Telescopic mechanism for preventing vibration of hectometer-level ring column antenna

Abstract

The invention discloses a telescopic mechanism for preventing vibration of a hectometer-level ring column antenna, and relates to the field of mechanical structure design. The invention aims to solve the problem that a connecting structure for relieving large-amplitude vibration of an antenna is added between the outside of the antenna and a satellite platform in the prior art and is large and heavy, so that the injection and stability of a satellite are influenced. Each limiting protective cover telescopic mechanism comprises two telescopic connecting rod mechanisms of the same structure and a 1 / 4 arc satellite limiting protective cover. The two telescopic connecting rod mechanisms are arranged side by side and are in sliding connection with the outer arc wall of the 1 / 4 arc satellite limiting shield; the four 1 / 4 arc satellite limiting shields are spliced into a circle through a locking mechanism and are embraced on an antenna; explosive bolts are arranged on the locking mechanisms and are used for exploding to break connection between every two adjacent limiting protective cover telescopic mechanisms; when all the telescopic connecting rod mechanisms retract synchronously, a space is reserved between the antenna and the fairing, and when all the telescopic connecting rod mechanisms stretch synchronously, all the telescopic connecting rod 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 development of aerospace technology, the demand for space exploration and communication missions is growing, especially the requirements for the size, function and performance of antennas have increased significantly. At present, the trend of antenna design is gradually leaning towards large size, especially in the fields of deep space exploration, broadband communication and scientific experiments, where 100-meter-class antennas have great application potential. The size advantage of this type of antenna enables it to provide a wider range, higher resolution signal coverage and data transmission capabilities in the space environment, greatly improving the efficiency of the satellite platform.

[0003] like Figure 1 As shown, the antenna 6 is arranged 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-column antenna is a potential key antenna structure, and its envelope size can reach 100 meters after being deployed. However, the antenna needs to be in a folded state before launch to adapt to the size limit of the fairing of the current launch vehicle. Existing research shows that the size of the folded antenna may still reach more than ten meters in height and more than five meters in diameter, which is far beyond the launch capability of China's current launch vehicles. The diameter of the current launch vehicle fairing is generally about five meters, and for the launch of the 100-meter-class antenna, the fairing size and load capacity of future rockets must be greatly improved, which undoubtedly puts higher requirements on the launch system.

[0005] In the prior art, the problem of fixing and preventing vibration of the antenna during launch is usually solved by adding a connection structure between the outside of the antenna and the satellite platform to provide support and stability during launch. Although this solution can alleviate the large-scale vibration of the antenna to a certain extent, it also has the following significant disadvantages:

[0006] The weight and size of the connection structure: Since the size and weight of the antenna itself are already considerable, the additional connection structure inevitably increases the mass of the entire system. This places higher demands on the rocket's launch capability, especially when the existing launch capability is limited. How to ensure a successful launch without sacrificing the payload has become a major challenge.

[0007] Reliability issues of the abandonment mechanism: After the antenna and satellite platform enter the predetermined orbit, the connection structure usually needs to be abandoned so that the antenna can be deployed smoothly. However, the connection structure is often designed to be large and heavy, and the reliability of its abandonment process may be affected by many factors, such as mechanism jamming, insufficient abandonment torque, etc. If the connection structure cannot be abandoned 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 abandonment process of large-size connection structures is likely to increase the difficulty of control, which further affects the orbit entry and stability of the satellite platform and antenna. Summary of the invention

[0008] The purpose of the present invention is to solve the problem that the existing connection structure added between the outside of the antenna and the satellite platform to alleviate the large-amplitude vibration of the antenna is large and heavy, which affects the satellite's orbit insertion and stability. A telescopic mechanism is proposed to prevent the vibration of the 100-meter-class ring column antenna.

