Satellite-borne dipole antenna

Abstract

The invention discloses a satellite-borne dipole antenna. The satellite-borne dipole antenna comprises a reflecting plate, a radiation assembly, a supporting rod assembly and a locking and releasing mechanism, the radiation assembly is provided with four inverted-L-shaped radiation sheets in a three-dimensional structure, and every two radiation sheets form a dipole unit. Each radiation sheet is connected to the reflecting plate through a supporting rod assembly, and each supporting rod assembly comprises a telescopic rod and an elastic piece driving the telescopic rod to extend. The locking and releasing mechanism is used for locking the supporting rod assembly in a compressed state and releasing the supporting rod assembly when the supporting rod assembly is controlled, so that the elastic piece drives the telescopic rod to extend and is locked in an extending state, and the distance between the radiation sheet and the reflection plate is changed from a first distance to a larger second distance. Through the combination of the three-dimensional radiation sheet and the compressible expansion mechanism, the problems of large longitudinal size and large emission envelope of a traditional antenna are solved, wide-beam and high-performance work in an on-orbit state is realized, and the antenna has the advantages of compact structure, reliable expansion and excellent electrical performance.

Description

Technical Field

[0001] This application relates to the field of satellite communication equipment technology, and in particular to a spaceborne dipole antenna. Background Technology

[0002] With the rapid development of satellite technology, especially the rise of small satellite constellations, extremely stringent requirements have been placed on the performance and structure of spaceborne antennas. On the one hand, to reduce launch costs, the antenna's loading envelope within the rocket fairing must be as small as possible, requiring the antenna to be compressible or foldable. On the other hand, to achieve reliable satellite communication, the antenna must have wide bandwidth, wide beam coverage, and stable radiation performance after being deployed in orbit.

[0003] In existing technologies, traditional spaceborne dipole antennas are usually fixed structures with large cross-sectional heights, which directly restricts the layout of satellite platforms and increases launch costs.

[0004] To address the size issue, existing technologies employ planar printed inverted L-shaped dipoles. While this achieves a degree of structural compactness, this two-dimensional planar structure inherently suffers from narrow operating bandwidth, low gain, and poor anti-interference capabilities, failing to meet the demands of modern broadband satellite communications. Some large satellite antennas utilize complex and expensive deployable mechanisms such as scissor-type antennas. However, these designs primarily serve high-gain reflector antennas with apertures of several meters or even tens of meters. Their design philosophy, structural complexity, and cost are unsuitable for small spaceborne dipole antennas with extreme requirements for miniaturization, lightweight design, and low cost.

[0005] Therefore, there is an urgent need in this field for an innovative technical solution that can resolve the contradiction between the small envelope of a spaceborne dipole antenna in the transmission state and its high performance in the on-orbit operating state. Summary of the Invention

[0006] The present invention aims to overcome the shortcomings of the prior art and provide a spaceborne dipole antenna to solve the technical problems of large longitudinal size and large transmission envelope of traditional spaceborne antennas, as well as the limited performance of existing miniaturized planar antennas and the difficulty in achieving both wide bandwidth and high reliability.

[0007] The technical solution is as follows:

[0008] According to a first aspect of the present invention, a spaceborne dipole antenna is provided, comprising a reflector and a radiating assembly. The radiating assembly includes four inverted L-shaped radiating plates in a three-dimensional configuration, wherein every two inverted L-shaped radiating plates constitute a dipole unit. The spaceborne dipole antenna further includes four support rod assemblies, each support rod assembly being connected between the reflector and a corresponding inverted L-shaped radiating plate, and including a telescopic rod and an elastic element for driving the telescopic rod to extend. The spaceborne dipole antenna further includes a locking and releasing mechanism. The locking and releasing mechanism is used to lock the support rod assembly in a compressed state and, under controlled conditions, release the support rod assembly so that the telescopic rod extends under the drive of the elastic element and is locked in an extended state. In the compressed state, the distance between the inverted L-shaped radiating plate and the reflector is a first distance; in the extended state, the distance between the inverted L-shaped radiating plate and the reflector is a second distance, and the first distance is less than the second distance.

[0009] Optionally, the radiation assembly further includes a dielectric plate; one side of the dielectric plate is connected to the reflector via the support rod assembly; the inverted L-shaped radiating sheet includes two integrally formed first side plates and second side plates forming a first included angle, the first side plate being fixedly connected to the other side of the dielectric plate, and the second side plate being located on the side of the first side plate closer to the reflector.

[0010] Optionally, the first included angle of each of the inverted L-shaped radiating plates is different.

[0011] Optionally, the four inverted L-shaped radiating plates are installed in a cross-shaped symmetrical distribution around the center of the reflector.

[0012] Optionally, two inverted L-shaped radiating plates located on the same diagonal are connected by a feed conductor to form a dipole unit, and the feed conductors of the two dipole units maintain a set distance.

[0013] Optionally, of the two feed conductors, one feed conductor bends upward and the other feed conductor bends downward.

[0014] Optionally, the telescopic rod includes an outer tube and an inner rod slidably sleeved inside the outer tube, and the elastic element is a helical compression spring sleeved outside the outer tube; the inner rod is provided with a pop-out locking pin, and the outer tube wall is provided with a locking hole; when the inner rod is extended to the extended state, the locking pin is engaged with the locking hole to achieve locking.

