Telescopic mechanism for preventing vibration of a hundred-meter ring cylinder antenna

Abstract

The invention discloses a telescopic mechanism for preventing vibration of a hundred-meter ring column antenna, and relates to the field of mechanical structure design. The invention is used to solve the problem that the existing connecting structure between the antenna and the satellite platform is large and heavy, which affects the orbiting and stability of the satellite. Each limiting cover telescopic mechanism comprises two telescopic link mechanisms with the same structure and one 1 / 4 circular arc satellite limiting cover. The two telescopic link mechanisms are arranged side by side and are both in sliding connection with the outer arc wall of the 1 / 4 circular arc satellite limiting cover. The four 1 / 4 circular arc satellite limiting covers are spliced into a circle through a locking mechanism and are held on the antenna. The locking mechanism is provided with an explosive bolt for explosively disconnecting the connection between every two adjacent limiting cover telescopic mechanisms. When all the telescopic link mechanisms are synchronously contracted, a space is left between the antenna and the fairing. When all the telescopic link mechanisms are synchronously extended, all the telescopic link mechanisms are supported on the fairing. The invention is used for preventing antenna vibration.

Description

Technical Field

[0001] The invention relates to the field of mechanical structure design and belongs to a folding structure. Background Art

[0002] With the continuous advancement of aerospace technology, the demand for space exploration and communication missions is growing, and the requirements for antenna size, functionality, and performance are significantly increasing. Currently, antenna design is trending towards larger sizes, especially in deep space exploration, broadband communications, and scientific experiments. Hundred-meter-class antennas hold enormous potential for application. The size advantage of these antennas enables them to provide extended range, higher-resolution signal coverage, and data transmission capabilities in space environments, significantly enhancing the effectiveness of satellite platforms.

[0003] like Figure 1 As shown, the antenna 6 is set on the satellite platform 8, and the fairing 7 is covered on the outside of the antenna 6 and the satellite platform 8 to protect the antenna 6 and the satellite platform 8. The antenna 6, the satellite platform 8 and the fairing 7 are brought into the atmosphere by a multi-stage rocket 9 located at the bottom of the satellite platform 8; when the rocket rushes out of the atmosphere, the fairing 7 is separated, and the antenna 6 and the satellite platform 8 enter the predetermined orbit.

[0004] The 100-meter-class ring-shaped column antenna is a potential key antenna structure, and its envelope size can reach 100 meters when deployed. However, the antenna needs to be in a retracted state before launch to accommodate the size limitations of the current launch vehicle's fairing. Existing research shows that the retracted antenna can still reach a height of more than 10 meters and a diameter of more than 5 meters, which far exceeds the launch capability of China's current launch vehicles. The diameter of the current launch vehicle fairing is generally around 5 meters. To launch a 100-meter-class antenna, the fairing size and payload capacity of future rockets must be significantly increased, which undoubtedly places higher demands on the launch system.

[0005] In existing technologies, fixing and preventing vibrations in antennas during launch is typically accomplished by adding a connecting structure between the antenna's exterior and the satellite platform to provide support and stability during launch. While this solution can mitigate significant antenna vibrations to a certain extent, it also has the following significant drawbacks:

[0006] The weight and size of the connecting structure: Since the antenna itself is already quite large and heavy, the additional connecting structure inevitably increases the mass of the entire system. This places higher demands on the rocket's launch capability. Especially given the limited launch capacity, ensuring a successful launch without sacrificing payload becomes a major challenge.

[0007] Reliability of the discard mechanism: after the antenna and satellite platform enter the predetermined orbit, the connecting structure usually needs to be discarded so that the antenna can be smoothly deployed. However, the connecting structure is often designed to be large and heavy, and the reliability of the discarding process may be affected by various factors, such as mechanism jamming, insufficient discarding torque, etc. If the connecting structure cannot be discarded smoothly, it may hinder the deployment of the antenna, or even collide with the satellite platform, increasing the risk of satellite failure. In addition, the discarding process of the large-size connecting structure is prone to increase the control difficulty, thereby further affecting the orbiting and stability of the satellite platform and the antenna. SUMMARY

[0008] The purpose of the present application is to solve the problem that the existing connecting structure between the antenna outside and the satellite platform is large and heavy for relieving the large amplitude vibration of the antenna, affecting the orbiting and stability of the satellite. A telescopic mechanism for preventing the vibration of a hundred-meter ring column antenna is proposed.

[0009] The telescopic mechanism for preventing the vibration of a hundred-meter ring column antenna, the fixed end of the telescopic mechanism is fixed on the inner wall of the fairing, and the free end is used to hold or release the antenna in the fairing. The antenna is arranged on the satellite platform. The telescopic mechanism comprises one or more fixed protection devices, a locking mechanism and an explosive bolt.

[0010] Each fixed protection device comprises four limit shield telescopic mechanisms. Each limit shield telescopic mechanism comprises two telescopic link mechanisms with the same structure and one 1 / 4 circular satellite limit shield.

[0011] The two telescopic link mechanisms are arranged side by side and are both in sliding connection with the outer arc wall of the 1 / 4 circular satellite limit shield. The four 1 / 4 circular satellite limit shields are spliced into a circle by the locking mechanism and held on the antenna. The locking mechanism is provided with an explosive bolt for explosively disconnecting the connection of every two adjacent limit shield telescopic mechanisms.

[0012] When all the telescopic link mechanisms are synchronously contracted, a space is left between the antenna and the fairing. When all the telescopic link mechanisms are synchronously extended, all the telescopic link mechanisms are supported on the fairing.