[0009] A telescopic mechanism for preventing the vibration of a 100-meter-class ring column antenna, wherein the fixed end of the telescopic mechanism is fixed to 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 a satellite platform, and the telescopic mechanism includes one or more fixed protection devices, a locking mechanism and an explosive bolt;

[0010] Each fixed protection device includes four limit shield telescopic mechanisms, each of which includes two telescopic connecting rod mechanisms with the same structure and a 1 / 4 arc satellite limit shield;

[0011] Two telescopic connecting rod mechanisms are arranged side by side and are both slidably connected to the outer arc wall of the 1 / 4 arc satellite limit shield; four 1 / 4 arc satellite limit shields are spliced ​​into a circle through a locking mechanism and held on the antenna; an explosive bolt is provided on the locking mechanism for explosively disconnecting the connection between each two adjacent limit shield telescopic mechanisms;

[0012] When all the telescopic link mechanisms are retracted synchronously, a space is left between the antenna and the fairing; when all the telescopic link mechanisms are extended synchronously, 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 a telescopic function. One end of the upper rod assembly and one end of the lower rod assembly are both rotatably connected to the connecting seat, and the upper rod assembly and the lower rod assembly rotate in the same direction. 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 to the inner wall of the fairing as fixed ends of the telescopic mechanism.

[0015] The connecting seat is connected to the arc-shaped outer wall of the satellite limiting protective cover of 1 / 4 arc through a connecting piece.

[0016] Preferably, the upper rod assembly comprises a fixed hinge support, a hinge rod end No. 1, a damper No. 1, a coupling No. 1 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 end 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 end, 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 comprises a three-way connecting rod, a left curved tube No. 1, a right curved tube No. 1, a left sliding groove rod, a right sliding groove rod, a left sleeve, a right sleeve, a left curved tube No. 2, a right curved tube 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 groove rod, and the other end of the right sleeve extends into the slide groove of the right slide groove rod. The left sleeve and the right sleeve can slide along their respective slide grooves, so that the three-way connecting rod moves 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 comprises a No. 3 damper, a No. 3 coupling and a terminal 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 1 / 4 arc satellite limiting shield comprises a 1 / 4 arc piece and a limiting mechanism;

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

[0028] The limit block is fixed at the middle of the outer wall of the 1 / 4 arc piece, a slide groove is arranged on the side wall of the limit block, the limit block is embedded in the slide groove, and the other end of each end connecting rod is hinged with a slider.

[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 to the housing of the No. 2 DC motor.

[0031] The output shaft of the No. 2 DC motor is connected to the screw through a gear box, driving the screw to rotate. The lower push rod is sleeved on the screw, and a sliding part is sleeved on the outside of the lower push rod. The upper push rod is a hollow frame, and its inner wall is connected to the slide rail. The sliding part slides along the slide rail, thereby driving the upper push rod to extend and retract. The top of the upper push rod is fixed on the gear box and sleeved on the outside of the lower push rod. The lower push rod extends out of the bottom of the upper push rod and is fixedly connected to the three-way connecting rod.

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

[0033] The two opposite ends of each of the two adjacent 1 / 4 arc pieces are respectively fixedly connected with a locking limit cylinder and a locking clamp;

[0034] The two elastic components are arranged on the locking limit cylinder relatively, and their tips are located in the locking limit cylinder.

[0035] After the locking chuck squeezes the tips of the two elastic components, it is inserted into the locking limit cylinder to lock the locking mechanism.

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

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

[0038] The present invention aims to solve the problem in the prior art that it is difficult for launch vehicles to safely and stably send a 100-meter-class ring column antenna into space. In view of the huge size of the antenna in the folded state, the large vibration that is easy to generate during the launch, and the quality and reliability of the traditional connection structure, the present invention proposes a telescopic mechanism to prevent the vibration of the 100-meter-class ring column antenna. The design ensures that the antenna can be effectively fixed and protected during the launch process through the close integration of the fairing and the antenna, thereby improving the safety and stability of the launch process.

[0039] During the rocket assembly process, a retractable mechanical structure is installed on the inner wall of the fairing, which is used to automatically fix the antenna in the folded state during the launch process. Through the automatic retraction and locking function of the mechanical device, the antenna will not interfere with the fairing during the launch process, avoiding the potential collision risk between the traditional antenna and the fairing during the assembly and launch process.

[0040] Before launch, the telescopic mechanism is in a retracted state to ensure that there is enough space between the antenna and the fairing to avoid interfering with the assembly of the fairing. When the rocket is assembled, the telescopic mechanism will automatically extend to fix the antenna to the inner wall of the fairing, and provide all-round support and protection for the antenna through multiple locking points to prevent the antenna from shifting or being damaged due to vibration during launch. At the same time, a damper device is integrated into the mechanical structure, which can effectively absorb the vibration energy during the launch process, further reduce the force on the antenna during the launch process, and improve the vibration resistance of the system. Through the application of the damper, the vibration environment of the antenna in the fairing is improved, which helps to reduce the structural stress and fatigue damage of the satellite and improve the reliability of the entire launch mission.