[0015] Optionally, the locking release mechanism includes a pull rope and a hot knife; the locking release mechanism further includes a first upright plate and a second upright plate fixedly connected to the reflector plate, the first upright plate being provided with a guide post, and the second upright plate being provided with a rope hole; the first end of the pull rope is connected to the side of the medium plate near the reflector plate, and the pull rope passes through the rope hole after changing direction via the guide post; when the support rod assembly is in a compressed state, the pull rope passes through the rope hole and is locked in the compressed state by a locking structure; the hot knife is in close contact with the pull rope; when the hot knife is heated in a controlled manner, the hot knife can melt the pull rope to allow the inner rod to extend from the outer tube and be locked in the extended state.

[0016] Optionally, the first upright plate is provided with a hinge support, and a hinge shaft is provided inside the hinge support. The handle of the hot knife is connected to the hinge shaft through a connecting rod. The locking and releasing mechanism also includes a tension spring. One end of the tension spring is connected to the handle of the hot knife, and the other end is connected to the first upright plate or the reflector plate. The elastic force of the tension spring provides a torque for the hot knife to rotate around the hinge shaft, so that the cylindrical blade of the hot knife is pressed against the pull rope.

[0017] Optionally, the spaceborne dipole antenna further includes a coaxial cable assembly corresponding to each of the dipole units; the coaxial cable assembly includes a tubular outer conductor and a cylindrical inner conductor disposed within the tubular outer conductor; the tubular outer conductor is connected to the dielectric substrate through an insulating support block, and the cylindrical inner conductor is electrically connected to the corresponding feed conductor; the cylindrical inner conductor is connected to the polarizer through an RF cable.

[0018] The beneficial effects of the technical solutions provided in this application include at least the following:

[0019] The spaceborne dipole antenna includes a reflector and a radiating assembly. The radiating assembly comprises four three-dimensional inverted L-shaped radiating plates, with each pair of inverted L-shaped radiating plates forming a dipole unit. Each radiating plate is connected to the reflector via a support rod assembly containing a telescopic rod and a drive spring, and is controlled by a locking and releasing mechanism. The spaceborne deployable dipole antenna provided by this invention has the following significant advantages: Through the telescopic design of the support rod assembly and the constraint of the locking and releasing mechanism, the antenna can be reliably compressed to its lowest profile height before launch, significantly optimizing the space utilization of the launch vehicle and effectively reducing launch costs. The three-dimensional metal radiating plates have superior radiation efficiency and bandwidth potential compared to planar printed structures. The array of four radiating plates, combined with a specific spatial layout and feeding, can achieve high-performance indicators such as wide beam and circular polarization. The locking and releasing mechanism adopts a non-explosive unlocking scheme of hot-blade melting the pull rope, combined with the mechanical self-locking structure inside the support rod, achieving a one-time successful deployment and secure locking after deployment, meeting the requirements of long space life and high reliability. This invention highly integrates a high-performance radiator, a reliable deployment and recovery mechanism, and a low-loss power supply network, achieving complex functions while ensuring a simple, lightweight, and manufacturable structure, making it particularly suitable for application on small satellite platforms.

[0020] Other features and advantages of this disclosure will be described in detail in the following detailed description section. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0022] Figure 1 This is a three-dimensional schematic diagram of the first view of the spaceborne dipole antenna provided in the embodiments of this application;

[0023] Figure 2 This is a three-dimensional schematic diagram of the second view of the spaceborne dipole antenna provided in the embodiments of this application;

[0024] Figure 3 This is a three-dimensional schematic diagram of the third-view spaceborne dipole antenna provided in the embodiments of this application;

[0025] Figure 4 This is a partial three-dimensional schematic diagram of the locking and releasing mechanism in the spaceborne dipole antenna provided in the embodiments of this application;

[0026] Figure 5 This is a three-dimensional schematic diagram of the support rod assembly in the spaceborne dipole antenna provided in the embodiments of this application;

[0027] Figure 6 It is the radiation pattern of the spaceborne dipole antenna at fl (the lowest frequency point);

[0028] Figure 7 It is the radiation pattern of the spaceborne dipole antenna at f0 (center frequency);

[0029] Figure 8 It is the radiation pattern of the spaceborne dipole antenna at fu (the highest frequency point).

[0030] Explanation of reference numerals in the attached figures

[0031] 1-Reflector; 2-Radiation assembly; 201-Inverted L-shaped radiating plate; 202-Dielectric plate; 203-Feed conductor; 3-Support rod assembly; 301-Telescopic rod; 3011-Outer tube; 3012-Inner rod; 3013-Locking pin; 302-Elastic element; 4-Locking and releasing mechanism; 401-Pull rope; 402-Hot knife; 403-First upright plate; 404-Second upright plate; 405-Guide column; 406-Hinge shaft; 407-Tension spring; 5-Coaxial cable assembly; 501-Tubular outer conductor; 502-Columnar inner conductor; 6-RF cable; 7-Polarizer. Detailed Implementation

[0032] The specific embodiments of this disclosure will be described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are for illustration and explanation only and are not intended to limit this disclosure.

[0033] In this disclosure, unless otherwise stated, directional terms such as "upper" and "lower" generally refer to the relative positions of the corresponding components in the direction of gravity when they are in use, and "inner" and "outer" refer to their relative positions to the contours of the corresponding components themselves. Furthermore, the terms "first," "second," etc., used in this disclosure are for distinguishing one element from another and do not have sequential or importance implications. In the following description, when referring to the accompanying drawings, unless otherwise explained, the same reference numerals in different drawings denote the same or similar elements.

