CN108493591A - Spaceborne VHF antenna assemblies - Google Patents
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- H—ELECTRICITY
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- H01Q15/00—Devices for reflection, refraction, diffraction or polarisation of waves radiated from an antenna, e.g. quasi-optical devices
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- H01Q19/00—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic
- H01Q19/10—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces
- H01Q19/104—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces using a substantially flat reflector for deflecting the radiated beam, e.g. periscopic antennas
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Abstract
本发明的目的在于提供一种星载VHF天线装置，其是一种平面变形加载IFA的线极化星载VHF天线装置，包括反射板、馈电单元及天线辐射单元。天线辐射单元包括：由左侧天线辐射片和上侧天线辐射片构成的平面倒F天线主体部；及位于上侧天线辐射片的右侧末端的多片末端天线辐射片。馈电单元设置在反射板与天线辐射单元的上侧天线辐射片之间。根据本发明，能在满足现有天线主要电性能指标要求的同时，兼具小型化、轻量化、对各类卫星(尤其是微小卫星、微纳卫星))适应性高等优点。
The object of the present invention is to provide a space-borne VHF antenna device, which is a linearly polarized space-borne VHF antenna device loaded with plane deformation IFA, including a reflector, a feed unit and an antenna radiation unit. The antenna radiating unit includes: a planar inverted-F antenna main body composed of a left antenna radiating piece and an upper antenna radiating piece; and a plurality of terminal antenna radiating pieces located at the right end of the upper antenna radiating piece. The feed unit is arranged between the reflection plate and the upper antenna radiation piece of the antenna radiation unit. According to the present invention, while meeting the main electrical performance index requirements of existing antennas, it also has the advantages of miniaturization, light weight, and high adaptability to various satellites (especially micro-satellites and micro-nano satellites).
Description
技术领域technical field
本发明涉及星载通信系统所使用的星载VHF天线装置。The invention relates to a spaceborne VHF antenna device used in a spaceborne communication system.
背景技术Background technique
VHF频段是现有卫星数据通信的主要频段，被广泛应用于各类卫星的短数据通信和重要信息实时下传。相对于其它微波频段，VHF频段的信号频率较低，波长较长，因此与之对应的天线尺寸也较大。The VHF frequency band is the main frequency band of existing satellite data communication, and is widely used in short data communication of various satellites and real-time downloading of important information. Compared with other microwave frequency bands, the VHF frequency band has a lower signal frequency and a longer wavelength, so the corresponding antenna size is also larger.
伴随着航天技术的飞速发展，微小卫星、微纳卫星被越来越广泛地应用，相应地，卫星体积、重量和功耗等也日益减小。因而，对于将VHF频段用作为通信频段的VHF天线而言，VHF天线小型化、轻量化设计和应用的要求不断增高。因此，在保持天线已有效能的情况下，如何精简VHF天线尺寸，使之适应未来更多类型的卫星应用是VHF链路和VHF天线研制的主要方向和必由之路。With the rapid development of aerospace technology, micro-satellites and micro-nano-satellites are more and more widely used, and correspondingly, the size, weight and power consumption of satellites are also decreasing day by day. Therefore, for a VHF antenna using the VHF frequency band as a communication frequency band, the requirements for miniaturization, lightweight design and application of the VHF antenna are increasing. Therefore, how to reduce the size of the VHF antenna and make it suitable for more types of satellite applications in the future is the main direction and the only way for the development of VHF links and VHF antennas while maintaining the effective performance of the antenna.
发明内容Contents of the invention
发明所要解决的技术问题The technical problem to be solved by the invention
众所周知，天线的辐射效率与性能直接与天线的物理口径相关，当天线物理口径显著缩小时，在相同工作频率上天线性能会急剧恶化，甚至难以满足正常使用需求，无法有效接收和辐射电磁波。由于VHF使用频段的限制，VHF天线工作波长超过2m，因而常规天线类型难以在满足电性能指标要求的同时兼具天线小型化和轻量化的设计特征，从而影响了VHF链路在微小卫星和微纳卫星上的高效应用。As we all know, the radiation efficiency and performance of the antenna are directly related to the physical aperture of the antenna. When the physical aperture of the antenna is significantly reduced, the performance of the antenna will deteriorate sharply at the same operating frequency, and it will even be difficult to meet the normal use requirements and cannot effectively receive and radiate electromagnetic waves. Due to the limitation of the frequency band used by VHF, the operating wavelength of VHF antenna exceeds 2m, so it is difficult for conventional antenna types to meet the requirements of electrical performance indicators while having the design features of antenna miniaturization and light weight, which affects the use of VHF links in micro-satellites and micro-satellites. Efficient applications on nanosatellites.