[0013] Preferably, each telescopic link mechanism comprises an upper rod assembly, a lower rod assembly, a connecting seat and a connecting piece.

[0014] The upper rod assembly has telescopic function. One end of the upper rod assembly and one end of the lower rod assembly are both rotationally connected to the connecting seat, and the rotation directions of the upper rod assembly and the lower rod assembly are the same. The upper rod assembly can also slide forward and backward along the connecting seat. The other end of the upper rod assembly and the other end of the lower rod assembly are both fixed as the fixed end of the telescopic mechanism on the inner wall of the fairing.

[0015] The connecting seat is connected to the arc-shaped outer wall of the 1 / 4 circular satellite limit shield through the connecting piece.

[0016] Preferably, the upper rod assembly includes a fixed hinge support, a No. 1 hinge rod end, a No. 1 damper, a No. 1 coupling and an electric push rod;

[0017] The upper fixed hinge support is fixed on the inner wall of the fairing, one end of the No. 1 hinge rod is hinged to the upper fixed hinge support, one end of the No. 1 damper is fixedly connected to the other end of the No. 1 hinge rod, the other end of the No. 1 damper is fixedly connected to one end of the electric push rod through the No. 1 coupling, and the other end of the electric push rod is rotatably connected to the connecting seat.

[0018] Preferably, the lower rod assembly comprises a lower fixed hinge support, a No. 1 DC motor, a No. 2 hinge rod end, a No. 2 damper, a No. 2 coupling and an articulated rod;

[0019] The lower fixed hinge support is supported on the fairing, one end of the No. 2 hinge rod end is hinged to the lower fixed hinge support, the No. 1 DC motor is used to drive the hinge rod end to perform circular motion around the hinge, one end of the No. 2 damper is fixedly connected to the other end of the No. 2 hinge rod end, the other end of the No. 2 damper is fixedly connected to one end of the hinge rod through the No. 2 coupling, and the other end of the hinge rod is rotatably connected to the connecting seat.

[0020] Preferably, the connecting seat includes a three-way connecting rod, a left bend pipe No. 1, a right bend pipe No. 1, a left slide rod, a right slide rod, a left sleeve, a right sleeve, a left bend pipe No. 2, a right bend pipe No. 2 and a three-way coupling;

[0021] The hinge rod is connected to one end of the first left curved pipe and one end of the first right curved pipe through a hinge pin, and the hinge rod can rotate around the hinge pin;

[0022] The other end of the electric push rod is fixedly connected to the three-way connecting rod. The left and right ends of the three-way connecting rod are respectively inserted into one end of the left sleeve and one end of the right sleeve. The other end of the left sleeve extends into the slide groove of the left slide rod, and the other end of the right sleeve extends into the slide groove of the right slide rod. The left sleeve and the right sleeve can slide along their respective slide grooves, thereby causing the three-way connecting rod to move along the slide groove direction.

[0023] The other end of the No. 1 left bend pipe is fixedly connected to one end of the left slide rod, and the other end of the left slide rod is fixedly connected to one end of the No. 2 left bend pipe. Symmetrically, the other end of the No. 1 right bend pipe is fixedly connected to one end of the right slide rod, and the other end of the right slide rod is fixedly connected to one end of the No. 2 right bend pipe. The other end of the No. 2 left bend pipe and the other end of the No. 2 right bend pipe are connected to the connecting piece through a three-way coupling.

[0024] Preferably, the connecting member includes a No. 3 damper, a No. 3 coupling and an end connecting rod;

[0025] The three-way coupling is fixedly connected to one end of the No. 3 damper, and the other end of the No. 3 damper is fixedly connected to one end of the terminal connecting rod through the No. 3 coupling.

[0026] Preferably, the satellite limiting shield of the 1 / 4 circular arc comprises a 1 / 4 circular arc piece and a limiting mechanism;

[0027] The limiting mechanism comprises a limiting block and two sliding blocks;

[0028] The limiting block is fixed in the middle of the outer wall of the 1 / 4 circular arc piece, a sliding groove is formed in the side wall of the limiting block, and the limiting block is embedded in the sliding groove; the other end of each end link is hingedly connected with a sliding block.

[0029] Preferably, the electric push rod comprises a No. 2 DC motor, a gear box, a lead screw, an upper push rod and a lower push rod;

[0030] The No. 1 coupling is connected with the shell of the No. 2 DC motor,

[0031] The output shaft of the No. 2 DC motor is connected with the lead screw through the gear box to drive the rotation of the lead screw; the lower push rod is sleeved on the lead screw; the lower push rod is externally sleeved with a sliding member; the upper push rod is a hollow frame body, the inner wall of which is connected with a sliding rail; the sliding member slides along the sliding rail to drive the extension and contraction of the upper push rod; the top of the upper push rod is fixed on the gear box and is sleeved outside the lower push rod; the lower push rod is fixedly connected with the three-way link outside the bottom of the upper push rod.

[0032] Preferably, the locking mechanism comprises a locking limiting cylinder, two elastic components and a locking chuck;

[0033] The locking limiting cylinder and the locking chuck are respectively fixedly connected on the two opposite ends of each adjacent two 1 / 4 circular arc pieces;

[0034] The two elastic components are oppositely arranged on the locking limiting cylinder, and the tips thereof are in the locking limiting cylinder,

[0035] After the locking chuck extrudes the tips of the two elastic components, the locking chuck is inserted into the locking limiting cylinder to realize the locking of the locking mechanism.