[0034] The present invention will now be described in detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are for illustrative purposes only and are not intended to limit the scope of the invention.

[0035] According to the embodiments of this application, refer to Figures 1 to 5The spaceborne dipole antenna includes a reflector 1 and a radiating assembly 2. The radiating assembly 2 comprises four three-dimensional inverted L-shaped radiating plates 201, with each pair of inverted L-shaped radiating plates 201 forming a dipole unit. Each radiating plate is connected to the reflector 1 via a support rod assembly 3, which includes a telescopic rod 301 and a drive spring, and is controlled by a locking and releasing mechanism 4. The locking and releasing mechanism 4 locks the support rod assembly 3 in a compressed state and releases it under controlled conditions, allowing the telescopic rod 301 to extend under the drive of the elastic element 302 and lock in the extended state. In the compressed state, the distance between the inverted L-shaped radiating plate 201 and the reflector 1 is a first distance; in the extended state, the distance between the inverted L-shaped radiating plate 201 and the reflector 1 is a second distance, and the first distance is less than the second distance.

[0036] Traditional fixed dipole antennas suffer from limited loading envelope due to their large profile height, while planar printed structures have performance defects. This design resolves the contradiction between small envelope and high performance by combining a three-dimensional inverted L-shaped radiating plate, a telescopic support rod assembly 3, and a locking and releasing mechanism 4. The four inverted L-shaped radiating plates, in a three-dimensional configuration, can optimize the radiation field distribution through spatial layout compared to a two-dimensional planar structure, laying the foundation for wideband and wide beam performance. Each pair of radiating plates forms a dipole unit, and radiation stability can be improved through symmetrical design.

[0037] The support rod assembly 3 serves as a telescopic mechanism, with its telescopic rod 301 working in conjunction with the elastic element 302 to achieve the functional conversion of compression, storage, release, and deployment. During the satellite launch phase, the locking and release mechanism 4 locks the support rod assembly 3 in a compressed state. At this time, the first distance between the inverted L-shaped radiating plate 201 and the reflector 1 is minimized, and the overall profile height of the spaceborne dipole antenna is significantly reduced, meeting the minimum loading envelope requirements of the rocket fairing. After the satellite is in orbit, the locking and release mechanism 4 is released under control, and the elastic element 302 drives the telescopic rod 301 to extend and lock. The increase in the second distance allows the radiating assembly 2 to obtain a reasonable working height, ensuring radiation performance.

[0038] This design eliminates the need for complex transmission structures, directly driving the device via the elastic element 302, thus achieving both lightweight design and low cost, making it suitable for small satellites. Compared to the complex mechanisms of existing large deployable antennas, this solution features a simple and reliable structure with a low failure rate; compared to planar printed dipoles, the three-dimensional configuration and reasonable operating height significantly improve bandwidth, gain, and anti-interference capabilities.

[0039] According to the embodiments of this application, refer to Figures 1 to 3The radiation assembly 2 further includes a dielectric plate 202; one side of the dielectric plate 202 is connected to the reflector plate 1 via the support rod assembly 3; the inverted L-shaped radiation sheet 201 includes two integrally formed first side plates and second side plates forming a first included angle, the first side plate is fixedly connected to the other side of the dielectric plate 202, and the second side plate is located on the side of the first side plate closer to the reflector plate 1.

[0040] This embodiment adds a dielectric substrate 202 and optimizes the structure of the inverted L-shaped radiating plate, further improving the structural stability and radiation performance of the antenna. From an assembly perspective, the dielectric substrate 202 serves as a bearing reference: one side is connected to the reflector 1 via four support rod assemblies 3, ensuring the installation position accuracy of the four radiating plates and preventing the layout of the radiating elements from shifting due to installation errors of the support rod assemblies 3, thus affecting the cooperative radiation effect of the dipole units; the other side fixes the inverted L-shaped radiating plate 201, providing a stable mounting carrier for the inverted L-shaped radiating plate 201, while the insulation characteristics of the dielectric substrate 202 prevent short circuits between the radiating plate and other metal components. The inverted L-shaped radiating plate 201 uses an integrally formed first side plate and second side plate, which reduces assembly gaps and contact resistance compared to a spliced ​​structure, improving radiation efficiency; the first side plate is fixed to the dielectric substrate 202, and the layout of the second side plate facing the reflector 1 allows the radiating plate to form a reasonable spatial orientation, and the second side plate can form coupled radiation with the reflector 1, further widening the operating bandwidth. The integrated structural design simplifies the manufacturing process, reduces production costs, and enhances the mechanical strength of the radiating element, enabling it to withstand the vibration environment during satellite launch and the on-orbit space environment. The introduction of the dielectric substrate 202 not only does not significantly increase the antenna weight but also achieves a modular design for the radiating component 2 through structural integration, facilitating assembly and maintenance. For example, the dielectric substrate 202 can be made of lightweight, high-strength materials such as polytetrafluoroethylene (PTFE).

