screws, and then multiple satellites are stacked in sequence on the rocket adapter 20 through satellite load-bearing columns 18. At the same time, part of the assembly work of the device can continue. First, the first section rod 2, the middle section rod 1 and the tail section rod 3 are connected end to end in sequence by screws to obtain a tension rod; then the tension rod is clamped with an arched support member 4 and a slot 15, and then the tension rod is installed to the specified position of the rocket adapter 20 through an explosive bolt 21.

[0080] After completing the above-mentioned product assembly implementation in sequence, the rubber sleeve 17, the pressure cap 10 with the pressure sensor 9 installed, the disc spring 11 and the rack 14 with the level 13 installed are passed through the first section rod 2 in sequence until the lower end surface of the pressure sensor 9 is in contact with the satellite load-bearing column 18, and then the rubber sleeve 17 is pushed from bottom to top into the gap between the circular hole of the pressure cap 10 and the first section rod 2, and then the two nuts 12 are respectively screwed into the threads at the top of the first section rod 2, tightened and applied with the same set torque. At this time, the horizontal state of the rack 14 can be judged by the parameters of the level 13 on the top, thereby judging whether the tension on the tension rods on the left and right sides is skewed and whether the two states are consistent. If the horizontal state is biased towards one side, continue to tighten the nuts 12 and compress the disc spring 11 until the rack 14 is in a horizontal state.

[0081] After completing the above operations, install the two pairs of first hinges 7 and second hinges 8 to the interfaces on the upper and lower sides of the reinforcement frame 6, and then connect the arched transfer beam 5 and the two slots 16 to clamp the two tail rods 3 by screws, and then adjust the rotation angle of the first hinge 7 and the second hinge 8, as shown in FIG. Fig.15 As shown, it is possible to connect the upwardly rotating bow-shaped connecting beam 5 and the L-shaped hinge bracket 22 at the same time.

[0082] like Figure 1As shown, after the operation is completed, the satellite assembly is initially locked between the rocket adapter 20 and the pressure sensor 9, and the data monitoring cable is led out through the connector on the pressure sensor 9 (the connector is facing away from the satellite body 19). The monitoring cable is routed to the rocket adapter 20 through the tension rods on both sides, the bow-shaped transfer beam 5 and the L-shaped hinge bracket 22, and is connected to the corresponding related collection equipment on the arrow.

[0083] During ground storage and testing, the monitoring data of relevant acquisition equipment can be read to determine whether the preload force of the tension rod is still within the specified range. If the preload force is reduced due to changes in the external environment, the tightening torque of the nut 12 is increased, otherwise it is reduced. During the flight of the launch vehicle, relevant data can be recorded to provide a reference for subsequent improved design.

[0084] It can be understood that in actual operation, in addition to the level 13, other collection equipment can also be configured on the rocket to reflect the specific fixing conditions of the fixing device of the stacked satellite of the present application for monitoring and correction.

[0085] See also Fig.16 A structural schematic diagram of the unfolding process of the fixing device of the stacked satellite of the present application is shown. After the carrier rocket enters orbit, eight explosive bolts 21 are unlocked at the same time, and the device starts to perform the unfolding action under the joint action of the first hinge 7 and the second hinge 8.

[0086] According to the principle of the double-link mechanism, the device will first move obliquely upward so that the part pressed on the uppermost satellite load-bearing column 18 will be disengaged from the groove in the flange of the satellite load-bearing column 18. At the same time, the relative angle between the tension rod and the reinforcement frame 6 will also change (that is, the first hinge 7 will rotate). The principle is detailed in the following content. When the locking device moves to a certain position, the first hinge 7 is locked, so that no relative movement occurs between the locking device and the reinforcement frame 6.