本发明是考虑上述问题而完成的，其目的在于提供一种能在满足现有天线主要电性能指标要求的同时，兼具小型化、轻量化、对各类卫星(尤其是微小卫星、微纳卫星)适应性高的星载VHF天线装置，从而解决VHF天线在微小卫星、微纳卫星设计应用上的瓶颈，同时起到节省整星资源，降低成本。The present invention is completed in consideration of the above problems, and its purpose is to provide an antenna that can meet the main electrical performance index requirements of existing antennas while being miniaturized, lightweight, and suitable for various types of satellites (especially microsatellites, micro-nano antennas, etc.) Satellite) highly adaptable space-borne VHF antenna device, thereby solving the bottleneck of VHF antenna design and application in micro-satellites and micro-nano-satellites, and at the same time saving the entire star resources and reducing costs.
解决技术问题所采用的技术方案Technical solutions adopted to solve technical problems
发明人为了解决上述问题而进行了潜心研究，通过在结构设计上采用全金属结构，并在常规微带设计基础上增加中心短路墙结构及末端多片式加载技术，从而能获得一种辐射性能强的小型线极化VHF天线装置。然后，在线极化VHF天线装置的基础上，根据正交旋转馈电设计组阵技术，实现高性能高纯度的圆极化辐射模式重构及辐射性能增强设计。In order to solve the above-mentioned problems, the inventor has conducted a painstaking research. By adopting an all-metal structure in the structural design, and adding a central short-circuit wall structure and terminal multi-chip loading technology on the basis of the conventional microstrip design, a radiation performance can be obtained. Strong small linear polarized VHF antenna unit. Then, on the basis of the online polarized VHF antenna device, according to the orthogonal rotating feed design array technology, the high-performance and high-purity circular polarization radiation pattern reconstruction and radiation performance enhancement design are realized.
即，本发明的星载VHF天线装置的特征在于，是平面变形加载IFA的线极化星载VHF天线装置，包括：反射板，馈电单元以及天线辐射单元，That is, the space-borne VHF antenna device of the present invention is characterized in that it is a linearly polarized space-borne VHF antenna device with plane deformation loading IFA, including: reflector, feed unit and antenna radiation unit,
所述天线辐射单元包括：由左侧天线辐射片和上侧天线辐射片构成的平面倒F天线主体部；以及位于所述上侧天线辐射片的右侧末端的多片末端天线辐射片，The antenna radiating unit includes: a plane inverted-F antenna main body composed of a left antenna radiating piece and an upper antenna radiating piece; and a plurality of terminal antenna radiating pieces positioned at the right end of the upper antenna radiating piece,
所述左侧天线辐射片的下端部垂直设置于所述反射板的左侧端部，The lower end of the left antenna radiation piece is vertically arranged on the left end of the reflector,
所述上侧天线辐射片以在X方向上与所述反射板平行的方式延伸，The upper antenna radiation piece extends parallel to the reflector in the X direction,
所述多片末端天线辐射片以彼此平行且在X方向上相互隔开一定间距的方式依次位于所述上侧天线辐射片的右侧末端，The plurality of terminal antenna radiation pieces are sequentially located at the right end of the upper antenna radiation piece in a manner parallel to each other and separated from each other by a certain distance in the X direction,
所述多片末端天线辐射片中的部分末端天线辐射片以垂直于所述上侧天线辐射片的方式连接于所述上侧天线辐射片的右侧端部下表面，且其在Y方向上的长度短于所述左侧天线辐射片的长度，Part of the end antenna radiation pieces in the plurality of terminal antenna radiation pieces are connected to the lower surface of the right side end of the upper side antenna radiation piece in a manner perpendicular to the upper side antenna radiation piece, and its direction in the Y direction length is shorter than the length of the left antenna radiation piece,
所述多片末端天线辐射片中的另一部分末端天线辐射片以垂直于所述反射板的方式连接于所述反射板的右侧端部上表面，且其在Y方向上的长度短于所述左侧天线辐射片的长度，Another part of the end antenna radiation pieces among the plurality of terminal antenna radiation pieces is connected to the upper surface of the right end of the reflection plate in a manner perpendicular to the reflection plate, and its length in the Y direction is shorter than the Describe the length of the left antenna radiator,
所述馈电单元设置在所述反射板与所述天线辐射单元的上侧天线辐射片之间。The feed unit is disposed between the reflection plate and the upper antenna radiation piece of the antenna radiation unit.