[0036] Preferably, the material of the 1 / 4 circular arc piece is composed of three layers, from outside to inside, which are aluminum plate, rubber and sponge.

[0037] The beneficial effects of the present application are:

[0038] The present application aims to solve the problem that the existing technology is difficult to safely and stably send a hundred-meter ring antenna into space by a carrier rocket. In view of the problems of huge size in the antenna retracted state, large vibration in the launching process and mass, reliability and other problems existing in the traditional connection structure, the present application provides a telescopic mechanism for preventing vibration of a hundred-meter ring antenna. The design ensures that the antenna can be effectively fixed and protected during the launching process through the close integration of the fairing and the antenna, thereby improving the safety and stability during the launching process.

[0039] During rocket assembly, a retractable mechanical structure is installed on the inner wall of the fairing to automatically secure the antenna in its retracted position during launch. This automatic retraction and locking mechanism prevents interference between the antenna and the fairing during launch, eliminating the potential collision risk associated with conventional antennas and fairings during assembly and launch.

[0040] Before launch, the telescopic mechanism is in a retracted state to ensure sufficient space between the antenna and the fairing to avoid interfering with the assembly of the fairing. When the rocket is assembled, the telescopic mechanism automatically extends to secure the antenna to the inner wall of the fairing. Multiple locking points provide all-round support and protection for the antenna to prevent displacement or damage to the antenna due to vibration during launch. At the same time, a damper device is integrated into the mechanical structure to effectively absorb vibration energy during launch, further reducing the force on the antenna during launch and improving the system's vibration resistance. Through the use of dampers, the vibration environment of the antenna inside the fairing is improved, which helps reduce structural stress and fatigue damage to the satellite and improve the reliability of the entire launch mission.

[0041] As the rocket exits the atmosphere and prepares to separate the fairing, the retractor's automatic unlocking function activates, retracting the mechanism and allowing the fairing to smoothly detach from the antenna without affecting subsequent antenna deployment. At this point, the fairing and retractor are jettisoned together, avoiding the risk of jettisoning failure or collision with the antenna that can occur with traditional connection structures.

[0042] This design significantly reduces the weight of the launch system while also improving the stability and safety of the antenna during launch, resolving the challenges of securing and isolating large antennas during launch. This solution offers fully automated operation, enabling an unmanned launch process and ensuring system reliability and antenna safety at critical launch points.

[0043] The present invention provides an innovative solution for the transmission of future 100-meter-class ring-column antennas, and has significant application value and prospects in solving the technical difficulties in large-scale antenna transmission.

[0044] By introducing technologies such as dual-motor control, a multi-degree-of-freedom rod system, and a three-series damping and shock absorption system, the antenna is securely fixed during launch, vibrations are effectively suppressed, and launch stability is greatly improved. At the same time, the automated limit-protection shield retraction design and safety locking mechanism simplify the separation process between the antenna and the fairing, reducing the risk of collision and damage. Furthermore, the three-layer protective material design and highly integrated solution further optimize the system's space utilization efficiency and safety. This invention not only solves the launch challenge of large-scale antennas, but also provides reliable technical support for larger and more complex space communications and exploration missions in the future, and has broad application prospects.

[0045] In summary, this patent addresses the launch fixation and vibration prevention of a hundred-meter ring antenna, proposing an innovative integrated design that breaks through the limitations of existing connection structures. By combining the use of mechanical structures inside the fairing and dampers, this design reduces system weight while ensuring vibration suppression effects for the antenna, providing a new solution for large antenna launches. In future large satellite antenna launch missions, this patent design is expected to become one of the key technologies.

[0046] Dual-motor control design (No. 1 DC motor and No. 2 DC motor): enhances the stability of the fairing and antenna mechanical operation, significantly improves energy utilization efficiency during launch, and reduces the risk of operation failure in complex environments.

[0047] Multi-degree-of-freedom linkage design (telescopic linkage mechanism): has high flexibility and adaptability, can achieve complex motion control, withstands large loads and external environmental changes, enhancing the stability and adaptability of the system during launch.

[0048] Three-series damper shock absorption system (No. 1 damper, No. 2 damper, and No. 3 damper): effectively absorbs vibration energy generated during launch, quickly disperses vibration impact, ensures system stability, and improves the safety and reliability of the antenna during launch and orbit insertion.

[0049] Limiting shield vertical telescopic design: solves the interference problem between the antenna inside the fairing and other components, avoids interference and collision during launch or separation, and ensures smooth operation of the system.

[0050] Safety locking mechanism design: improves the stability and reliability of the antenna during fairing separation, reducing the risk of antenna deployment failure or damage due to insecure locking.

[0051] Compact design and high integration: reduces the volume and weight of system equipment, improves space utilization efficiency, and is suitable for rocket launch tasks with limited carrying capacity.

[0052] Full-automatic docking locking and unlocking system: realizes full automation, simplifies the installation and disassembly process of the system, is suitable for complex launch tasks, and reduces the risk of human intervention.

