A passive high-precision spatial plane antenna deployment mechanism and a deployment method

Abstract

This invention provides a passive high-precision spatial planar antenna deployment mechanism and method, relating to the field of smart materials and deployable structure technology. The mechanism includes multiple stacked composite material rods, shape memory hinges, and an unlocking assembly and a support mounted on a supporting base. The shape memory hinges are sequentially connected between two adjacent composite material rods and also between the lowest composite material rod and the support. The unlocking assembly is used to connect to the multiple composite material rods in a locked state and to separate from them in an unlocked state. After the unlocking assembly is unlocked, the shape memory hinges are used to drive the multiple composite material rods coaxially via external excitation.

Description

Technical Field

[0001] This invention relates to the field of smart materials and deployable structures, and more specifically, to a passive high-precision spatial planar antenna deployment mechanism and deployment method. Background Technology

[0002] In the fields of aerospace engineering, advanced equipment, and portable structural systems, the ever-expanding demands for deep space exploration missions and high-precision communication have placed increasingly stringent requirements on the lightweight, compactness, and reliable deployability of structural components. While traditional rigid rod structures possess high structural stiffness and static load-bearing capacity, their inherent volume leads to increasingly prominent space constraints during spacecraft launch, orbital transportation, and long-term storage, making them unsuitable for the limited installation space within the launch vehicle fairing.

[0003] Existing deployable rod devices generally employ traditional methods such as mechanical hinges combined with spring drives, pneumatic actuators, or motor servo systems to achieve deployment. While such structures can accomplish basic deployment tasks, they generally suffer from inherent drawbacks such as a large number of mechanical components, complex overall configuration, and significantly increased system mass. During deployment, the friction pairs of mechanical hinges are susceptible to changes in ambient temperature, micro-vibrations, and radiation, leading to trajectory deviations and decreased deployment accuracy. Spring drive systems are prone to preload decay and accidental release. Pneumatic and motor drives rely on external energy supply and complex control loops, which not only increase system power consumption but also expose problems such as response lag, poor synchronization, and increased failure rates in microgravity environments, severely affecting antenna deployment accuracy and stability. Summary of the Invention

[0004] The problem addressed by this invention is how to solve the problems of complex deployment mechanism, insufficient deployment reliability, and large overall mass in existing deployable rod structures.

[0005] To address the aforementioned problems, this invention provides a passive high-precision spatial planar antenna deployment mechanism, comprising multiple composite material rods stacked together, a shape memory hinge, and an unlocking assembly and a support mounted on a supporting base. The shape memory hinge is sequentially connected between two adjacent composite material rods and also between the lowest composite material rod and the support. The unlocking assembly is used to connect with the multiple composite material rods in a locked state and to separate from the multiple composite material rods in an unlocked state. The shape memory hinge is used to drive the multiple composite material rods coaxially through external excitation after the unlocking assembly is unlocked.

[0006] Optionally, the passive high-precision spatial planar antenna deployment mechanism further includes a locking component. The locking component is disposed between the tail ends of two adjacent composite material rods and between the head ends of two adjacent composite material rods, and also between the tail end of the lowest composite material rod and the support. The locking component includes a locking protrusion and a locking recess. When multiple composite material rods are coaxial, the locking protrusion and the locking recess cooperate to lock.

[0007] Optionally, the unlocking assembly includes multiple locking blocks, a fixing seat, a slotted bolt, and a shape memory metal block. The locking blocks are fitted onto the corresponding composite material rods. The slotted bolts are connected in series with multiple locking blocks, multiple composite material rods, and the shape memory metal blocks. The shape memory metal blocks are embedded in the fixing seat and are pulled off by external excitation.

[0008] Optionally, the unlocking assembly further includes a lower unlocking spring and an upper unlocking spring in a compressed state. The two ends of the slotted bolt extend from the uppermost locking block and the shape memory metal block, respectively, and are respectively provided with a top cover and a bottom cover. The lower unlocking spring is fitted onto the shape memory metal block, and the two ends of the lower unlocking spring are respectively connected to the bottom cover and the fixing seat. The two ends of the upper unlocking spring are respectively connected to the top cover and the uppermost locking block.

[0009] Optionally, the unlocking assembly further includes a locking nut that engages with the top thread of the slotted bolt, and the top cover is located between the locking nut and the upper unlocking spring.

[0010] Optionally, the unlocking component further includes a limiting nut that engages with the bottom thread of the slotted bolt, and the shape memory metal block is located between the limiting nut and the fixing seat.

[0011] Optionally, the unlocking assembly further includes a protective cover that covers the top cover and the locking nut and is connected to the uppermost locking block.