[0041] The dielectric plate 202 plays a crucial role as a multifunctional integrated carrier. One side of the dielectric plate 202 is used to centrally connect to the upper ends of the four support rod assemblies 3, integrating the four dispersed mechanical support points into a stable mounting plane, simplifying the structure and assembly. Its other side is used to fix four inverted L-shaped radiating plates 201. Here, the inverted L-shaped radiating plates 201 are specifically defined as two integrally formed first side plates and second side plates at a first included angle. The first side plate is fixed to the dielectric plate 202, ensuring the stability of the radiator under mechanical vibration; the second side plate, set at the first included angle, extends freely, and its angle directly determines the horizontal projection and spatial orientation of the radiating plate.

[0042] The "fixed side + radiating side" configuration design of the inverted L-shaped radiating plate 201 in this embodiment brings multiple benefits: First, it simplifies the installation of the complex three-dimensional radiating plate into a single-plane fastening operation, reducing the requirements for manufacturing and assembly precision; Second, the dielectric plate 202 itself can be made of low-loss composite material, which plays a certain role in radio frequency insulation and support.

[0043] According to the embodiments of this application, refer to Figures 1 to 3 Each inverted L-shaped radiating plate 201 has a different first included angle.

[0044] Traditional dipole antennas typically use radiating plates with the same included angle, which limits the operating bandwidth. This design significantly widens the bandwidth by making the first included angle of each inverted L-shaped radiating plate 201 different, thus solving the inherent defect of narrow bandwidth in existing planar dipoles.

[0045] From the perspective of radiation principles, the first included angle of the inverted L-shaped radiating plate 201 directly affects its impedance characteristics and radiation frequency range: inverted L-shaped radiating plates 201 with different first included angles correspond to different resonant frequencies. Designing four inverted L-shaped radiating plates 201 with different first included angles is equivalent to integrating multiple radiating elements with different resonant frequencies in a spaceborne dipole antenna. When two inverted L-shaped radiating plates 201 with different first included angles form a dipole unit, the operating bandwidth of this dipole unit will cover the resonant frequency range of the two radiating plates; the combination of two dipole units further widens the overall bandwidth, enabling the antenna to adapt to the multi-frequency requirements of modern broadband satellite communication. At the same time, the differentiated design of the first included angle does not destroy the symmetry of the radiating component 2 and will not affect the wide beam coverage performance. Compared with existing schemes that widen the bandwidth by increasing the number of radiating elements, this design does not require an additional number of radiating plates; the bandwidth can be improved simply by adjusting the first included angle, taking into account both structural compactness and lightweight design. The integral molding structure of each inverted L-shaped radiating plate 201 ensures the accuracy of the included angle, avoids performance fluctuations caused by deviation of the first included angle, and improves the consistency of the antenna.

[0046] According to the embodiments of this application, refer to Figures 1 to 3 The four inverted L-shaped radiating plates 201 are installed in a cross-shaped symmetrical distribution around the center of the reflector plate 1.

[0047] Based on the different first included angles of each inverted L-shaped radiating plate 201, a cross-shaped symmetrical distribution layout is adopted to further optimize the radiation characteristics and structural stability of the dipole antenna.

[0048] From the perspective of radiation field distribution, the four L-shaped radiating plates 201 are installed in a cross-shaped symmetrical distribution, so that the four inverted L-shaped radiating plates 201 uniformly surround the center of the reflector plate 1. The two dipole units are arranged along the two diagonals respectively, forming an orthogonal radiation field, which can achieve 360° wide beam coverage and meet the omnidirectional radiation requirements in satellite communication.

[0049] The symmetrical layout effectively counteracts the radiation field distortion caused by the different first included angles of a single inverted L-shaped radiating plate 201, resulting in a more uniform radiation pattern for the spaceborne dipole antenna and improved radiation performance stability. From a mechanical perspective, the cross-shaped distribution of the four L-shaped radiating plates 201 ensures uniform stress distribution across the four support rod assemblies 3. During the compression phase of launch and the elongation phase in orbit, the forces on the dielectric plate 202 and radiating assembly 2 are more balanced, reducing local stress concentration and improving the structural reliability of the spaceborne dipole antenna, thus better resisting shocks and vibrations during launch. Furthermore, the symmetrical layout reduces the design complexity of the feed network and ensures that the center of gravity of the spaceborne dipole antenna coincides with the center of the reflector 1, which is beneficial for satellite platform attitude control. Compared to the asymmetrical layout, this scheme offers more stable radiation performance, a more reliable structure, and meets the high-precision requirements of satellite operation in orbit.

[0050] According to the embodiments of this application, refer to Figures 1 to 3 The two inverted L-shaped radiating plates 201 located on the same diagonal are connected by a feed conductor 203 to form a dipole unit, and the feed conductors 203 of the two dipole units maintain a set distance.

[0051] From the perspective of the composition logic of the dipole element, two radiating plates on the same diagonal constitute a dipole element. This fully utilizes the symmetry of the cross-shaped layout, allowing the two dipole elements to form an orthogonal configuration, further enhancing the wide beam coverage effect. The feed conductor 203 directly connects to the two inverted L-shaped radiating plates 201 of the same element, achieving efficient energy transmission. Compared with indirect feeding methods, this reduces energy loss and improves antenna gain. Maintaining a set distance between the feed conductors 203 of the two dipole elements is to avoid feed interference. Because the feed conductor 203 generates an electromagnetic field when transmitting energy, if the distance is too close, the electromagnetic fields of the two dipole elements will couple with each other, leading to impedance mismatch, narrowing bandwidth, and other problems. By setting a reasonable distance, the electromagnetic fields of the two elements can be effectively isolated, ensuring that each dipole element operates independently and stably. At the same time, it makes it easier to match the impedance characteristics of the spaceborne dipole antenna, thereby improving communication quality. This design, combined with a cross-shaped layout and differentiated angles, enhances the performance of the spaceborne dipole antenna in terms of wide bandwidth, wide beam, and high gain, meeting the high-performance requirements of modern satellite communications.