[0087] See also Fig.17 The schematic diagram of the unfolding process of the stacked satellite fixing device of the present application is shown. It can be seen that the second hinge 8 in the device is equivalent to Fig.17 The first hinge 7 is equivalent to the rotation axis A in Fig.17 The axis B in the drawing is equivalent to Fig.17 The connecting rod No. ① in the reinforcement frame 6 is equivalent to Fig.17 In the connecting rod No. ②, under the joint action of the rotating shaft A and the rotating shaft B, the trapezoidal pressure cap 10 (because the pressure sensor 9 is fixedly connected) first passes over the groove of the uppermost load-bearing column 18, and then rotates to a position away from the satellite.

[0088] After the first hinge 7 is locked, the device becomes a single-axis rotation mechanism. At the same time, under the action of the second hinge 8, it is turned at a certain angle and then locked, evenly distributed around the last stage of the launch vehicle, and maintains a certain safety distance from the last stage of the launch vehicle. Fig.18 A structural schematic diagram showing the fixing device of the stacked satellite of the present application being unfolded to a locked state. At this time, there is no other obstruction in the space above the satellite-rocket separation plane except the unseparated satellite, and the stacked satellite can perform related separation actions more safely.

[0089] The above-mentioned deployment process can also be briefly understood as follows: after the rocket is launched into orbit, the eight explosive bolts are unlocked at the same time. After losing its restraint, the device first moves obliquely upward to break away from the restraint of the groove of the satellite bearing column 18, and after moving to a certain position, the hinge in the middle is locked. Then the entire device rotates to a certain angle along with the root hinge and is locked in a position away from the satellite assembly. At this time, the satellite assembly loses its restraint and can perform further separation actions.

[0090] Under the above-mentioned hardware structure and dynamic working content, it can be obtained that the stacked satellite fixing device designed by the double-link structure in the present application can effectively lock the stacked satellite and the rocket adapter, and at the same time, it can easily separate the device from the satellite, so that the whole device remains outside the safe range of satellite separation, and is effectively locked at the same time to reduce the impact on transportation, thereby significantly improving reliability and safety.

[0091] The above is an introduction to the stacked satellite fixing device provided by the present application. Based on the stacked satellite fixing device, the present application also provides a control method for the stacked satellite fixing device from a control perspective. The control method may involve the locking and unfolding of the stacked satellite, and may be executed by the stacked satellite fixing system, control system or other business systems involved in actual applications.

[0092] See also Fig.19 , Fig.19 A flow chart of a control method of a fixing device for stacked satellites of the present application is shown. The control method of a fixing device for stacked satellites provided by the present application may specifically include the following steps S1901 to S1906:

[0093] Step S1901, installing the L-shaped hinge bracket 22 to the lower end surface of the rocket adapter 20, wherein one side of the L-shaped hinge bracket 22 is provided with a through hole connected to the rocket adapter 20, and the other side is provided with a mounting interface of the second hinge 8;

[0094] Step S1902, stacking multiple satellites on the rocket adapter 20 in sequence through the bearing column 18, wherein the rocket adapter 20 adopts a positive cone design, and a boss is provided on the upper end surface, and the boss is composed of three circular bosses, one large and two small. The large boss is located in the middle for installing the satellite bearing column 18, and the two small bosses are used to pass the explosive bolts 21 to fix the bottom of the tail section rod 3;

[0095] Step S1903, after the middle section rod 1, the first section rod 2 and the tail section rod 3 are connected and fixed by threaded connection of the head and tail flanges, they are used in pairs to form a tension rod, and then the bottom of the tail section rod 3 is fixed at the small boss by an explosive bolt 21;

[0096] Step S1904, pass the trapezoidal pressure cap 10 equipped with the pressure sensor 9 through the two first sections of the rod 2 until the lower end surface of the pressure sensor 9 is fitted with the satellite bearing column 18 and embedded into the inner side of the flange of the satellite bearing column 18, wherein the middle part of the trapezoidal pressure cap 10 is concave upward to form a cylindrical groove, and the pressure sensor 9 is fixedly connected to the upper trapezoidal pressure cap 10 in the cylindrical groove through a threaded connection;