[0012] Optionally, the shape memory hinge includes two metal frames and a herringbone hinge. The metal frame includes an assembly ring and a slot located in its middle. The slot is located at both ends of the metal frame. The assembly ring is connected to the composite material rod and / or support. The herringbone hinge is located between the two metal frames. The slot is engaged with the main support and two branches of the herringbone hinge, respectively.

[0013] Optionally, the diameter of the multiple composite rods decreases sequentially along the stacking direction.

[0014] Compared with related technologies, the passive high-precision spatial planar antenna deployment mechanism of the present invention, in the folding stage, is supported by an unlocking component and a support base, which provide support for the unlocking component and the support base and provide a reference for the subsequent deployment of multiple composite material rods 1. The compact storage is achieved by multiple stacked composite material rods, which significantly reduces the storage space requirements of multiple composite material rods. The unlocking component is used to connect with multiple composite material rods in the locked state to ensure the stability of the storage of multiple composite material rods. In the deployment stage, shape memory hinges are sequentially connected between two adjacent composite material rods, as well as between the bottom composite material rod and the support. By applying external excitation to the shape memory hinges, the shape memory hinges can provide self-driven deployment capability, reducing the number of parts, simplifying the structure, reducing weight, and improving the reliability of the deployment process. It avoids the disadvantages of traditional mechanical drive being susceptible to environmental interference. The unlocking of the unlocking component ensures the smooth deployment of multiple composite material rods, thereby achieving lightweight, high reliability, and low power consumption passive deployment, meeting the needs of high-requirement application scenarios such as aerospace engineering.

[0015] In another aspect, the present invention provides a method for deploying a passive high-precision spatial planar antenna deployment mechanism, based on the passive high-precision spatial planar antenna deployment mechanism as described above, comprising the following steps: An external excitation is applied to the shape memory metal block of the unlocking component to unlock the unlocking component; External excitation is applied to each shape memory hinge in turn until multiple composite rods are coaxial.

[0016] The deployment method of this passive high-precision spatial planar antenna deployment mechanism has all the beneficial effects of the passive high-precision spatial planar antenna deployment mechanism, which will not be elaborated here. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the passive high-precision spatial planar antenna deployment mechanism in an embodiment of the present invention when it is retracted; Figure 2 This is a schematic diagram of the unlocking component in an embodiment of the present invention; Figure 3 This is a schematic diagram of the upper composite material rod after it has been unfolded in an embodiment of the present invention; Figure 4 This is a schematic diagram of the unfolded composite material rod in an embodiment of the present invention; Figure 5 This is a schematic diagram of the three composite material rods fully deployed in an embodiment of the present invention. Figure 6 This is a schematic diagram of the shape memory hinge in an embodiment of the present invention; Figure 7This is a schematic diagram of the shape memory hinge when it is retracted in an embodiment of the present invention; Figure 8 This is a schematic diagram of the middle herringbone hinge in an embodiment of the present invention.

[0018] Explanation of reference numerals in the attached figures: 1- Composite material rod; 2- Shape memory hinge; 21- Metal frame; 22- Herringbone hinge; 3- Unlocking component; 31- Locking block; 32- Fixing base; 321- Mounting slot; 33- Slotted bolt; 331- Top cover; 332- Bottom cover; 34- Shape memory metal block; 35- Lower unlocking spring; 36- Upper unlocking spring; 37- Locking nut; 38- Limiting nut; 39- Protective cover; 4- Support; 5- Locking component; 51- Locking protrusion; 52- Locking recess. Detailed Implementation

[0019] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0020] In the attached figures, the X-axis represents left and right positions, with the positive direction of the X-axis representing the right side and the negative direction representing the left side; the Y-axis represents front and back positions, with the positive direction of the Y-axis representing the front and the negative direction representing the back; and the Z-axis represents up and down positions, with the positive direction of the Z-axis representing the top and the negative direction representing the bottom. It should be noted that the aforementioned representations of the X, Y, and Z axes are merely for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as limiting the invention.

[0021] It should be noted that the terms "first," "second," etc., used in the specification and claims of this invention are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate so that the embodiments of the invention described herein can be implemented in orders other than those illustrated or described herein.

[0022] Combination Figure 1 , Figures 3 to 5As shown, this embodiment of the invention provides a passive high-precision spatial planar antenna deployment mechanism, including multiple composite material rods 1 stacked together, a shape memory hinge 2, and an unlocking component 3 and a support 4 installed on a supporting base. The shape memory hinge 2 is sequentially connected between two adjacent composite material rods 1, and also connected between the lowest composite material rod 1 and the support 4. The unlocking component 3 is used to connect with the multiple composite material rods 1 in the locked state and to separate from the multiple composite material rods 1 in the unlocked state. The shape memory hinge 2 is used to drive the multiple composite material rods 1 to coaxiality through external excitation after the unlocking component 3 is unlocked.