发明效果Invention effect
根据本发明，能够实现一种能在满足现有天线主要电性能指标要求的同时，兼具小型化、轻量化、对各类卫星(尤其是微小卫星、微纳卫星))适应性高的星载VHF天线装置。According to the present invention, it is possible to realize a satellite that can meet the main electrical performance index requirements of existing antennas, and has the advantages of miniaturization, light weight, and high adaptability to various satellites (especially micro-satellites and micro-nano satellites). Carrying VHF antenna unit.
附图说明Description of drawings
图1是表示本发明的实施方式1的星载VHF天线装置的关键设计技术的示意图。FIG. 1 is a schematic diagram showing key design techniques of a spaceborne VHF antenna device according to Embodiment 1 of the present invention.
图2是表示本发明的实施方式1的星载VHF天线装置的设计的流程图。2 is a flow chart showing the design of the spaceborne VHF antenna device according to Embodiment 1 of the present invention.
图3是示意性表示本发明的实施方式1的星载VHF天线装置的结构的分解立体图。3 is an exploded perspective view schematically showing the configuration of the spaceborne VHF antenna device according to Embodiment 1 of the present invention.
图4是示意性表示本发明的实施方式2的星载VHF天线装置的结构的图。FIG. 4 is a diagram schematically showing the configuration of a spaceborne VHF antenna device according to Embodiment 2 of the present invention.
图5是表示本发明的实施方式2的星载VHF天线装置的全向性能仿真结果的图。FIG. 5 is a diagram showing the omnidirectional performance simulation results of the spaceborne VHF antenna device according to Embodiment 2 of the present invention.
具体实施方式Detailed ways
以下，基于附图详细说明本发明的实施方式。此外，本发明并不限于以下实施方式。各图中的相同标号表示相同的部分。Hereinafter, embodiments of the present invention will be described in detail based on the drawings. In addition, the present invention is not limited to the following embodiments. The same reference numerals in each figure denote the same parts.
实施方式1Embodiment 1
图1是表示本发明的实施方式的星载VHF天线装置的关键设计技术的示意图。FIG. 1 is a schematic diagram showing key design techniques of a spaceborne VHF antenna device according to an embodiment of the present invention.
如图1所示，星载VHF天线装置的关键设计技术划分为辐射效率保持小型化设计技术、宽波束及全向波束覆盖设计技术、极化重构及性能扩展增强设计技术、谐振窄带化高隔离度设计技术、以及环境适应通用性设计技术等5项关键技术。As shown in Figure 1, the key design technologies of the spaceborne VHF antenna device are divided into miniaturization design technology for maintaining radiation efficiency, wide beam and omnidirectional beam coverage design technology, polarization reconfiguration and performance expansion and enhancement design technology, narrow-band resonant high Five key technologies including isolation design technology and environmental adaptability design technology.
在进行星载VHF天线装置设计时，为了提高星载VHF天线装置的实际可用性，需要尽量减小其与其它射频系统间的耦合传输以提高系统的EMC性能，可以考虑采用减小VHF天线装置的阻抗带宽，实现窄带化的设计，即在谐振工作频带外实现反射抑制，从而减少电磁能量的二次耦合与寄生辐射，提高系统间辐射隔离度，避免高灵敏度测试时不同系统间产生电磁干扰(EMI)效应。When designing the spaceborne VHF antenna device, in order to improve the actual availability of the spaceborne VHF antenna device, it is necessary to minimize the coupling transmission between it and other radio frequency systems to improve the EMC performance of the system, and it is possible to consider reducing the VHF antenna device. Impedance bandwidth, realizing narrow-band design, that is, realizing reflection suppression outside the resonant working frequency band, thereby reducing the secondary coupling of electromagnetic energy and parasitic radiation, improving the radiation isolation between systems, and avoiding electromagnetic interference between different systems during high-sensitivity testing ( EMI) effect.