[0097] Step S1905, installing two pairs of first hinges 7 and two pairs of second hinges 8 to the interfaces on the upper and lower sides of the reinforcement frame 6, wherein the two first hinges 7 are installed at the arch back position of the arched transfer beam 5, and the reinforcement frame 6 is installed at the oblique lower side of the two first hinges 7. The upper and lower sides of the reinforcement frame 6 are respectively provided with two sets of hinge installation interfaces, the upper side is connected to the two first hinges 7, and the lower side is connected to the two second hinges 8;

[0098] Step S1906, the two ends of the bow-shaped adapter beam 5 are based on the mechanical interface that is adapted to the two slots 16 at the bottom of the tail section rod 3, and the two tail section rods 3 are clamped by threaded connection, and the rotation angle of the first hinge 7 and the second hinge 8 is adjusted to simultaneously connect the bow-shaped adapter beam 5 and the L-shaped hinge bracket 22 to complete the fixation of the stacked satellite fixing device.

[0099] It can be understood that the content of the control method here mainly involves the assembly part of the stacked satellite by the fixing device of the stacked satellite provided in this application, or the reinforcement part of the stacked satellite.

[0100] In the subsequent use of the device, the expansion part of the device may also be involved. Specifically, the method may also include:

[0101] After the launch vehicle enters orbit, the explosive bolt 21 is controlled to be unlocked, so that the first hinge 7 and the second hinge 8 start to perform the unfolding action. During the unfolding action, the fixing device of the stacked satellite will first move obliquely upward, so that the part pressed on the uppermost satellite bearing column 18 is separated from the groove in the flange of the satellite bearing column 18. At the same time, the relative angle between the tension rod and the reinforcement frame 6 also changes accordingly. When the fixing device of the stacked satellite moves to a certain position, the first hinge 7 is locked, so that the fixing device of the stacked satellite and the reinforcement frame 6 no longer move relative to each other;

[0102] After the first hinge 7 is locked, the fixing device of the stacked satellite becomes a single-axis rotating mechanism. Under the action of the second hinge 8, it is flipped at a certain angle and then locked. It is evenly distributed around the last stage of the launch vehicle and maintains a certain safety distance from the last stage of the launch vehicle, thereby completing the deployment of the fixing device of the stacked satellite.

[0103] It can be understood that the content of the control method here is based on the hardware structure of the above-mentioned stacked satellite fixing device. The technicians in the relevant field can clearly understand that for the convenience and simplicity of description, the specific working process of the control method of the above-mentioned stacked satellite fixing device (including the content of related components) can refer to the following. Figures 1 to 18 The description of the fixing device of the stacked satellite in the corresponding embodiment will not be repeated here.

[0104] A person of ordinary skill in the art will appreciate that all or part of the steps in the various methods of the above embodiments may be completed by instructions, or by controlling related hardware through instructions. The instructions may be stored in a computer-readable storage medium and loaded and executed by a processor.

[0105] To this end, the present application provides a computer-readable storage medium, in which a plurality of instructions are stored, and the instructions can be loaded by a processor to execute the present application as follows: Fig.19 The steps of the control method of the fixing device of the stacked satellite in the corresponding embodiment, the specific operation can refer to the following Fig.19 The description of the control method of the fixing device of the stacked satellite in the corresponding embodiment will not be repeated here.

[0106] The computer-readable storage medium may include: a read-only memory (ROM), a random access memory (RAM), a magnetic disk or an optical disk, etc.

[0107] Due to the instructions stored in the computer-readable storage medium, the present application can be executed. Fig.19The steps of the control method of the fixing device of the stacked satellite in the corresponding embodiment, therefore, the present application can be implemented as follows Fig.19 The beneficial effects that can be achieved by the control method of the fixing device of the stacked satellite in the corresponding embodiment are detailed in the previous description and will not be repeated here.