[0023] Specifically, in this embodiment, there can be three composite material rods 1, all of which are made of carbon fiber composite material, such as... Figure 1 As shown, three composite material rods 1 are stacked parallel to each other from bottom to top, with a gap between any two adjacent rods 1. The end of each rod 1 facing the positive Y-axis is its tail end, and the end facing the negative Y-axis is its head end. The tail end of the uppermost rod 1 is connected to the tail end of the middle rod 1 via a shape memory hinge 2. The head end of the middle rod 1 is connected to the head end of the bottommost rod 1 via a shape memory hinge 2. The tail end of the bottommost rod 1 is connected to the support 4 via a shape memory hinge 2. Initially, the shape memory hinge 2 can have a certain bending angle through heat shaping treatment, such as... Figure 1 As shown, the two upper shape memory hinges 2 have a bending angle of 180°, and the lowermost shape memory hinge 2 has a bending angle of 90 degrees. During assembly, the support 4 is mounted on the support base, which can be understood as the shell of a spacecraft. Two unlocking components 3 are spaced apart along the length of the composite material rods 1 and are respectively mounted on the support base. The unlocking components 3 have locked and unlocked states. Initially, the unlocking components 3 are connected to the three composite material rods 1 in the locked state. When the three composite material rods 1 need to be unfolded, as... Figure 3 As shown, unlocking component 3 unlocks, and then an external excitation is applied to the upper shape memory hinge 2. The upper composite material rod 1 unfolds under the action of the shape memory hinge 2 until it is coaxial with the middle composite material rod 1. Then, an external excitation is applied to the middle shape memory hinge 2, as shown. Figure 4 As shown, the middle composite material rod 1 unfolds to be coaxial with the bottom composite material rod 1 under the action of the shape memory hinge 2. Finally, as... Figure 5 As shown, an external excitation is then applied to the bottom shape memory hinge 2, so that the bottom composite material rod 1 is coaxial with the support 4, thus completing the full unfolding of the three composite material rods 1.

[0024] Therefore, in this embodiment, during the folding stage, the unlocking component 3 and the support 4 are respectively installed on the support base. The support base provides support for the unlocking component 3 and the support 4, and provides a reference for the subsequent unfolding of multiple composite material rods 1. The multiple composite material rods 1 are stacked and distributed to achieve compact storage, significantly reducing the storage space requirements of multiple composite material rods 1. The unlocking component 3 is used to connect with multiple composite material rods 1 in the locked state to ensure the stability of the storage of multiple composite material rods 1. During the unfolding stage, the shape memory hinge 2 is sequentially connected between two adjacent composite material rods 1, and also between the bottom composite material rod 1 and the support 4. By applying external excitation to the shape memory hinge 2, the shape memory hinge 2 can provide self-driven unfolding capability, reducing the number of parts, simplifying the structure, reducing the weight, and improving the reliability of the unfolding process. It avoids the disadvantages of traditional mechanical drive being susceptible to environmental interference. The unlocking of the unlocking component 3 ensures the smooth unfolding process of multiple composite material rods 1, thereby realizing lightweight, high reliability, low power consumption passive unfolding, meeting the needs of high-requirement application scenarios such as aerospace engineering.

[0025] Optionally, combined Figure 1 As shown, the passive high-precision spatial planar antenna deployment mechanism also includes a locking component 5. The locking component 5 is disposed between the tail ends of two adjacent composite material rods 1 and between the head ends of two adjacent composite material rods 1, and is also disposed between the tail end of the lowest composite material rod 1 and the support 4. The locking component 5 includes a locking protrusion 51 and a locking recess 52. When multiple composite material rods 1 are coaxial, the locking protrusion 51 and the locking recess 52 cooperate to lock.

[0026] Specifically, such as Figure 1 As shown, the locking assembly 5 includes a locking protrusion 51 and a locking recess 52, which are engaged and locked together. The locking protrusion 51 connects to the tail end of the upper composite material rod 1, and the locking recess 52 connects to the tail end of the middle composite material rod 1. The locking protrusion 51 connects to the head end of the middle composite material rod 1, and the locking recess 52 connects to the head end of the lowermost composite material rod 1. The locking protrusion 51 connects to the tail end of the lowermost composite material rod 1, and the locking recess 52 connects to the support 4. Because the shape memory hinge 2 unfolds according to a predetermined trajectory, when multiple composite material rods 1 are fully unfolded, the corresponding locking protrusions 51 and locking recesses 52 engage, preventing relative movement between any two composite material rods 1 and also preventing relative movement between multiple composite material rods 1 and the support 4.