此外，为了满足星载VHF天线装置对于灵活测试及环境适应性的需求，在天线结构及工程实现方面，着重考虑天线接口通用化设计、天线辐射结构全金属化设计、天线非金属有耗媒质环境适应性设计及天线力学性能设计等方面内容。优选具有航天适应性的成熟金属及非金属材料进行小型化星载VHF天线电性及环境适应性设计，为提高星载VHF天线装置的可用性与通用性提供保障。In addition, in order to meet the needs of space-borne VHF antenna devices for flexible testing and environmental adaptability, in terms of antenna structure and engineering implementation, the general design of the antenna interface, the full-metal design of the antenna radiation structure, and the non-metallic lossy medium environment of the antenna should be considered. Adaptive design and antenna mechanical performance design and other aspects. Mature metal and non-metal materials with aerospace adaptability are selected for miniaturized space-borne VHF antenna electrical and environmental adaptability design, which provides guarantee for improving the usability and versatility of space-borne VHF antenna devices.
图2是示意性表示本发明的实施方式的星载VHF天线装置的设计的流程图。FIG. 2 is a flowchart schematically showing the design of the spaceborne VHF antenna device according to the embodiment of the present invention.
如图2所示，在进行星载VHF天线装置设计时，首先分析VHF天线的具体要求。该步骤可以通过整理具体要求并分解关键技术来进行。As shown in Figure 2, when designing a spaceborne VHF antenna device, first analyze the specific requirements of the VHF antenna. This step can be done by collating specific requirements and breaking down key technologies.
接着，进行VHF天线装置的选型设计。该步骤可以通过高增益定向波束方案、低剖面宽波束方案、高性能宽波束CP方案、小型化全向方案来实现。Next, carry on the type selection design of the VHF antenna device. This step can be realized through a high-gain directional beam scheme, a low-profile wide-beam scheme, a high-performance wide-beam CP scheme, and a miniaturized omnidirectional scheme.
然后，对该阶段的VHF天线装置的性能，例如增益、波束宽度、VSWR、极化特性、尺寸、重量等性能是否满足要求进行检测，该检测可以利用理论计算、数学仿真计算、全波数值仿真计算来进行。在检测结果为符合性能要求的情况下，进行下一步的VHF天线装置结构设计，在检测结果为不符合性能要求的情况下，返回上一步来重新进行天线选型设计。Then, the performance of the VHF antenna device at this stage, such as gain, beam width, VSWR, polarization characteristics, size, weight and other performances, is tested to meet the requirements. The detection can use theoretical calculations, mathematical simulation calculations, and full-wave numerical simulations. calculation to proceed. If the test result meets the performance requirements, proceed to the next step of structural design of the VHF antenna device; if the test result does not meet the performance requirements, return to the previous step to re-select the antenna design.
在VHF天线装置结构设计步骤中，进行理想辐射结构工程化、理想馈电结构工程化。In the structural design step of the VHF antenna device, the engineering of the ideal radiation structure and the engineering of the ideal feeding structure are carried out.
之后，进行VHF天线装置的加工，主要针对辐射体、支撑体、馈电结构、集成连接结构、调谐结构、加载结构等进行加工。After that, the processing of the VHF antenna device is carried out, mainly for the radiator, the support body, the feeding structure, the integrated connection structure, the tuning structure, the loading structure and so on.
接下来，进行VHF天线装置的装配，主要是进行辐射体装配、加载结构装配、馈电结构装配、以及支承及集成连接机构装配。Next, the assembly of the VHF antenna device is carried out, mainly including the assembly of the radiator, the assembly of the loading structure, the assembly of the feeding structure, and the assembly of the supporting and integrated connection mechanism.
最后，进行天线性能调试，例如针对增益、波束宽度、VSWR、极化特性、尺寸、重量等进行调试，在调试结果不达标时，返回至上一步来重新进行天线装配，在调试结果达标时，获得最终的天线装置产品。Finally, perform antenna performance debugging, such as debugging for gain, beam width, VSWR, polarization characteristics, size, weight, etc. If the debugging results do not meet the standards, return to the previous step to reassemble the antenna. When the debugging results meet the standards, get The final antenna assembly product.
星载VHF天线装置从结构上可以分为三大部分：小型化高效辐射结构、馈电及阻抗变换匹配结构和机械接口匹配安装结构。The structure of the spaceborne VHF antenna device can be divided into three parts: a miniaturized and efficient radiation structure, a feeding and impedance transformation matching structure, and a mechanical interface matching installation structure.
具体而言，小型化高效辐射结构会形成主面宽波束或全向波束辐射特性，因而能通过采用最优拓扑设计来实现包络小型化设计的同时保持了较高的辐射效率。Specifically, the miniaturized high-efficiency radiation structure will form the main surface wide beam or omnidirectional beam radiation characteristics, so the optimal topology design can be used to realize the envelope miniaturization design while maintaining high radiation efficiency.