[0053] Satellite and rocket integrated innovative design: optimizes the combination of rockets and antenna systems, solves the technical bottleneck of current launch vehicles that cannot effectively accommodate large antennas, and improves the feasibility of large antenna launches. BRIEF DESCRIPTION OF DRAWINGS

[0054] Figure 1 Overall assembly drawing of the fairing;

[0055] Figure 2 This is a diagram showing the expansion method of the telescopic mechanism of the limit guard. In the figure, Figure 2 (a) Figure 2 (b) and 2(c) are diagrams of three unfolded states;

[0056] Figure 3 It is the diagram of telescopic linkage mechanism;

[0057] Figure 4 This is a detailed view of the hinged part;

[0058] Figure 5 This is a detailed diagram of the three-way connecting rod;

[0059] Figure 6 This is a detailed diagram of the connection part of the limit guard;

[0060] Figure 7 This is a detailed picture of the electric push rod;

[0061] Figure 8 This is a structural diagram of two adjacent 1 / 4 arcs being locked by a locking mechanism;

[0062] Figure 9 for Figure 8 A partial enlarged view of the middle A;

[0063] Figure 10 This is the overall diagram of the locking mechanism. Figure 10 (a) is the structural diagram of the locking mechanism when it is locked. Figure 10 (b) is a cross-sectional view of the locking mechanism;

[0064] Figure 11 for Figure 10 (b) A local enlarged view of point B;

[0065] Figure 12 This is the locking action diagram of the locking mechanism. In the figure, Figure 12 (a) is the state diagram of the locking mechanism before locking. Figure 12 (b) is a diagram showing the locking mechanism in a state where it is about to be locked;

[0066] Figure 13 is a perspective view of the locking mechanism in a locked state;

[0067] Figure 14 This is the material composition diagram of the 1 / 4 arc piece. DETAILED DESCRIPTION

[0068] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making any creative efforts shall fall within the scope of protection of the present invention.

[0069] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments may be combined with each other.

[0070] The present invention will be further described below with reference to the accompanying drawings and specific embodiments, but they are not intended to limit the present invention.

[0071] Example:

[0072] Combine Figures 1 to 3 、 Figure 8 and Figure 9 This embodiment describes a telescopic mechanism for preventing vibration of a 100-meter-class ring-column antenna. The fixed end of the telescopic mechanism is fixed to the inner wall of the fairing 7, and the free end is used to hold or release the antenna 6 within the fairing 7. The antenna 6 is installed on the satellite platform 8. The telescopic mechanism includes one or more fixing protection devices, a locking mechanism 2, and an explosive bolt 3.

[0073] Each fixed protection device includes four limiting shield telescopic mechanisms 1, and each limiting shield telescopic mechanism 1 includes two telescopic link mechanisms 4 with the same structure and a 1 / 4 arc satellite limiting shield 5;

[0074] Two telescopic link mechanisms 4 are arranged side by side and are both slidably connected to the outer arc wall of the 1 / 4 arc satellite limit shield 5; the four 1 / 4 arc satellite limit shields 5 are spliced ​​into a circle through the locking mechanism 2 and are held on the antenna 6; the locking mechanism 2 is provided with an explosive bolt 3 for explosively disconnecting the connection between each two adjacent limit shield telescopic mechanisms 1;

[0075] When all the telescopic link mechanisms 4 are retracted synchronously, space is left between the antenna 6 and the fairing 7 . When all the telescopic link mechanisms 4 are extended synchronously, all the telescopic link mechanisms 4 are supported on the fairing 7 .

[0076] Specifically, this embodiment is mainly used for fixing the 100-meter-class ring column antenna during the transmission phase. The overall effect is as follows: Figure 1 As shown. Under the action of the telescopic link mechanism, the satellite limit shield can be expanded and contracted vertically along the radial direction of the fairing. The process is as follows Figure 2 As shown. After the four 1 / 4 satellite limit shields are deployed into place, Figure 8 The locking mechanism shown in the figure is docked and locked to form a complete satellite limit shield. Figure 12As shown. To unlock, use the explosive bolt 3 to separate the locking mechanism.

[0077] The following combination Figure 3 Introducing the structure of the telescopic link mechanism 4:

[0078] Each telescopic link mechanism 4 includes an upper rod assembly 4-1, a lower rod assembly 4-2, a connecting seat 4-3 and a connecting piece 4-4;

[0079] The upper rod assembly 4-1 has a telescopic function. One end of the upper rod assembly 4-1 and one end of the lower rod assembly 4-2 are both rotatably connected to the connecting seat 4-3, and the upper rod assembly 4-1 and the lower rod assembly 4-2 rotate in the same direction. The upper rod assembly 4-1 can also slide back and forth along the connecting seat 4-3. The other end of the upper rod assembly 4-1 and the other end of the lower rod assembly 4-2 are both fixed to the inner wall of the fairing 7 as fixed ends of the telescopic mechanism.

[0080] The connecting seat 4 - 3 is connected to the arc-shaped outer wall of the 1 / 4 arc satellite limiting shield 5 through the connecting piece 4 - 4 .

[0081] The structure of the upper rod assembly 4-1 is introduced below:

[0082] The upper rod assembly 4-1 includes a fixed hinge support 4-1-1, a No. 1 hinge rod end 4-1-2, a No. 1 damper 4-1-3, a No. 1 coupling 4-1-4 and an electric push rod 4-1-5;

[0083] The upper fixed hinge support 4-1-1 is supported on the fairing, one end of the No. 1 hinge rod end 4-1-2 is hinged to the upper fixed hinge support 4-1-1, one end of the No. 1 damper 4-1-3 is fixedly connected to the other end of the No. 1 hinge rod end 4-1-2, the other end of the No. 1 damper 4-1-3 is fixedly connected to one end of the electric push rod 4-1-5 through the No. 1 coupling 4-1-4, and the other end of the electric push rod 4-1-5 is rotatably connected to the connecting seat 4-3.