[0027] Thus, when the shape memory hinge 2 drives each composite rod 1 to move to the coaxial unfolding position, the locking protrusion 51 and the locking recess 52 can automatically align and lock together without the need for additional driving components, simplifying the locking process. This not only provides high-precision alignment, ensuring the coaxial accuracy of each composite rod 1 after unfolding, but also provides sufficient connection stiffness, effectively improving the load-bearing capacity and stability of the overall structure after unfolding. As a result, reliable mechanical locking can be achieved after unfolding, significantly enhancing the overall stiffness and anti-interference capability of the structure. This meets the high requirements for the structural stability and load-bearing capacity of the unfolding mechanism in space application scenarios, ensuring the working accuracy of the space planar antenna.

[0028] Optionally, combined Figure 1 and Figure 2 As shown, the unlocking component 3 includes multiple locking blocks 31, a fixing seat 32, a slotted bolt 33, and a shape memory metal block 34. The locking blocks 31 are fitted onto the corresponding composite material rods 1. The slotted bolts 33 are connected in series with multiple locking blocks 31, multiple composite material rods 1, and shape memory metal blocks 34. The shape memory metal blocks 34 are embedded in the fixing seat 32 and are pulled off by external excitation.

[0029] Specifically, the slotted bolt 33 is a special bolt with a predetermined fracture point. Its main body can be made of high-strength alloy steel or titanium alloy, and an annular or V-shaped slot is machined at a specific location (e.g., near the connection end of the shape memory metal block 34), reducing the cross-sectional area at that location so that it can precisely fracture at that point under a predetermined tensile force. Figure 2 As shown, three locking blocks 31 are provided, each locking block 31 fitting onto a corresponding composite material rod 1. Both the locking blocks 31 and the composite material rod 1 have pre-drilled through holes along the radial direction of the composite material rod 1. One end of the slotted bolt 33 is connected to the uppermost locking block 31, and the other end passes through the remaining locking blocks 31 and multiple through holes to connect with the shape memory metal block 34. The fixing base 32 is connected to the supporting foundation and includes a mounting groove 321 with an opening facing the supporting foundation. The shape memory metal block 34 is pre-treated by heat shaping and is embedded in the mounting groove 321 in a compressed state. When unlocking, the shape memory metal block 34 extends under external excitation in a direction opposite to that of the slotted bolt 33, i.e., downwards, and applies tension to the slotted bolt 33. Under this tension, the slotted bolt 33 is broken, allowing each locking block 31 to move with its corresponding composite material rod 1, thus completing the unlocking process.

[0030] Thus, by fitting the locking block 31 onto the corresponding composite material rod 1, and connecting multiple locking blocks 31, multiple composite material rods 1, and shape memory metal blocks 34 in series with the slotted bolt 33, and embedding the shape memory metal blocks 34 into the fixing base 32, the overall and stable constraint of multiple composite material rods 1 in the stacked state is achieved. This avoids structural loosening or premature deployment due to accidental vibration or impact during transportation, storage, and launch. When deployment is required, external excitation is applied to the shape memory metal blocks 34, and the strong tensile force generated by its thermal deformation can be precisely applied to the preset slotted position of the slotted bolt 33, causing it to break along the preset point. This greatly simplifies the unlocking process, improves the reliability and success rate of unlocking, and reduces power consumption.

[0031] Optionally, combined Figure 2 As shown, the unlocking assembly 3 also includes a lower unlocking spring 35 and an upper unlocking spring 36 in a compressed state. The two ends of the slotted bolt 33 extend from the uppermost locking block 31 and the shape memory metal block 34, respectively, and are respectively provided with a top cover 331 and a bottom cover 332. The lower unlocking spring 35 is fitted into the shape memory metal block 34. The two ends of the lower unlocking spring 35 are respectively connected to the bottom cover 332 and the bottom wall of the mounting groove 321. The two ends of the upper unlocking spring 36 are respectively connected to the top cover 331 and the uppermost locking block 31.