[0052] According to the embodiments of this application, refer to Figures 1 to 3The two feed conductors 203 are arranged such that one bends upward and the other bends downward. Designing the two feed conductors 203 as upper and lower bow shapes with opposite bending directions and facing away from each other is a further optimization of the feed layout, which takes into account both structural compactness and anti-interference performance.

[0053] From a spatial layout perspective, the upper and lower bow-shaped design allows the two feed conductors 203 to be staggered in three-dimensional space. Compared to a planar parallel arrangement, this significantly reduces the planar size of the feed area while maintaining the set isolation distance, thus meeting the compact design requirements of the radiating component 2. The opposite bending directions of the upper and lower bows create complementary electromagnetic field distributions for the two conductors, further reducing the risk of mutual coupling and improving anti-interference capabilities. The curved structure also increases the length of the feed conductors 203. By adjusting the bending radius and curvature, the impedance characteristics of the conductors can be optimized, resulting in more precise impedance matching of the antenna and thus improving radiation efficiency. Furthermore, the bow-shaped structure has better mechanical flexibility than a straight structure, adapting to vibrations during satellite launch and temperature changes in orbit, reducing feed failures caused by deformation. This design eliminates the need for additional isolation components; isolation and impedance optimization are achieved through structural morphology optimization, balancing lightweight design and low cost, consistent with the overall antenna design philosophy.

[0054] According to the embodiments of this application, refer to Figure 1 and Figure 5 The telescopic rod 301 includes an outer tube 3011 and an inner rod 3012 slidably sleeved inside the outer tube 3011. The elastic element 302 is a helical compression spring sleeved outside the outer tube 3011. The inner rod 3012 is provided with a pop-out locking pin 3013. The outer tube 3011 has a locking hole on its wall. When the inner rod 3012 is extended to the extended state, the locking pin 3013 is engaged in the locking hole to achieve locking.

[0055] This embodiment provides a specific structure for the telescopic rod 301 and the elastic element 302, as well as the locking method after deployment, ensuring the telescopic reliability and operational stability of the support rod assembly 3. The nested structure of the outer tube 3011 and the inner rod 3012 is simple and compact, with low sliding resistance, enabling smooth telescopic movements. The helical compression spring is sleeved on the outside of the outer tube 3011, which is easier to install and maintain compared to the built-in spring. At the same time, the elastic force of the helical compression spring can directly act on the ends of the inner rod 3012 and the outer tube 3011, driving the inner rod 3012 to extend quickly.

[0056] During satellite launch, the helical compression spring is compressed, providing sufficient elastic potential energy for deployment. After the satellite is released in orbit, the elastic force of the helical compression spring is converted into the kinetic energy of the inner rod 3012, enabling rapid deployment without the need for an additional drive device, thus simplifying the structure. The locking pin 3013 and the locking hole ensure reliable locking after deployment: when the inner rod 3012 extends to the set position, the locking pin 3013 pops out under the action of its own spring and engages with the locking hole, preventing the inner rod 3012 from retracting due to vibration or external forces in the orbital environment, thereby ensuring the stable working height of the radiation assembly 2. This locking method is mechanical self-locking, requiring no continuous power supply, thus reducing the satellite's energy consumption.

[0057] The elastic element 302 can also be a rubber spring. Rubber springs have good elastic recovery performance and also possess certain damping characteristics, enabling them to absorb vibration energy during the emission phase and reduce the impact of vibration on the radiation component 2. They are compact, lightweight, and can be molded, resulting in lower production costs. The rubber spring is sleeved on the outside of the outer tube 3011, with its two ends abutting against the limiting platform of the inner rod 3012 and the end of the outer tube 3011, respectively. Under compression, it stores elastic potential energy, and upon release, it drives the inner rod 3012 to extend.

[0058] According to the embodiments of this application, refer to Figures 2 to 4The locking and releasing mechanism 4 includes a pull rope 401 and a hot knife 402. The locking and releasing mechanism 4 also includes a first upright plate 403 and a second upright plate 404 fixedly connected to the reflector plate 1. The first upright plate 403 is provided with a guide post 405, and the second upright plate 404 is provided with a rope threading hole. The first end of the pull rope 401 is connected to the side of the medium plate 202 near the reflector plate 1. After the pull rope 401 changes direction via the guide post 405, it passes through the rope threading hole. When the support rod assembly 3 is in a compressed state, the pull rope 401 passes through the rope threading hole and is locked in the compressed state by a locking structure. The hot knife 402 is in close contact with the pull rope 401. When the hot knife 402 is heated in a controlled manner, it can melt the pull rope 401, causing the inner rod 3012 to extend from the outer tube 3011 and lock in the extended state. The locking and releasing mechanism 4 achieves locking of the support rod assembly 3 in the compressed state and precise release on track. During the launch phase, the support rod assembly 3 is in a compressed state. One end of the pull rope 401 is connected to the dielectric plate 202. After being guided by the guide post 405, it passes through the rope hole and is knotted. The tension of the pull rope 401 counteracts the elastic force of the elastic element 302, firmly locking the dielectric plate 202 and the radiating assembly 2 in the compressed position, ensuring that the antenna maintains a minimal loading envelope during launch. The first upright plate 403 and the second upright plate 404 provide a stable mounting base for the guide post 405 and the rope hole. The guide post 405 can change the direction of force on the pull rope 401, so that the tension of the pull rope 401 is evenly applied to the dielectric plate 202, avoiding excessive local stress that could cause deformation of the dielectric plate 202. The rope hole limits the pull rope 401. After the pull rope 401 passes through the rope hole, it is compressed by a locking structure. The locking structure can be a mechanical lock or a knot tied after the pull rope extends out of the rope hole. In this way, the position of the radiating assembly 2 is determined by the restoring force of the elastic element 302.