能利用一体化馈电及阻抗匹配结构能实现天线端输入阻抗馈线端特性阻抗的最佳匹配，从而实现天线端最大功率馈送，并进一步提高天线实现增益，同时实现谐振窄带化设计，提高射频RF系统间隔离度，增强EMC性能。The integrated feed and impedance matching structure can be used to achieve the best matching of the input impedance of the antenna end and the characteristic impedance of the feed line end, so as to realize the maximum power feeding of the antenna end, and further improve the gain of the antenna. Inter-system isolation, enhanced EMC performance.
通过集成转接机械接口板，能够实现星载VHF天线装置对天线样机力学性能和安装接口匹配化的特定要求。By integrating the transfer mechanical interface board, the specific requirements of the spaceborne VHF antenna device for the mechanical performance of the antenna prototype and the matching of the installation interface can be realized.
图3是示意性表示本发明的实施方式1的星载VHF天线装置1的结构的分解立体图。FIG. 3 is an exploded perspective view schematically showing the configuration of the spaceborne VHF antenna device 1 according to Embodiment 1 of the present invention.
星载VHF天线装置1是例如线极化天线装置，即LP模式天线装置，其采用全金属平面变形加载IFA方案。如图3所示，星载VHF天线装置1包括：反射板101，馈电单元102以及天线辐射单元103。The spaceborne VHF antenna device 1 is, for example, a linearly polarized antenna device, that is, an LP mode antenna device, which adopts an all-metal planar deformation loading IFA scheme. As shown in FIG. 3 , the spaceborne VHF antenna device 1 includes: a reflector 101 , a feeding unit 102 and an antenna radiation unit 103 .
其中，反射板101采用例如铝等金属材料。馈电单元102配置在反射板101和天线辐射单元103的上侧天线辐射片103b之间，例如采用铍青铜等金属材料。Wherein, the reflection plate 101 is made of metal materials such as aluminum. The feeding unit 102 is disposed between the reflector 101 and the upper antenna radiation piece 103b of the antenna radiation unit 103, and is made of metal materials such as beryllium copper, for example.
天线辐射单元103采用平面变形加载IFA结构，其包括：构成平面倒F天线主体部的左侧天线辐射片103a和上侧天线辐射片103b；以及位于天线辐射片103b右侧末端的多片末端天线辐射片103c～103f。The antenna radiating unit 103 adopts a plane deformation loading IFA structure, which includes: the left antenna radiation piece 103a and the upper side antenna radiation piece 103b constituting the main body of the plane inverted F antenna; and a multi-piece terminal antenna located at the right end of the antenna radiation piece 103b Radiation sheets 103c-103f.
左侧天线辐射片103a的下表面垂直连接于反射板101的左侧端部，上侧天线辐射片103b以与反射板101平行的方式沿X方向延伸。4片末端天线辐射片103c～103f依次配置为彼此平行且在X方向上相互隔开一定间距。其中，末端天线辐射片103c和末端天线辐射片103e以垂直于上侧天线辐射片103b的方式连接于上侧天线辐射片103b的右侧端部下表面，且其在Y方向上的长度短于左侧天线辐射片103a在Y方向上的长度。末端天线辐射片103d和末端天线辐射片103f以垂直于反射板101的方式连接于反射板101的右侧端部上表面，且其在Y方向上的长度短于左侧天线辐射片103a在Y方向上的长度。换言之，末端天线辐射片103d和末端天线辐射片103f不与上侧天线辐射片103b的下表面相连接。The lower surface of the left antenna radiation piece 103 a is vertically connected to the left end of the reflector 101 , and the upper antenna radiation piece 103 b extends parallel to the reflector 101 in the X direction. The four end antenna radiation pieces 103c to 103f are sequentially arranged parallel to each other and spaced apart from each other by a certain distance in the X direction. Wherein, the terminal antenna radiation piece 103c and the terminal antenna radiation piece 103e are connected to the lower surface of the right end of the upper side antenna radiation piece 103b in a manner perpendicular to the upper side antenna radiation piece 103b, and their length in the Y direction is shorter than that of the left side. The length of the side antenna radiation piece 103a in the Y direction. The end antenna radiation piece 103d and the end antenna radiation piece 103f are connected to the upper surface of the right end of the reflection plate 101 in a manner perpendicular to the reflection plate 101, and their length in the Y direction is shorter than that of the left antenna radiation piece 103a in the Y direction. length in the direction. In other words, the end antenna radiation piece 103d and the end antenna radiation piece 103f are not connected to the lower surface of the upper side antenna radiation piece 103b.