[0032] Specifically, the length of the slotted bolt 33 is greater than the thickness of the shape memory metal block 34 and the multiple locking blocks 31, allowing both ends of the slotted bolt 33 to extend from the uppermost locking block 31 and shape memory metal block 34. The top cover 331 and bottom cover 332 are components respectively fixed to both ends of the slotted bolt 33. For example, the top cover 331 and bottom cover 332 can be designed as a disc-shaped structure with threaded holes, which are connected and locked to the corresponding threaded sections of the slotted bolt 33 via threads. The lower unlocking spring 35 is fitted onto the shape memory metal block 34, and both ends of the lower unlocking spring 35 are respectively connected to the top of the bottom cover 332 and the mounting groove 321. Through the support of the top of the mounting groove 321, the elastic force of the lower unlocking spring 35 can act on the lower end of the slotted bolt 33 through the bottom cover 332. The two ends of the upper unlocking spring 36 are connected to the top cover 331 and the uppermost locking block 31 respectively, so that the elastic force of the upper unlocking spring 36 can act on the upper end of the slotted bolt 33 through the top cover 331, while its other end is fixed on the uppermost locking block 31, thereby applying an upward pulling force to the slotted bolt 33.

[0033] Thus, during the unlocking process, when the shape memory metal block 34 deforms and contracts downward under external stimulation, it pulls the slotted bolt 33 downward. Simultaneously, the lower unlocking spring 35 and the upper unlocking spring 36, which are in a compressed state, release their stored elastic potential energy. The lower unlocking spring 35 applies a continuous downward pulling force to the lower end of the slotted bolt 33 through the bottom cover 332, consistent with the pulling force of the shape memory metal block 34, thereby enhancing the total downward pulling force. The upper unlocking spring 36 applies a continuous upward pulling force to the upper end of the slotted bolt 33 through the top cover 331. In this way, the slotted bolt 33 simultaneously bears pulling forces from both the upper and lower directions, and these forces act stably on the body of the slotted bolt 33 through the top cover 331 and the bottom cover 332, avoiding force dispersion and significantly increasing the probability of the slotted bolt 33 being reliably broken. This ensures the smooth completion of the unlocking process of the unfolding mechanism and provides a solid foundation for the subsequent coaxial unfolding of multiple composite material rods 1.

[0034] Optionally, combined Figure 2 As shown, the unlocking assembly 3 also includes a locking nut 37, which engages with the top thread of the slotted bolt 33, and the top cover 331 is located between the locking nut 37 and the upper unlocking spring 36.

[0035] Specifically, the locking nut 37 engages with the top thread of the slotted bolt 33. By tightening the locking nut 37, the top cover 331 is pressed down from above by the locking nut 37, while the bottom of the top cover 331 directly acts on the upper unlocking spring 36. The locking force applied by the locking nut 37 can be directly and effectively transmitted to the top cover 331, thereby stably acting on the upper unlocking spring 36, ensuring that the upper unlocking spring 36 always remains in a preset compressed state, thus maintaining its preload.

[0036] Thus, by adding a locking nut 37 and engaging it with the top thread of the slotted bolt 33, while simultaneously positioning the top cover 331 between the locking nut 37 and the upper unlocking spring 36, the locking nut 37 provides reliable axial restraint to the top cover 331 through the threaded engagement, preventing the top cover 331 from loosening due to vibration or impact during mechanism folding, transportation, or launch. Simultaneously, by adjusting the tightness of the locking nut 37, the compression preload of the upper unlocking spring 36 can be precisely set and maintained, ensuring it provides stable and sufficient elastic force during unlocking to assist in breaking the slotted bolt 33. This not only improves the reliability and stability of the unlocking mechanism, meeting the stringent high reliability requirements of space applications, but also, due to the simple structure and light weight of the locking nut 37, requires minimal structural modification to the original unlocking components, making it easy to integrate and conforming to lightweight design principles.

[0037] Optionally, combined Figure 2As shown, the unlocking component 3 also includes a limiting nut 38, which engages with the bottom thread of the slotted bolt 33, and the shape memory metal block 34 is located between the limiting nut 38 and the fixing seat 32.

[0038] Specifically, the limiting nut 38 engages with the bottom thread of the slotted bolt 33, thereby fixing or adjusting the position of the shape memory metal block 34 in the axial direction. This allows the limiting nut 38 to move axially on the slotted bolt 33 and be fixed in a specific position, thereby achieving axial position adjustment and limiting of the shape memory metal block 34. In other words, the shape memory metal block 34 is clamped between the limiting nut 38 and the mounting groove 321 of the fixing seat 32.

[0039] Thus, by adding a limiting nut 38, the axial position of the shape memory metal block 34 is limited, ensuring the stability of the shape memory metal block 34's position and thereby improving the overall reliability of the unlocking action. Using the rod structure of the slotted bolt 33 itself to install the limiting nut 38 eliminates the need for excessively complex additional structures, preventing any additional weight increase to the mechanism and meeting the lightweight requirements of aerospace equipment. By confining the shape memory metal block 34 between the limiting nut 38 and the fixing seat 32, and relying on the threaded engagement between the limiting nut 38 and the slotted bolt 33, the installation position of the limiting nut 38 on the slotted bolt 33 can be flexibly adjusted. This accommodates shape memory metal blocks 34 of different sizes and provides appropriate preload, preventing axial movement or displacement of the shape memory metal block 34 during assembly and stress operations. This ensures that the force generated by external excitation on the shape memory metal block 34 is accurately transmitted along the axial direction of the slotted bolt 33, guaranteeing that the slotted bolt 33 can be successfully pulled apart. This ensures that the unlocking action can be completed smoothly and on time, effectively improving the reliability of the entire deployment mechanism.