[0041] When the rocket flies out of the atmosphere and is ready to separate the fairing, the automatic unlocking function of the telescopic mechanism is activated, the telescopic mechanism retracts, and the fairing can be smoothly separated from the antenna without affecting the subsequent antenna deployment process. At this time, the fairing and the telescopic mechanism will be discarded together, avoiding the risk of discarding failure or collision with the antenna that may be caused by the traditional connection structure.

[0042] Through this design, the present invention not only significantly reduces the weight of the launch system, but also improves the stability and safety of the antenna during the launch process, and solves the problem of fixation and vibration prevention in the launch of large-size antennas. The solution has the characteristics of fully automatic operation, can realize an unmanned launch process, and ensure the reliability of the system and the safety of the antenna at the key nodes of the rocket launch.

[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 of large-size antenna transmission.

[0044] By introducing technologies such as dual motor control, multi-degree-of-freedom rod system, and three-series damping and shock absorption system, the antenna is firmly fixed during the launch process, vibration is effectively suppressed, and the launch stability is greatly improved. At the same time, the automatic limit shield telescopic design and safety locking mechanism simplify the separation process of the antenna and the fairing, reducing the risk of collision and damage. In addition, the three-layer protective material design and high integration solution further optimize the space utilization efficiency and safety of the system. The present invention not only solves the launch problem of large-size antennas, but also provides reliable technical support for larger and more complex space communications and detection missions in the future, and has broad application prospects.

[0045] In summary, this patent proposes an innovative integrated design solution for the launch fixation and vibration protection of the 100-meter-class ring column antenna, breaking through the limitations of the existing connection structure. Through the combination of the built-in mechanical structure of the fairing and the damper, this design reduces the weight of the system while ensuring the vibration suppression effect of the antenna, providing a new solution for the launch of large-size antennas. In future large-scale satellite antenna launch missions, this patented design is expected to become one of the key technologies.

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

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

[0048] Three-series damper shock absorption system (damper No. 1, damper No. 2 and damper No. 3): can effectively absorb the vibration energy generated during launch, quickly disperse the vibration impact, ensure system stability, and improve the safety and reliability of the antenna during launch and orbit entry.

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

[0050] Safety locking mechanism design: improves the stability and reliability of the antenna when the fairing is separated, and reduces the risk of antenna deployment failure or damage due to loose locking.

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

[0052] Fully automatic docking locking and unlocking system: fully automated operation simplifies the system installation and disassembly process, suitable for complex launch missions, and reduces the risk of human intervention.

[0053] Innovative integrated design of satellite and rocket: It optimizes the combination of the rocket and antenna system, solves the technical bottleneck that the current launch vehicle cannot effectively accommodate large-size antennas, and improves the feasibility of large antenna launches. BRIEF DESCRIPTION OF THE DRAWINGS

[0054] Figure 1 This is the 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 shield;

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

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

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

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

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

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

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

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

[0068] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. 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 creative work are 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 in conjunction with the accompanying drawings and specific embodiments, but they are not intended to limit the present invention.

[0071] Example:

[0072] Combination Figures 1 to 3 , Figure 8 and Fig. 9 This embodiment is described, a telescopic mechanism for preventing a 100-meter-class ring column antenna from vibrating, wherein a fixed end of the telescopic mechanism is fixed to an inner wall of a fairing 7, and a 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, and the telescopic mechanism comprises one or more fixing protection devices, a locking mechanism 2 and an explosive bolt 3;

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

[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; four 1 / 4 arc satellite limit 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 limit shield telescopic mechanisms 1;

[0075] When all telescopic link mechanisms 4 are retracted synchronously, a space is left between the antenna 6 and the fairing 7 . When all telescopic link mechanisms 4 are extended synchronously, all 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 at the transmitting stage, and 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 After the four 1 / 4 satellite limit guards are deployed, Figure 8 The locking mechanism shown in the figure is docked and locked to form a complete satellite limit cover. Fig.12As shown. To unlock, the locking mechanism is separated using the explosive bolt 3.