[0084] Specifically, the fixed hinge support 4-1-1 is used to fit on the inner wall surface of the fairing, and the electric push rod 4-1-5 can be extended and retracted, thereby allowing the upper rod assembly 4-1 to extend and retract.

[0085] The following combination Figure 3 Introducing the structure of the lower rod assembly 4-2:

[0086] The lower rod assembly 4-2 includes a lower fixed hinge support 4-2-1, a No. 1 DC motor 4-2-2, a No. 2 hinge rod end 4-2-3, a No. 2 damper 4-2-4, a No. 2 coupling 4-2-5 and a hinge rod 4-2-6;

[0087] The lower fixed hinge support 4-2-1 is supported on the fairing, one end of the No. 2 hinge rod end 4-2-3 is hinged to the lower fixed hinge support 4-2-1, the No. 1 DC motor 4-2-2 is used to drive the hinge rod end 4-2-3 to perform circular motion around the hinge, one end of the No. 2 damper 4-2-4 is fixedly connected to the other end of the No. 2 hinge rod end 4-2-3, the other end of the No. 2 damper 4-2-4 is fixedly connected to one end of the hinge rod 4-2-6 through the No. 2 coupling 4-2-5, and the other end of the hinge rod 4-2-6 is rotatably connected to the connecting seat 4-3.

[0088] The following combination Figures 3 to 5 Introducing the structure of connector 4-3:

[0089] The connecting seat 4-3 includes a three-way connecting rod 4-3-1, a left curved pipe 4-3-2, a right curved pipe 4-3-3, a left sliding rod 4-3-4, a right sliding rod 4-3-5, a left sleeve 4-3-6, a right sleeve 4-3-7, a second left curved pipe 4-3-8, a second right curved pipe 4-3-9 and a three-way coupling 4-3-10;

[0090] The hinge rod 4-2-6 is connected to one end of the No. 1 left curved pipe 4-3-2 and one end of the No. 1 right curved pipe 4-3-3 through the hinge pin 4-3-11. The hinge rod 4-2-6 can rotate around the hinge pin 4-3-11.

[0091] The other end of the electric push rod 4-1-5 is fixedly connected to the three-way connecting rod 4-3-1. The left and right ends of the three-way connecting rod 4-3-1 are respectively inserted into one end of the left sleeve 4-3-6 and one end of the right sleeve 4-3-7. The other end of the left sleeve 4-3-6 extends into the slide groove of the left slide rod 4-3-4, and the other end of the right sleeve 4-3-7 extends into the slide groove of the right slide rod 4-3-5. The left sleeve 4-3-6 and the right sleeve 4-3-7 can slide along their respective slide grooves, thereby causing the three-way connecting rod 4-3-1 to move along the slide groove direction.

[0092] The other end of the No. 1 left bend pipe 4-3-2 is fixedly connected to one end of the left slide rod 4-3-4, the other end of the left slide rod 4-3-4 is fixedly connected to one end of the No. 2 left bend pipe 4-3-8, symmetrically, the other end of the No. 1 right bend pipe 4-3-3 is fixedly connected to one end of the right slide rod 4-3-5, the other end of the right slide rod 4-3-5 is fixedly connected to one end of the No. 2 right bend pipe 4-3-9, the other end of the No. 2 left bend pipe 4-3-8 and the other end of the No. 2 right bend pipe 4-3-9 are connected to the connecting piece 4-4 through a three-way coupling 4-3-10.

[0093] Specifically, the electric push rod 4-1-5 can rotate around the three-way connecting rod. A locking mechanism is provided in the chute to lock the left and right sleeves in corresponding positions in the chute, thereby restricting the left and right sleeves to prevent them from sliding freely in the chute and failing to support the fairing.

[0094] The following combination Figure 3 Introducing the structure of connector 4-4:

[0095] The connecting member 4-4 includes a No. 3 damper 4-4-1, a No. 3 coupling 4-4-2 and an end connecting rod 4-4-3;

[0096] The three-way coupling 4-3-10 is fixedly connected to one end of the No. 3 damper 4-4-1, and the other end of the No. 3 damper 4-4-1 is fixedly connected to one end of the end connecting rod 4-4-3 through the No. 3 coupling 4-4-2.

[0097] The following combination Figure 6 Introducing the structure of the 1 / 4 arc satellite limiting shield 5:

[0098] The 1 / 4 arc satellite limiting shield 5 includes a 1 / 4 arc piece 5-1 and a limiting mechanism 5-2;

[0099] The limiting mechanism 5-2 includes a limiting block 5-2-1 and two sliders 5-2-2;

[0100] The limit block 5-2-1 is fixed to the middle of the outer wall of the 1 / 4 arc piece 5-1. A sliding groove is provided on the side wall of the limit block 5-2-1. The limit block 5-2-1 is embedded in the sliding groove. The other end of each end connecting rod 4-4-3 is hinged to a slider 5-2-2.

[0101] The following combination Figure 7 Introducing the structure of electric linear actuator 4-1-5:

[0102] The electric push rod 4-1-5 includes a No. 2 DC motor 4-1-5-1, a gear box 4-1-5-2, a lead screw 4-1-5-3, an upper push rod 4-1-5-4 and a lower push rod 4-1-5-5;

[0103] The No. 1 coupling 4-1-4 is connected to the housing of the No. 2 DC motor 4-1-5-1.