[0059] The hot knife 402, serving as the release actuator, features a simple structure and rapid response: After the satellite is in orbit, the ground control system sends a command to the hot knife 402, which then heats up and quickly melts the pull rope 401. Upon failure of the pull rope 401, the elastic force of the elastic element 302 drives the telescopic rod 301 to extend, thus deploying the radiation assembly 2. This locking method eliminates the need for complex mechanical transmissions, the knotting operation of the pull rope 401 is simple, and the locking is reliable. The hot knife 402's melt-and-release mechanism has a short response time and low failure rate. Compared to electromagnetic release mechanisms, the hot knife 402 has a simpler structure, lighter weight, and lower cost, making it suitable for the needs of small satellites. The pull rope 401 can be made of high-strength, low-melting-point materials such as nylon or aramid to ensure it can withstand sufficient tension during launch while being quickly melted by the hot knife 402.

[0060] According to the embodiments of this application, refer to Figures 2 to 4The first upright plate 403 is provided with a hinge support, and a hinge shaft 406 is provided inside the hinge support. The handle of the hot knife 402 is connected to the hinge shaft 406 through a connecting rod. The locking and releasing mechanism 4 also includes a tension spring 407. One end of the tension spring 407 is connected to the handle of the hot knife 402, and the other end is connected to the first upright plate 403 or the reflector plate 1. The elastic force of the tension spring 407 provides a torque for the hot knife 402 to rotate around the hinge shaft 406, so that the cylindrical blade of the hot knife 402 is pressed against the pull rope 401.

[0061] This design optimizes the contact state between the hot blade 402 and the pull rope 401 through a hinged support and a tension spring 407, ensuring the reliability of the release action. The hot blade 402 is connected to the hinged support of the first vertical plate 403 through a hinge shaft 406, and can rotate around the hinge shaft 406. Combined with the elastic force of the tension spring 407, it ensures that the cylindrical blade head of the hot blade 402 always presses against the pull rope 401.

[0062] This design solves the problem of poor contact between the hot blade 402 and the pull cord 401 caused by factors such as vibration and installation errors: vibration during the launch phase may cause a slight shift in the pull cord 401, and the elastic force of the tension spring 407 will drive the hot blade 402 to rotate accordingly, maintaining a tight contact between the blade head and the pull cord 401; during installation, even if there are minor dimensional errors, the tension spring 407 can compensate through elastic deformation to ensure stable contact pressure. The cylindrical blade head design increases the contact area with the pull cord 401, making heat conduction more efficient, enabling rapid melting of the pull cord 401, and shortening the release time.

[0063] The tension of the tension spring 407 can be adjusted by selecting the appropriate type and installation position to ensure that it provides sufficient clamping force without causing premature damage to the pull rope 401 due to excessive pressure.

[0064] This design further enhances the reliability of the locking and releasing mechanism 4, avoids release failure due to poor contact, ensures the success rate of on-orbit deployment of the dipole antenna, and meets the high reliability requirements of satellite technology.

[0065] According to the embodiments of this application, refer to Figures 1 to 3The spaceborne dipole antenna further includes a coaxial cable assembly 5 corresponding to each dipole element; the coaxial cable assembly 5 includes a tubular outer conductor 501 and a cylindrical inner conductor 502 disposed within the tubular outer conductor 501; the tubular outer conductor 501 is connected to the dielectric substrate 202 through an insulating support block, and the cylindrical inner conductor 502 is electrically connected to the corresponding feed conductor 203; the cylindrical inner conductor 502 is connected to the polarizer 7 through an RF cable 6. In this example, the polarizer 7 uses a 3dB bridge, where the two output ports provide feed signals with a 90° phase difference to the two feed points through the RF cable 6, achieving circular polarization and simultaneously expanding the antenna bandwidth.