[0077] Combine the following Figure 3 Introduce the structure of the telescopic connecting rod 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 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.

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

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

[0082] The upper rod assembly 4-1 includes a fixed hinge support 4-1-1, a hinge rod end No. 1 4-1-2, a damper No. 1 4-1-3, a coupling No. 1 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, so that the upper rod assembly 4-1 can be extended and retracted.

[0085] Combine the following Figure 3 Introduce 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 an articulated 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 make 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 articulated rod 4-2-6 through the No. 2 coupling 4-2-5, and the other end of the articulated rod 4-2-6 is rotatably connected to the connecting seat 4-3.

[0088] Combine the following Figures 3 to 5 Introduce the structure of the connecting seat 4-3:

[0089] The connecting seat 4-3 includes a three-way connecting rod 4-3-1, a left curved pipe No. 1 4-3-2, a right curved pipe No. 1 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 left curved pipe No. 2 4-3-8, a right curved pipe No. 2 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 first left curved pipe 4-3-2 and one end of the first right curved pipe 4-3-3 through the hinge pin 4-3-11, and 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 groove rod 4-3-4, and the other end of the right sleeve 4-3-7 extends into the slide groove of the right slide groove 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 moving the three-way connecting rod 4-3-1 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 slide slot to lock the left sleeve and the right sleeve at the corresponding position in the slide slot, thereby restricting the left sleeve and the right sleeve to prevent the left sleeve and the right sleeve from sliding freely in the slide slot and failing to support the fairing.

[0094] Combine the following Figure 3 Introduce 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] Combine the following Figure 6 The structure of the 1 / 4 arc satellite limit shield 5 is introduced as follows:

[0098] The 1 / 4 arc satellite limiting shield 5 comprises 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 sliding blocks 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, and a slide groove is provided on the side wall of the limit block 5-2-1. The limit block 5-2-1 is embedded in the slide groove, and the other end of each end connecting rod 4-4-3 is hinged to a slider 5-2-2.

[0101] Combine the following Figure 7 Introduce 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, and 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, and its inner wall is connected to the slide rail. 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] Combine the following Figures 8 to 13 The structure of the locking mechanism 2 is introduced as follows:

[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 arranged on the locking and limiting cylinder 2-1, and their tips are located in the locking and limiting 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] Combination Fig.14 Introduce 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 respectively an aluminum plate 5-1-1, rubber 5-1-2 and sponge 5-1-3 from the outside to the inside.

[0113] Working principle:

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

[0115] Step 1: Assemble the fairing. The limit shield telescopic mechanism 1 remains in a retracted state and close to the fairing. The fairing is assembled into the rocket according to the normal process.

[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, and the No. 1 DC motor 4-2-2 and the No. 2 DC motor 4-1-5-1 are started.

[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 thereto to swing.

[0118] Step 4: The electric push rod 4-1-5 is shortened. The second DC motor 4-1-5-1 is started, and the lead screw 4-1-5-3 is driven to rotate through the transmission 4-1-5-2, so that the lower push rod 4-1-5-5 is shortened 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 making the upper rod assembly swing.

[0120] Step 6: The extension rod group performs planar motion. Under the joint action of the upper and lower rod groups and the dual motors, the extension rod group, 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 connecting rod 4-4-3 will perform planar motion, and ensure that the plane is always parallel to the satellite installation platform, so as to ensure that the satellite limit shield is always parallel to the satellite antenna, avoiding interference with the satellite antenna during the expansion or contraction process.

[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 connecting rod mechanism does not include the degree of freedom in the tangential direction of the fairing, the slider 5-2-2 connected to the end connecting rod 4-4-3 will slide outward in the groove of the 1 / 4 satellite limit shield.

[0122] Step 8: Docking of satellite limit shields. After the limit shield telescopic mechanism is fully unfolded, the four 1 / 4 satellite limit shields 5 will be combined into a complete satellite limit shield. When two adjacent 1 / 4 satellite limit shields 5 gradually approach and are ready to be locked, the locking chuck 2-3 pushes the locking rod 2-2-1 to move outward, and the reset spring 2-2-2 is compressed. As the locking chuck 2-3 is further advanced, when the inclined surface of the locking rod 2-2-1 no longer contacts the front arc surface of the locking chuck 2-3, the reset spring 2-2-2 is released, and the locking rod 2-2-1 is pushed inward by the elastic force of the reset spring 2-2-2 until the two locking rods 2-2-1 clamp the middle rod of the locking chuck 2-3 to achieve locking.