[0104] The output shaft of the No. 2 DC motor 4-1-5-1 is connected to the screw through the gear box 4-1-5-2, driving the screw to rotate. The lower push rod 4-1-5-5 is sleeved on the screw. A sliding part is sleeved on the outside of the lower push rod 4-1-5-5. The upper push rod 4-1-5-4 is a hollow frame, the inner wall of which is connected to the slide rail, and the sliding part slides along the slide rail. The upper push rod 4-1-5-4 is connected to the box body of the gear box 4-1-5-2 and is sleeved on the outside of the upper push rod 4-1-5-4. The end of the lower push rod 4-1-5-5 extends out of the upper push rod 4-1-5-4 and is fixedly connected to the three-way connecting rod 4-3-1.

[0105] Specifically, the torque of the gear box 4-1-5-2 is large, so the use of the gear box enables the electric push rod 4-1-5 to achieve a better telescopic function.

[0106] The following combination Figures 8 to 13 Introducing the structure of the locking mechanism 2:

[0107] The locking mechanism 2 includes a locking limit cylinder 2-1, two elastic components 2-2 and a locking clamp 2-3;

[0108] The two opposite ends of each two adjacent 1 / 4 arc pieces 5-1 are respectively fixedly connected to the locking limit cylinder 2-1 and the locking clamp 2-3;

[0109] The two elastic components 2-2 are relatively arranged on the locking limit cylinder 2-1, and their tips are located inside the locking limit cylinder 2-1.

[0110] After the locking chuck 2-3 squeezes the tips of the two elastic components 2-2, it is inserted into the locking limit cylinder 2-1 to lock the locking mechanism 2.

[0111] Combine Figure 14 Introducing the material composition of 1 / 4 arc sheet 5-1:

[0112] The material of the 1 / 4 arc piece 5-1 consists of three layers, which are, from the outside to the inside, an aluminum plate 5-1-1, rubber 5-1-2 and sponge 5-1-3.

[0113] Working principle:

[0114] The new fairing and the integrated device of the 100-meter-class ring column antenna in the folded state, such as Figure 1 The following will explain how to achieve the deployment, locking, unlocking and recovery of the satellite limit shield through the limit shield telescopic mechanism.

[0115] Step 1: Fairing Assembly. The limited shield retractable mechanism 1 remains retracted, close to the fairing. The fairing is assembled into the rocket as normal.

[0116] Step 2: Motor drive: The controller sends a command and transmits it to the No. 1 DC motor 4-2-2 and the No. 2 DC motor 4-1-5-1 through serial communication. The No. 1 DC motor 4-2-2 and the No. 2 DC motor 4-1-5-1 start.

[0117] Step 3: The lower rod assembly swings. The No. 1 DC motor 4-2-2 drives the No. 2 hinge rod end 4-2-3 of the lower rod assembly to make a circular motion around the hinge, driving the No. 2 damper 4-2-4 and the hinge rod 4-2-6 connected to it to swing.

[0118] Step 4: Electric push rod 4-1-5 shortens. The second DC motor 4-1-5-1 starts, and drives the lead screw 4-1-5-3 to rotate through 4-1-5-2, causing the lower push rod 4-1-5-5 to shorten inward.

[0119] Step 5: The three-way connecting rod 4-3-1 slides. Under the action of the electric push rod 4-1-5, the three-way connecting rod 4-3-1 will drive the left sleeve 4-3-6 and the right sleeve 4-3-7 to roll in the left slide rod 4-3-4 and the right slide rod 4-3-5, further causing the upper rod assembly to swing.

[0120] Step 6: Extend the rod assembly to perform planar motion. Under the combined action of the upper and lower rod assemblies and the dual motors, the extended rod assembly, namely the No. 1 left curved tube 4-3-2, the No. 1 right curved tube 4-3-3, the left slide rod 4-3-4, the right slide rod 4-3-5, the left sleeve 4-3-6, the right sleeve 4-3-7, the No. 2 left curved tube 4-3-8, the No. 2 right curved tube 4-3-9, the three-way coupling 4-3-10, and the end link 4-4-3, will perform planar motion, ensuring that the plane is always parallel to the satellite mounting platform. This ensures that the satellite limit shield is always parallel to the satellite antenna, avoiding interference with the satellite antenna during expansion or contraction.

[0121] Step 7: Slider slides. During the deployment process, the radius of the circle where the 1 / 4 satellite limit shield 5 is located continues to shrink. Since the mounting bracket is fixedly connected and the linkage mechanism does not include the degree of freedom in the tangential direction of the fairing, the slider 5-2-2 connected to the end link 4-4-3 will slide outward in the groove of the 1 / 4 satellite limit shield.

[0122] Step eight: satellite limiting shield docking. After the limiting shield telescopic mechanism is fully deployed, four 1 / 4 satellite limiting shields 5 will combine into a complete satellite limiting shield. When the adjacent two 1 / 4 satellite limiting shields 5 gradually approach and prepare to lock, the locking chuck 2-3 pushes the locking rod 2-2-1 to move outward, and at this time the return spring 2-2-2 is compressed. With the locking chuck 2-3 further advancing, when the inclined surface of the locking rod 2-2-1 is no longer in contact with the front end arc surface of the locking chuck 2-3, the return spring 2-2-2 is released, and the locking rod 2-2-1 is pushed inward by the elastic force of the return spring 2-2-2 until the two locking rods 2-2-1 clamp the middle rod of the locking chuck 2-3, achieving locking.