[0066] This design achieves efficient power feeding for the dipole units through coaxial cable assembly 5, ensuring signal transmission stability and anti-interference capability. Each dipole unit corresponds to a set of coaxial cable assemblies 5, achieving independent power feeding and avoiding signal crosstalk caused by multiple units sharing the feed line, thus improving communication quality. The coaxial cable assembly 5 adopts a structure of tubular outer conductor 501 and cylindrical inner conductor 502. The tubular outer conductor 501 acts as a shield, effectively isolating spatial electromagnetic interference and preventing external interference signals from entering the feed line and affecting the antenna's receiving performance. It also prevents signals inside the feed line from radiating outwards, causing energy loss, making it particularly suitable for complex space electromagnetic environments. The tubular outer conductor 501 is connected to the dielectric substrate 202 through an insulating support block. The insulating support block not only ensures electrical isolation between the outer conductor and the dielectric substrate 202 and the radiating component 2, but also provides stable installation and fixation for the coaxial cable assembly 5, preventing the feed line connection from loosening due to satellite vibration. The columnar inner conductor 502 is directly electrically connected to the feed conductor 203, resulting in low contact resistance and low signal transmission loss. This maximizes the transmission of satellite signals to the radiating component 2, or the transmission of signals received by the radiating component 2 to the satellite receiving system. The coaxial cable assembly 5 has a mature structure and low manufacturing cost. Its independent design corresponding to the dipole unit facilitates feeder matching based on the impedance characteristics of each unit, further improving the antenna's radiation efficiency and bandwidth performance.

[0067] To make the working principle of this invention easier to understand, the complete working process of the spaceborne dipole antenna of this application is described in detail below with reference to specific embodiments:

[0068] Launch Phase: After the spaceborne dipole antenna is assembled, the inner rods 3012 of the four support rod assemblies 3 are first pressed into the outer tube 3011. The helical compression spring 302, acting as an elastic element, is compressed and stores elastic potential energy. At this time, the inverted L-shaped radiating plate 201 moves closer to the reflector plate 1 along with the dielectric plate 202, with the distance between them being the first distance. At this point, the dipole antenna is in the minimum envelope state. Subsequently, one end of the pull rope 401 of the locking release mechanism 4 is connected to the side of the dielectric plate 202 near the reflector plate 1. After being guided by the guide post 405 of the first upright plate 403, it passes through the rope hole of the second upright plate 404 and is knotted. The tension of the pull rope 401 counteracts the elastic force of the helical compression spring, firmly locking the dielectric plate 202 and the radiating assembly 2 in the compressed position, ensuring that the dipole antenna occupies a minimal loading envelope within the rocket fairing, meeting the launch requirements. At this time, the cylindrical blade of the hot knife 402 is pressed tightly against the pull rope 401 by the elastic force of the tension spring 407; the tubular outer conductor 501 of the coaxial cable assembly 5 is fixed to the dielectric plate 202 by the insulating support block, and the cylindrical inner conductor 502 and the corresponding feed conductor 203 have been electrically connected.

[0069] In-orbit deployment phase: After the satellite enters its predetermined orbit, the ground control system sends a power-on command to the hot knife 402 of the dipole antenna. Upon power-on, the hot knife 402 heats up rapidly. Due to the close contact between the cylindrical blade and the pull rope 401, heat is quickly transferred to the pull rope 401, causing it to melt and break. After the pull rope 401 melts, its tension on the dielectric plate 202 disappears, and the helical compression springs in the four support rod assemblies 3 release their elastic potential energy, driving the inner rod 3012 to quickly extend from the outer tube 3011. When the inner rod 3012 extends to the set position, the locking pin 3013 on the inner rod 3012 pops out under the action of its own spring, engaging with the locking hole in the wall of the outer tube 3011, achieving mechanical locking of the telescopic rod 301. At this time, the distance between the inverted L-shaped radiating plate 201 and the reflector 1 reaches the second distance, and the radiating assembly 2 enters the working position.

[0070] In-orbit operation phase: After locking, the onboard dipole antenna enters normal operation. The satellite's transmitted signal is transmitted to the two dipole units via two sets of coaxial cable assemblies 5: the cylindrical inner conductor 502 transmits the signal to the feed conductor 203, which then distributes it to two inverted L-shaped radiating plates 201 on the same diagonal. Since the first included angles of the four inverted L-shaped radiating plates 201 are different, a wide bandwidth coverage is formed. The first and second side plates of the inverted L-shaped radiating plates 201 form coupled radiation. The three-dimensional configuration and cross-shaped symmetrical distribution enable the antenna to generate a 360° wide beam radiation field, meeting the omnidirectional communication requirements. The tubular outer conductor 501 of the coaxial cable assembly 5 acts as a shield to resist space electromagnetic interference. The reflector 1 serves as a reflective surface, further enhancing the radiation gain. When receiving signals, the space signal received by the radiating assembly 2 is transmitted to the satellite receiving system via the feed conductor 203 and the coaxial cable assembly 5, completing the communication link. Throughout the entire operation, the mechanical structure remained stable and reliable, and the power supply transmission was highly efficient, achieving a perfect combination of extremely small launch envelope and high-performance on-orbit operation.

[0071] Verification has shown that this design results in a significantly smaller longitudinal envelope size for the dipole antenna during transmission compared to its on-orbit operational state.

[0072] In terms of antenna performance, such as Figure 6 As shown, the radiation pattern of the spaceborne dipole antenna at fl (the lowest frequency point) has a gain of 0.98 dBi at -60° and a gain of 0.92 dBi at 60°.

[0073] like Figure 7 As shown, the radiation pattern of the spaceborne dipole antenna at f0 (center frequency) has a gain of 0.90 dBi at -60° and a gain of 0.11 dBi at 60°.

[0074] like Figure 8 The image shows the radiation pattern of the spaceborne dipole antenna at fu (the highest frequency point). The gain is 1.26 dBi at -60° and 0.54 dBi at 60°.