[0108] The stacked satellite fixing device, the control method of the stacked satellite fixing device and the computer-readable storage medium provided by the present application are introduced in detail above. Specific examples are used in this article to illustrate the principles and implementation methods of the present application. The description of the above embodiments is only used to help understand the method of the present application and its core idea; at the same time, for technical personnel in this field, according to the idea of ​​the present application, there will be changes in the specific implementation method and application scope. In summary, the content of this specification should not be understood as a limitation on the present application.

Claims

1. A stacked satellite fixing device, characterized in that: The device comprises a middle section rod (1), a first section rod (2), a tail section rod (3) and a rocket adapter (20); the middle section rod (1), the first section rod (2) and the tail section rod (3) are connected and fixed by means of head and tail flange threads; the middle section rod (1), the first section rod (2) and the tail section rod (3) are used in pairs and form a tension rod; The two first-section rods (2) are provided with trapezoidal pressure caps (10), the middle of the trapezoidal pressure caps (10) being concave upward to form a cylindrical groove, the pressure sensor (9) being fixedly connected to the upper trapezoidal pressure cap (10) in the cylindrical groove by means of a threaded connection, the pressure sensor (9) being used to fit with the lower satellite bearing column (18) and embedded in the inner side of the flange of the satellite bearing column (18); The bottoms of the two tail section rods (3) are connected with an arched transfer beam (5), and two ends of the arched transfer beam (5) are provided with mechanical interfaces adapted to two slots (16) at the bottoms of the tail section rods (3), and the two tail section rods (3) are clamped by threaded connection, and two first hinges (7) are installed at the back of the arched transfer beam (5), and a reinforcement frame (6) is provided at the oblique lower side of the two first hinges (7), and two sets of hinge installation interfaces are respectively provided on the upper and lower sides of the reinforcement frame (6), the upper side of which is connected to the two first hinges (7), and the lower side of which is connected to the two second hinges (8); The rocket adapter (20) is designed in a positive cone shape, and a boss is provided on the upper end surface. The boss is composed of three circular bosses, one large and two small. The large boss is located in the middle and is used to install the satellite load-bearing column (18). The two small bosses pass through the explosive bolts (21) to fix the bottom of the tail section rod (3). An L-shaped hinge bracket (22) is installed on the lower end surface of the rocket adapter (20). One side of the L-shaped hinge bracket (22) is provided with a through hole connected to the rocket adapter (20), and the other side is provided with a mounting interface for the second hinge (8).

2. The stacked satellite fixing device according to claim 1, characterized in that: A rubber sleeve (17) is provided between the trapezoidal pressure cap (10) and the first section rod (2).

3. The stacked satellite fixing device according to claim 1, characterized in that: The first section rod (2) continues to pass through the disc spring (11) at the position where it passes through the trapezoidal pressure cap (10). A flat dumbbell-shaped storage rack (14) is installed on the upper side of the two disc springs (11). The two ends of the storage rack (14) pass through the top ends of the two first section rods (2). A level (13) is provided in the middle of the storage rack (14). The top end of the first section rod (2) is used to lock the storage rack (14), the disc spring (11) and the trapezoidal pressure cap (10) through a nut (12).

4. The stacked satellite fixing device according to claim 1, characterized in that: An arch support member (4) is provided between the two middle rods (1), and mechanical interfaces adapted to the two slots (15) of the middle rods (1) are provided at both ends of the arch support member (4), so as to clamp the two middle rods (1) together through a threaded connection.

5. The stacked satellite fixing device according to claim 1, characterized in that: The middle section rod (1) is made of non-metallic material, and the first section rod (2) and the tail section rod (3) are made of alloy material.

6. The stacked satellite fixing device according to claim 1, characterized in that: The reinforcement frame (6) adopts a flat hollow reinforced structure.