[0123] Step nine: rocket launch. The satellite limiting shield locking mechanism remains locked, providing continuous buffer protection for the hundred-meter ring cylinder antenna during the rocket launch process.

[0124] Step ten: locking mechanism unlocking. Before the rocket fairing separates, the explosive bolt 3 explodes and breaks, and the locking chuck 2-3 is disconnected from the 1 / 4 satellite limiting shield, thereby realizing the separation of the adjacent two 1 / 4 satellite limiting shields.

[0125] Step eleven: telescopic mechanism retraction. Similar to the deployment process, under the action of the double motors, the 1 / 4 satellite limiting shield gradually moves away from the satellite while maintaining a parallel attitude with the satellite antenna, until it returns to the initial state.

[0126] Step twelve: fairing separation. The fairing separates from the rocket under the action of the explosive bolt.

[0127] Although the present application is described herein with reference to particular embodiments, it is to be understood that these examples are merely illustrative of principles and applications of the present application. It should therefore be understood that numerous modifications can be made to the illustrative embodiments and that other arrangements can be devised without departing from the spirit and scope of the present application as defined by the appended claims. It should be understood that the features described in connection with one embodiment can be used in conjunction with other embodiments described herein. It should be understood that the features described in connection with one embodiment can be used in conjunction with other embodiments described herein.

Claims

1. A telescopic mechanism for preventing vibration of a hundred-meter-class ring column antenna, wherein the fixed end of the telescopic mechanism is fixed to the inner wall of a fairing (7), and the free end is used to hold or release an antenna (6) in the fairing (7), and the antenna (6) is arranged on a satellite platform (8), characterized in that: The telescopic mechanism comprises one or more fixing protection devices, a locking mechanism (2) and an explosive bolt (3); Each fixed protection device includes four position-limiting guard telescopic mechanisms (1), and each position-limiting guard telescopic mechanism (1) includes two telescopic link mechanisms (4) of identical structure and a satellite position-limiting guard (5) of 1 / 4 arc; Two telescopic link mechanisms (4) are arranged side by side and are both slidably connected to the outer arc wall of a 1 / 4 arc satellite limiting shield (5); four 1 / 4 arc satellite limiting shields (5) are spliced ​​into a circle through a locking mechanism (2) and are held on the antenna (6); an explosive bolt (3) is provided on the locking mechanism (2) for explosively disconnecting the connection between each two adjacent limiting shield telescopic mechanisms (1); When all the telescopic link mechanisms (4) are synchronously retracted, a space is left between the antenna (6) and the fairing (7); when all the telescopic link mechanisms (4) are synchronously extended, all the telescopic link mechanisms (4) are supported on the fairing (7).

2. The telescopic mechanism for preventing vibration of a 100-meter-class ring column antenna according to claim 1, characterized in that: Each telescopic connecting rod mechanism (4) comprises an upper rod assembly (4-1), a lower rod assembly (4-2), a connecting seat (4-3) and a connecting piece (4-4); The upper rod assembly (4-1) has a telescopic function. One end of the upper rod assembly (4-1) and one end of the lower rod assembly (4-2) are both rotatably connected to the connecting seat (4-3). The upper rod assembly (4-1) and the lower rod assembly (4-2) rotate in the same direction. The upper rod assembly (4-1) can also slide forward and backward along the connecting seat (4-3). The other end of the upper rod assembly (4-1) and the other end of the lower rod assembly (4-2) are both fixed to the inner wall of the fairing (7) as fixed ends of the telescopic mechanism. The connecting seat (4-3) is connected to the arc-shaped outer wall of the 1 / 4 arc satellite limiting shield (5) through a connecting piece (4-4).

3. The telescopic mechanism for preventing vibration of a 100-meter-class ring column antenna according to claim 2, characterized in that: The upper rod assembly (4-1) includes a fixed hinge support (4-1-1), a No. 1 hinge rod end (4-1-2), a No. 1 damper (4-1-3), a No. 1 coupling (4-1-4) and an electric push rod (4-1-5); An upper fixed hinge support (4-1-1) is fixed on the inner wall of the fairing (7); one end of a No. 1 hinge rod end (4-1-2) is hinged to the upper fixed hinge support (4-1-1); one end of a No. 1 damper (4-1-3) is fixedly connected to the other end of the No. 1 hinge rod end (4-1-2); the other end of the No. 1 damper (4-1-3) is fixedly connected to one end of an electric push rod (4-1-5) via a No. 1 coupling (4-1-4); and the other end of the electric push rod (4-1-5) is rotatably connected to the connecting seat (4-3).

4. The telescopic mechanism for preventing vibration of a 100-meter-class ring column antenna according to claim 3, characterized in that: The lower rod assembly (4-2) includes a lower fixed hinge support (4-2-1), a No. 1 DC motor (4-2-2), a No. 2 hinge rod end (4-2-3), a No. 2 damper (4-2-4), a No. 2 coupling (4-2-5) and a hinge rod (4-2-6); The lower fixed hinge support (4-2-1) is supported on the fairing (7), one end of the second hinge rod end (4-2-3) is hinged to the lower fixed hinge support (4-2-1), the first DC motor (4-2-2) is used to drive the hinge rod end (4-2-3) to perform circular motion around the hinge, one end of the second damper (4-2-4) is fixedly connected to the other end of the second hinge rod end (4-2-3), the other end of the second damper (4-2-4) is fixedly connected to one end of the hinge rod (4-2-6) through the second coupling (4-2-5), and the other end of the hinge rod (4-2-6) is rotatably connected to the connecting seat (4-3).