[0040] Optionally, combined Figure 2 As shown, the unlocking component 3 also includes a protective cover 39, which covers the top cover 331 and the locking nut 37, and is connected to the uppermost locking block 31.

[0041] Specifically, the protective cover 39 can be integrally molded from high-strength engineering plastics (such as polycarbonate or ABS resin) to provide good impact resistance and environmental corrosion resistance. The structure of the protective cover 39 can be designed as a cylindrical, conical, or irregularly shaped shell to completely cover and enclose the top cover 331 and the locking nut 37. The connection between the protective cover 39 and the uppermost locking block 31 can be varied, for example, by screw fixing, snap-fit ​​connection, bonding, or integral molding with the locking block 31, to ensure its positional stability during the operation of the mechanism.

[0042] In this way, by covering the top cover 331 and the locking nut 37 with the protective cover 39 and connecting it with the uppermost locking block 31, effective protection is achieved for the top cover 331 and the locking nut 37, thereby improving the stability and reliability of the locking state of the unlocking component 3 and ensuring that the overall unfolding mechanism can work normally.

[0043] Optionally, combined Figures 6 to 8 As shown, the shape memory hinge 2 includes two metal frames 21 and a herringbone hinge 22. The metal frame 21 includes an assembly ring 211 and a slot 212 located in the middle. The slot 212 is located at both ends of the metal frame 21. The assembly ring 211 is connected to the composite material rod 1 and / or the support 4. The herringbone hinge 22 is located between the two metal frames 21. The slot 212 is engaged with the main support and two branches of the herringbone hinge 22 respectively.

[0044] Specifically, the projection of the herringbone hinge 22 onto a plane perpendicular to its extension direction is a "V" shape. The herringbone hinge 22 includes a main branch and two branches branching off from the ends of the main branch. The branches are arc-shaped and spaced far apart from each other, such as... Figure 8 As shown, Figure 8 This is a schematic diagram showing the two main supports of the two herringbone hinges 22 stacked together. Two metal frames 21 are provided, as shown... Figure 6 As shown, two metal frames 21 are parallel, and each metal frame 21 has an assembly ring 211 in the middle. Each metal frame 21 is connected to the end of the composite material rod 1 or the support 4 through its respective assembly ring 211. Each metal frame 21 has a slot at both ends in the length direction, which engages with the herringbone hinge 22 to fix the herringbone hinge 22. Figure 6 As shown, two metal frames 21 are located at both ends of the herringbone hinge 22. The two mounting rings 211 are coaxial. On the same side of the axis, the two main branches of each herringbone hinge 22 overlap and are snapped between the two metal frames 21, forming a "sandwich" structure. This allows the herringbone hinge 22 to be effectively constrained and guided by the metal frames 21 during the unfolding process, preventing unnecessary deflection or deformation when it unfolds freely.

[0045] Thus, by positioning the assembly ring 211 in the middle of the metal frame 21 and connecting it to the composite material rod 1 and / or support 4, the connection force is more evenly distributed, avoiding stress concentration and significantly improving the stability and reliability of the connection. The slots 212 at both ends of the metal frame 21 allow for multi-point engagement with the main support and two branches of the herringbone hinge 22, simplifying the assembly process and, more importantly, enhancing the connection strength and reliability between the herringbone hinge 22 and the metal frame 21. This effectively prevents the herringbone hinge 22 from shifting or falling off during deployment. Furthermore, the herringbone... The hinge 22 is arranged between the two metal frames 21, which provides driving force while also being fully protected and constrained by the structure, further improving the stability and accuracy of the deployment. In particular, its specific herringbone shape itself has geometric flexibility. After being heated or stimulated, the deformation path is clearer and the recovery process is smoother, making it less prone to sudden instability. This significantly improves the structural strength, connection reliability and deployment positioning accuracy of the shape memory hinge 2, enabling the passive high-precision space planar antenna deployment mechanism to meet the requirements of high rigidity, high reliability and high precision deployment.

[0046] Optionally, such as Figure 1 As shown, the diameter of the multiple composite rods 1 decreases sequentially along the stacking direction.