[0075] In summary, this dipole antenna achieves wide-angle beam coverage within its operating frequency band.

[0076] It should also be noted that the various specific technical features described in the above embodiments can be combined in any suitable manner without contradiction. To avoid unnecessary repetition, this disclosure will not describe the various possible combinations separately.

[0077] Furthermore, various different embodiments of this disclosure can be combined in any way, as long as they do not violate the spirit of this disclosure, they should also be regarded as the content disclosed in this disclosure.

Claims

1. A spaceborne dipole antenna, comprising a reflector (1) and a radiating assembly (2), characterized in that, The radiation assembly (2) includes four inverted L-shaped radiating plates (201) in a three-dimensional configuration, wherein every two inverted L-shaped radiating plates (201) constitute a dipole unit; The spaceborne dipole antenna also includes four support rod assemblies (3), each of which is connected between the reflector (1) and a corresponding inverted L-shaped radiating plate (201), and includes a telescopic rod (301) and an elastic element (302) for driving the telescopic rod (301) to extend. The spaceborne dipole antenna also includes a locking release mechanism (4). The locking release mechanism (4) is used to lock the support rod assembly (3) in a compressed state and release the support rod assembly (3) in a controlled manner so that the telescopic rod (301) extends under the drive of the elastic element (302) and is locked in an extended state; In the compressed state, the distance between the inverted L-shaped radiating plate (201) and the reflector (1) is a first distance, and in the extended state, the distance between the inverted L-shaped radiating plate (201) and the reflector (1) is a second distance, and the first distance is less than the second distance.

2. The spaceborne dipole antenna according to claim 1, characterized in that, The radiation assembly (2) also includes a dielectric plate (202); One side of the medium plate (202) is connected to the reflector (1) via the support rod assembly (3); The inverted L-shaped radiating plate (201) includes two integrally formed first side plates and second side plates forming a first included angle. The first side plate is fixedly connected to the other side of the dielectric plate (202), and the second side plate is located on the side of the first side plate close to the reflector plate (1).

3. The spaceborne dipole antenna according to claim 2, characterized in that, The first included angle of each of the inverted L-shaped radiating plates (201) is different.

4. The spaceborne dipole antenna according to claim 3, characterized in that, The four inverted L-shaped radiating plates (201) are installed in a cross-shaped symmetrical distribution around the center of the reflector (1).

5. The spaceborne dipole antenna according to claim 4, characterized in that, Two inverted L-shaped radiating plates (201) located on the same diagonal are connected by a feed conductor (203) to form a dipole unit, and the feed conductors (203) of the two dipole units maintain a set distance.

6. The spaceborne dipole antenna according to claim 5, characterized in that, Two feed conductors (203) are provided, one of which bends upward and the other bends downward.

7. The spaceborne dipole antenna according to claim 2, characterized in that, The telescopic rod (301) includes an outer tube (3011) and an inner rod (3012) slidably sleeved inside the outer tube (3011). The elastic element (302) is a helical compression spring sleeved outside the outer tube (3011). The inner rod (3012) is provided with a pop-out locking pin (3013), and the outer tube (3011) has a locking hole on its tube wall. When the inner rod (3012) is extended to the extended state, the locking pin (3013) is engaged in the locking hole to achieve locking.

8. The spaceborne dipole antenna according to claim 7, characterized in that, The locking release mechanism (4) includes a pull rope (401) and a hot knife (402). The locking release mechanism (4) further includes a first upright plate (403) and a second upright plate (404) fixedly connected to the reflector plate (1). The first upright plate (403) is provided with a guide post (405), and the second upright plate (404) is provided with a rope hole. The first end of the pull rope (401) is connected to the side of the medium plate (202) near the reflector (1). The pull rope (401) changes direction after passing through the guide post (405) and then passes through the rope hole. When the support rod assembly (3) is in a compressed state, the pull rope (401) passes through the rope hole and then passes through the locking structure to lock the compressed state. The hot knife (402) is in close contact with the pull rope (401); when the hot knife (402) is heated in a controlled manner, the hot knife (402) can melt the pull rope (401) so that the inner rod (3012) extends out of the outer tube (3011) and is locked in the extended state.

9. The spaceborne dipole antenna according to claim 8, characterized in that, A hinge support is provided on the first upright plate (403), and a hinge shaft (406) is provided inside the hinge support. The handle of the hot knife (402) is connected to the hinge shaft (406) through a connecting rod. The locking release mechanism (4) further includes a tension spring (407), one end of which is connected to the handle of the hot knife (402), and the other end is connected to the first upright plate (403) or the reflector plate (1). The elastic force of the tension spring (407) provides the hot knife (402) with a torque to rotate about the hinge axis (406), so that the cylindrical blade of the hot knife (402) is pressed against the pull rope (401).

10. The spaceborne dipole antenna according to claim 5, characterized in that, The spaceborne dipole antenna also includes a coaxial cable assembly (5) corresponding to each dipole unit; the coaxial cable assembly (5) includes a tubular outer conductor (501) and a cylindrical inner conductor (502) disposed inside the tubular outer conductor (501); the tubular outer conductor (501) is connected to the dielectric substrate (202) through an insulating support block, and the cylindrical inner conductor (502) is electrically connected to the corresponding feed conductor (203); the cylindrical inner conductor (502) is connected to the polarizer (7) through a radio frequency cable (6).

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