5. The telescopic mechanism for preventing vibration of a hundred-meter-class ring-pillar antenna according to claim 4, characterized in that: The connecting seat (4-3) includes a three-way connecting rod (4-3-1), a left curved pipe (4-3-2), a right curved pipe (4-3-3), a left sliding groove rod (4-3-4), a right sliding groove rod (4-3-5), a left sleeve (4-3-6), a right sleeve (4-3-7), a second left curved pipe (4-3-8), a second right curved pipe (4-3-9) and a three-way coupling (4-3-10); The hinge rod (4-2-6) is connected to one end of the first left curved pipe (4-3-2) and one end of the first right curved pipe (4-3-3) through a hinge pin (4-3-11), and the hinge rod (4-2-6) can rotate around the hinge pin (4-3-11); The other end of the electric push rod (4-1-5) is fixedly connected to the three-way connecting rod (4-3-1). The left and right ends of the three-way connecting rod (4-3-1) are respectively inserted into one end of the left sleeve (4-3-6) and one end of the right sleeve (4-3-7). The other end of the left sleeve (4-3-6) extends into the slide groove of the left slide rod (4-3-4), and the other end of the right sleeve (4-3-7) extends into the slide groove of the right slide rod (4-3-5). The left sleeve (4-3-6) and the right sleeve (4-3-7) can slide along their respective slide grooves, thereby causing the three-way connecting rod (4-3-1) to move along the slide groove direction. The other end of the No. 1 left curved tube (4-3-2) is fixedly connected to one end of the left sliding slot rod (4-3-4), the other end of the left sliding slot rod (4-3-4) is fixedly connected to one end of the No. 2 left curved tube (4-3-8), symmetrically, the other end of the No. 1 right curved tube (4-3-3) is fixedly connected to one end of the right sliding slot rod (4-3-5), the other end of the right sliding slot rod (4-3-5) is fixedly connected to one end of the No. 2 right curved tube (4-3-9), and the other end of the No. 2 left curved tube (4-3-8) and the other end of the No. 2 right curved tube (4-3-9) are connected to the connecting piece (4-4) via a three-way coupling (4-3-10).

6. The telescopic mechanism for preventing vibration of a 100-meter-class ring column antenna according to claim 5, characterized in that: The connecting member (4-4) includes a No. 3 damper (4-4-1), a No. 3 coupling (4-4-2) and an end link (4-4-3); The three-way coupling (4-3-10) is fixedly connected to one end of the No. 3 damper (4-4-1), and the other end of the No. 3 damper (4-4-1) is fixedly connected to one end of the end connecting rod (4-4-3) through the No. 3 coupling (4-4-2).

7. The telescopic mechanism for preventing vibration of a 100-meter-class ring column antenna according to claim 6, characterized in that: The 1 / 4 arc satellite limiting shield (5) comprises a 1 / 4 arc piece (5-1) and a limiting mechanism (5-2); The limiting mechanism (5-2) includes a limiting block (5-2-1) and two sliders (5-2-2); The limit block (5-2-1) is fixed to the middle of the outer wall of the 1 / 4 arc piece (5-1), a sliding groove is provided on the side wall of the limit block (5-2-1), the limit block (5-2-1) is embedded in the sliding groove, and the other end of each end connecting rod (4-4-3) is hinged to a slider (5-2-2).

8. The telescopic mechanism for preventing vibration of a 100-meter-class ring column antenna according to claim 3, characterized in that: The electric push rod (4-1-5) includes a No. 2 DC motor (4-1-5-1), a gear box (4-1-5-2), a lead screw (4-1-5-3), an upper push rod (4-1-5-5) and a lower push rod (4-1-5-4); The No. 1 coupling (4-1-4) is connected to the housing of the No. 2 DC motor (4-1-5-1). The output shaft of the No. 2 DC motor (4-1-5-1) is connected to the lead screw (4-1-5-3) through the gear box (4-1-5-2), driving the lead screw (4-1-5-3) to rotate, the lower push rod (4-1-5-4) is sleeved on the lead screw, and a sliding member is sleeved on the outside of the lower push rod (4-1-5-4). The upper push rod (4-1-5-5) is a hollow frame, the inner wall of which is connected to the slide rail, and the sliding member slides along the slide rail, thereby driving the upper push rod (4-1-5-5) to extend and retract, the top of the upper push rod (4-1-5-5) is fixed on the gear box (4-1-5-2), and is sleeved on the outside of the lower push rod (4-1-5-4), and the lower push rod (4-1-5-4) extends out of the bottom of the upper push rod (4-1-5-5) and is fixedly connected to the three-way connecting rod (4-3-1).

9. The telescopic mechanism for preventing vibration of a 100-meter-class ring-pillar antenna according to claim 7, characterized in that: The locking mechanism (2) comprises a locking limit cylinder (2-1), two elastic components (2-2) and a locking clamp (2-3); The two elastic components (2-2) are relatively arranged on the locking and limiting cylinder (2-1), and their tips are located inside the locking and limiting cylinder (2-1). After the locking clamp (2-3) squeezes the tips of the two elastic components (2-2), it is inserted into the locking limit cylinder (2-1) to lock the locking mechanism (2).

10. The telescopic mechanism for preventing vibration of a 100-meter-class ring column antenna according to claim 1, characterized in that: The material of the 1 / 4 arc piece (5-1) consists of three layers, which are an aluminum plate (5-1-1), rubber (5-1-2) and sponge (5-1-3) from the outside to the inside.

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