[0047] Specifically, the diameter of the bottom composite material rod 1 is larger than the diameter of the middle composite material rod 1, and the diameter of the middle composite material rod 1 is larger than the diameter of the top composite material rod 1.

[0048] Thus, by setting the diameter of multiple composite material rods 1 to decrease sequentially along the stacking direction, the multiple composite material rods 1 can be nested one by one in the folded storage state, making full use of the storage space and reducing the overall volume in the storage state. This effectively solves the problem of excessive storage volume of the mechanism and meets the space constraints of aerospace launch scenarios. Furthermore, after unfolding, the decreasing diameter helps to reduce local stiffness, and the mass of the composite material rods 1 can be further reduced, facilitating the unfolding operation in conjunction with the shape memory hinge 2.

[0049] Another embodiment of the present invention provides a method for deploying a passive high-precision spatial planar antenna deployment mechanism, based on the aforementioned passive high-precision spatial planar antenna deployment mechanism, comprising the following steps: Step 1: Apply an external stimulus to the shape memory metal block 34 of the unlocking component 3 to unlock the unlocking component 3; Step 2: Apply external excitation to each shape memory hinge 2 in sequence until multiple composite material rods 1 are coaxial.

[0050] Specifically, when the antenna needs to be deployed, an external excitation is first applied to the unlocking assembly 3. Specifically, the external excitation (e.g., by electrical heating) acts on the shape memory metal block 34 within the unlocking assembly 3. The shape memory metal block 34 deforms upon heating, generating tension. This tension, combined with the elastic force of the lower unlocking spring 35 and the upper unlocking spring 36 under compression, breaks the slotted bolt 33. One end of the slotted bolt 33 is connected to the uppermost locking block 31, and the other end passes through the pre-drilled holes in the remaining locking blocks 31 and the composite material rod 1, connecting to the shape memory metal block 34. The breakage of the slotted bolt 33 releases the connection between the locking block 31 and the composite material rod 1. The two ends of the lower unlocking spring 35 are connected to the bottom cover 332 of the slotted bolt 33 and the bottom wall of the mounting groove 321 of the fixing seat 32, respectively, while the two ends of the upper unlocking spring 36 are connected to the top cover 331 of the slotted bolt 33 and the uppermost locking block 31, respectively. After the slotted bolts 33 break, the release force of these springs pushes the locking blocks 31 away from the composite rods 1, thereby separating the multiple composite rods 1 from the unlocking assembly 3 and completing the unlocking process. The protective cover 39 is placed over the top cover 331 and the locking nut 37 and is connected to the uppermost locking block 31, providing protection for the unlocking mechanism and preventing the external environment from adversely affecting the unlocking process.

[0051] After unlocking, the multiple composite rods 1 are in a free state. At this time, an external excitation (e.g., by electric heating) is applied to each shape memory hinge 2 in sequence. Each shape memory hinge 2 includes two metal frames 21 and a herringbone hinge 22. The metal frames 21 are connected to the adjacent composite rod 1 (or the lowermost composite rod 1 and the support 4) through their mounting rings 211. The herringbone hinge 22 is located between the two metal frames 21, with its main support and two branches respectively engaged in the slots 212 at both ends of the metal frames 21. When the shape memory hinge 2 is heated, the shape memory material inside it restores its preset shape, driving the adjacent composite rod 1 to rotate around the hinge axis. This process is passive and self-driven, avoiding the complexity, quality, and power consumption problems associated with traditional motor or pneumatic drives. The precise deformation characteristics of the shape memory hinge 2 ensure the stability and high accuracy of the unfolding process.

[0052] As each shape memory hinge 2 is sequentially activated and unfolded, multiple composite material rods 1 gradually unfold from their stacked state and eventually achieve coaxial alignment. When all composite material rods 1 are fully unfolded and coaxial, the locking assembly 5 comes into play. The locking assembly 5 is located between the tail and head ends of adjacent composite material rods 1, and between the tail end of the lowest composite material rod 1 and the support 4. The locking assembly 5 includes a locking protrusion 51 and a locking recess 52. When the composite material rods 1 are coaxial, the locking protrusion 51 and the locking recess 52 precisely engage to achieve mechanical locking. This locking method provides a highly reliable mechanical connection, ensuring that the unfolded antenna structure has sufficient stiffness and load-bearing capacity, overcoming the problems of insufficient stiffness and limited load-bearing capacity that may exist in traditional shape memory materials in rod-shaped structures.

[0053] Thus, through the above process, the passive high-precision spatial planar antenna deployment mechanism achieves a transformation from compact storage to stable deployment. The entire deployment process utilizes the self-driving properties of shape memory materials, reducing the number of moving parts, simplifying the structure, reducing mass, and improving the reliability and accuracy of deployment.