[0123] Step 9: Rocket launch. The satellite limit shield locking mechanism remains locked, providing continuous buffer protection for the 100-meter-class ring column antenna during rocket launch.

[0124] Step 10: Unlocking the locking mechanism. Before the rocket fairing is separated, the explosive bolt 3 is exploded and disconnected, and the locking clamp 2-3 is disconnected from the 1 / 4 satellite limit shield, thereby achieving the separation of two adjacent 1 / 4 satellite limit shields.

[0125] Step 11: The telescopic mechanism retracts. Similar to the unfolding process, under the action of the dual motors, the 1 / 4 satellite limit shield gradually moves away from the satellite while maintaining a parallel posture with the satellite antenna until it returns to its initial state.

[0126] Step 12: Fairing separation: The fairing is separated from the rocket by the explosive bolts.

[0127] Although the present invention is described herein with reference to specific embodiments, it should be understood that these embodiments are merely examples of the principles and applications of the present invention. It should therefore be understood that many modifications may be made to the exemplary embodiments and that other arrangements may be devised without departing from the spirit and scope of the present invention as defined by the appended claims. It should be understood that the various dependent claims and features described herein may be combined in a manner different from that described in the original claims. It should also be understood that features described in conjunction with individual embodiments may be used in other described embodiments.

Claims

1. A telescopic mechanism for preventing a 100-meter-class ring column antenna from vibrating, 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), wherein the antenna (6) is arranged on a satellite platform (8), and wherein the telescopic mechanism is 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 comprises four position-limiting shield telescopic mechanisms (1), and each position-limiting shield telescopic mechanism (1) comprises two telescopic connecting rod mechanisms (4) of the same structure and a satellite position-limiting shield (5) of a 1 / 4 arc; Two telescopic connecting rod 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 arranged on the locking mechanism (2) and is used to explosively disconnect the connection between each two adjacent limiting shield telescopic mechanisms (1); When all telescopic link mechanisms (4) are synchronously retracted, a space is left between the antenna (6) and the fairing (7); when all telescopic link mechanisms (4) are synchronously extended, all telescopic link mechanisms (4) are supported on the fairing (7).

2. The telescopic mechanism for preventing the vibration of a hundred-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 satellite limiting protective cover (5) of a 1 / 4 arc through a connecting piece (4-4).

3. The telescopic mechanism for preventing the vibration of a hundred-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 hinge rod end No. 1 (4-1-2), a damper No. 1 (4-1-3), a coupling No. 1 (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 the vibration of a hundred-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 the vibration of a hundred-meter-class ring column antenna according to claim 4, characterized in that: The connecting seat (4-3) comprises a three-way connecting rod (4-3-1), a left curved pipe No. 1 (4-3-2), a right curved pipe No. 1 (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 left curved pipe No. 2 (4-3-8), a right curved pipe No. 2 (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 tube (4-3-2) and one end of the first right curved tube (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), and 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 groove rod (4-3-4), and the other end of the right sleeve (4-3-7) extends into the slide groove of the right slide groove rod (4-3-5), and the left sleeve (4-3-6) and the right sleeve (4-3-7) can slide along their respective slide grooves, thereby allowing 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), and 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), and 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). 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) through a three-way coupling (4-3-10).

6. The telescopic mechanism for preventing the vibration of a hundred-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 connecting rod (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 terminal connecting rod (4-4-3) through the No. 3 coupling (4-4-2).

7. The telescopic mechanism for preventing the vibration of a hundred-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) comprises a limiting block (5-2-1) and two sliding blocks (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 slide groove is provided on the side wall of the limit block (5-2-1), the limit block (5-2-1) is embedded in the slide 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 the vibration of a hundred-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 first coupling (4-1-4) is connected to the housing of the second DC motor (4-1-5-1). The output shaft of the second 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 piece 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 piece 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 sleeved on the outside of the lower push rod (4-1-5-4), 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 the vibration of a hundred-meter-class ring column 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 arranged relatively on the locking and limiting cylinder (2-1), and the tips of the two elastic components 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 the vibration of a hundred-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 respectively 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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