7. The stacked satellite fixing device according to claim 1, characterized in that: There are a total of four groups of the middle section rods (1), the first section rods (2) and the tail section rods (3), which are evenly distributed, and each group includes two middle section rods (1), two first section rods (2) and two tail section rods (3).

8. A control method for a stacked satellite fixing device, characterized in that: The method comprises: Mounting an L-shaped hinge bracket (22) to the lower end surface of the rocket adapter (20), wherein one side of the L-shaped hinge bracket (22) is provided with a through hole for connecting to the rocket adapter (20), and the other side is provided with a mounting interface for the second hinge (8); Multiple satellites are stacked in sequence on the rocket adapter (20) through a load-bearing column (18), wherein the rocket adapter (20) is designed in a positive cone shape, and a boss is provided on the upper end surface, and the boss is composed of three circular bosses, one large and two small, wherein the large boss is located in the middle and is used to install the satellite load-bearing column (18), and the two small bosses are used to pass explosive bolts (21) to fix the bottom of the tail section rod (3); After the middle section rod (1), the first section rod (2) and the tail section rod (3) are connected and fixed by threaded connection of the head and tail flanges, used in pairs and forming a tension rod, the bottom of the tail section rod (3) is fixed at the small boss by the explosive bolt (21); Passing a trapezoidal pressure cap (10) equipped with a pressure sensor (9) through the two first-section rods (2) until the lower end surface of the pressure sensor (9) is in contact with the satellite bearing column (18) and embedded into the inner side of the flange of the satellite bearing column (18), wherein the middle portion of the trapezoidal pressure cap (10) is concave upward to form a cylindrical groove, and the pressure sensor (9) is fixedly connected to the trapezoidal pressure cap (10) on the upper side in the cylindrical groove by means of a threaded connection; The two pairs of first hinges (7) and the two pairs of second hinges (8) are respectively mounted to the interfaces on the upper and lower sides of the reinforcement frame (6), wherein the two first hinges (7) are mounted at the arch back position of the arched transfer beam (5), and the reinforcement frame (6) is mounted at the oblique lower side of the two first hinges (7). The upper and lower sides of the reinforcement frame (6) are respectively provided with two sets of hinge mounting interfaces, the upper side is connected to the two first hinges (7), and the lower side is connected to the two second hinges (8); The two ends of the arched transfer beam (5) are provided with mechanical interfaces adapted to the two slots (16) at the bottom of the tail section rod (3), and the two tail section rods (3) are clamped by threaded connection. The rotation angles of the first hinge (7) and the second hinge (8) are adjusted so that the arched transfer beam (5) and the L-shaped hinge bracket (22) are connected at the same time, thereby completing the fixation of the stacked satellite fixing device.

9. The control method of the stacked satellite fixing device according to claim 8, characterized in that: The method further comprises: After the launch vehicle enters orbit, the explosive bolt (21) is controlled to be unlocked, so that the first hinge (7) and the second hinge (8) start to perform an unfolding action under the joint action. During the unfolding action, the stacked satellite fixing device first moves obliquely upward, so that the part pressed on the uppermost satellite bearing column (18) is separated from the groove in the flange of the satellite bearing column (18). At the same time, the relative angle between the tension rod and the reinforcement frame (6) also changes accordingly. When the stacked satellite fixing device moves to a certain position, the first hinge (7) is locked, so that the stacked satellite fixing device and the reinforcement frame (6) no longer move relative to each other. After the first hinge (7) is locked, the fixing device of the stacked satellite becomes a set of single-axis rotation mechanisms. Under the action of the second hinge (8), it is flipped at a certain angle and then locked, and is evenly distributed around the last stage of the launch vehicle and maintains a certain safety distance from the last stage of the launch vehicle, thereby completing the deployment of the fixing device of the stacked satellite.

10. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores a plurality of instructions, and the instructions are suitable for being loaded by a processor to execute the method of claim 8 or 9.

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