[0054] While the present invention has been disclosed above, its scope of protection is not limited thereto. Those skilled in the art can make various changes and modifications without departing from the spirit and scope of the present invention, and all such changes and modifications will fall within the scope of protection of the present invention.

Claims

1. A passive high-precision spatial planar antenna deployment mechanism, characterized in that, The device includes multiple composite material rods (1) stacked together, a shape memory hinge (2), and an unlocking assembly (3) and a support (4) installed on a supporting base. The shape memory hinge (2) is connected sequentially between two adjacent composite material rods (1) and between the lowest composite material rod (1) and the support (4). The unlocking assembly (3) is used to connect with the multiple composite material rods (1) in the locked state and to separate from the multiple composite material rods (1) in the unlocked state. The shape memory hinge (2) is used to drive the multiple composite material rods (1) to coaxiality through external excitation after the unlocking assembly (3) is unlocked.

2. The passive high-precision spatial planar antenna deployment mechanism according to claim 1, characterized in that, It also includes a locking component (5), which is disposed between the tail ends of two adjacent composite material rods (1) and between the head ends of two adjacent composite material rods (1), and is also disposed between the tail end of the lowest composite material rod (1) and the support (4). The locking component (5) includes a locking protrusion (51) and a locking recess (52). When multiple composite material rods (1) are coaxial, the locking protrusion (51) and the locking recess (52) cooperate to lock.

3. The passive high-precision spatial planar antenna deployment mechanism according to claim 1, characterized in that, The unlocking component (3) includes multiple locking blocks (31), a fixing seat (32), a slotted bolt (33), and a shape memory metal block (34). The locking blocks (31) are fitted onto the corresponding composite material rods (1). The slotted bolts (33) are connected in series with multiple locking blocks (31), multiple composite material rods (1), and the shape memory metal blocks (34). The shape memory metal blocks (34) are embedded in the fixing seat (32) and the slotted bolts (33) are broken by external excitation.

4. The passive high-precision spatial planar antenna deployment mechanism according to claim 3, characterized in that, The unlocking assembly (3) also includes a lower unlocking spring (35) and an upper unlocking spring (36) in a compressed state. The two ends of the slotted bolt (33) extend from the uppermost locking block (31) and the shape memory metal block (34) respectively, and are respectively provided with a top cover (331) and a bottom cover (332). The lower unlocking spring (35) is fitted onto the shape memory metal block (34). The two ends of the lower unlocking spring (35) are respectively connected to the bottom cover (332) and the bottom wall of the fixing seat (32). The two ends of the upper unlocking spring (36) are respectively connected to the top cover (331) and the uppermost locking block (31).

5. The passive high-precision spatial planar antenna deployment mechanism according to claim 4, characterized in that, The unlocking assembly (3) also includes a locking nut (37) that engages with the top thread of the slotted bolt (33), and the top cover (331) is located between the locking nut (37) and the upper unlocking spring (36).

6. The passive high-precision spatial planar antenna deployment mechanism according to claim 3, characterized in that, The unlocking component (3) also includes a limiting nut (38), which engages with the bottom thread of the slotted bolt (33), and the shape memory metal block (34) is located between the limiting nut (38) and the fixing seat (32).

7. The passive high-precision spatial planar antenna deployment mechanism according to claim 5, characterized in that, The unlocking component (3) also includes a protective cover (39) which covers the top cover (331) and the locking nut (37) and is connected to the uppermost locking block (31).

8. The passive high-precision spatial planar antenna deployment mechanism according to claim 1, characterized in that, The shape memory hinge (2) includes two metal frames (21) and a herringbone hinge (22). The metal frame (21) includes an assembly ring (211) and a slot (212) located in the middle. The slot (212) is located at both ends of the metal frame (21). The assembly ring (211) is connected to the composite material rod (1) and / or the support (4). The herringbone hinge (22) is located between the two metal frames (21). The slot (212) is engaged with the main support and two branches of the herringbone hinge (22) respectively.

9. The passive high-precision spatial planar antenna deployment mechanism according to claim 1, characterized in that, The diameter of the multiple composite rods (1) decreases sequentially along the stacking direction.

10. A method for deploying a passive high-precision spatial planar antenna deployment mechanism, based on the passive high-precision spatial planar antenna deployment mechanism as described in any one of claims 1-9, characterized in that, Includes the following steps: An external stimulus is applied to the shape memory metal block (34) of the unlocking component (3) to unlock the unlocking component (3); External excitation is applied to each shape memory hinge (2) in sequence until multiple composite rods (1) are coaxial.

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