通过设置多片末端天线辐射片，增加了星载VHF天线装置的电容，从而使天线容抗降低，由此在天线匹配阻抗不变的情况下，减小星载VHF天线装置的尺寸。By arranging multiple end antenna radiation pieces, the capacitance of the spaceborne VHF antenna device is increased, thereby reducing the capacitive reactance of the antenna, thereby reducing the size of the spaceborne VHF antenna device under the condition that the matching impedance of the antenna remains unchanged.
此处以4片末端天线辐射片103c～103f为例进行说明，但并不限于此。此外，此处以多片末端天线辐射片在Z方向上的宽度与上侧天线辐射片103b在Z方向上的宽度相一致为例进行了说明，但并不限于此。Here, four end antenna radiation pieces 103c-103f are taken as an example for illustration, but it is not limited thereto. In addition, it is described here that the width of the plurality of end antenna radiation pieces in the Z direction is consistent with the width of the upper antenna radiation piece 103b in the Z direction, but it is not limited thereto.
通过采用上述结构，星载VHF天线装置1的外形包络尺寸仅为0.08波长，高度为0.053波长，与常规单极子天线相比，其纵向尺寸缩减为单极子天线高度的16％，实现了很好的低剖面设计，容易实现与卫星卫星平台的共形布局应用，满足受限空间下的小型化低剖面设计和便携测试需求。By adopting the above-mentioned structure, the space-borne VHF antenna device 1 has an envelope size of only 0.08 wavelength and a height of 0.053 wavelength. Compared with the conventional monopole antenna, its longitudinal dimension is reduced to 16% of the height of the monopole antenna, realizing It has a very good low-profile design, and it is easy to realize the conformal layout application with the satellite satellite platform, and meet the needs of miniaturized low-profile design and portable testing in limited space.
此外，通过采用上述结构，天线辐射线极化波在自由空间条件下增益约为1.4dB。当采用金属PEC反射板模拟实现定向辐射时，经全波仿真分析，天线增益约为2dB，3dB波束宽度约为110°。由此，能够实现在减小星载VHF天线装置尺寸的同时，增强其电学性能。In addition, by adopting the above structure, the antenna radiates linearly polarized waves with a gain of about 1.4dB under free space conditions. When the metal PEC reflector is used to simulate directional radiation, the antenna gain is about 2dB and the 3dB beamwidth is about 110° through full-wave simulation analysis. Therefore, it is possible to reduce the size of the spaceborne VHF antenna device while enhancing its electrical performance.
根据实施方式1，通过采用全金属金属结构来去除微带基板对星载VHF天线装置的性能及环境适应性的约束，并在常规微带设计基础上增加中心短路墙结构及末端多片式加载技术，从而大幅缩减星载VHF天线装置的包络尺寸。由此，能在满足现有天线主要电性能指标要求的同时，兼具小型化、轻量化、对各类卫星(尤其是微小卫星、微纳卫星))适应性高等要求。According to Embodiment 1, the constraints of the microstrip substrate on the performance and environmental adaptability of the spaceborne VHF antenna device are removed by adopting an all-metal structure, and the central short-circuit wall structure and terminal multi-chip loading are added on the basis of the conventional microstrip design technology, thereby greatly reducing the envelope size of the spaceborne VHF antenna device. Therefore, while meeting the main electrical performance index requirements of existing antennas, it can meet the requirements of miniaturization, light weight, and high adaptability to various satellites (especially micro-satellites and micro-nano satellites).
实施方式2Embodiment 2
在上述实施方式1中，举例示出了构成为线极化天线装置的星载VHF天线装置1，在本实施方式2中，说明在线极化天线装置的基础上，对其进行组阵，从而构成圆极化(CP)模式天线装置，以进一步提高天线电性能。In Embodiment 1 above, the space-borne VHF antenna device 1 configured as a linearly polarized antenna device was shown as an example. In Embodiment 2, on the basis of describing the linearly polarized antenna device, it is formed into an array, so that A circular polarization (CP) mode antenna device is formed to further improve the electrical performance of the antenna.
如图3所示，本发明的实施方式2的星载VHF天线装置2即圆极化星载VHF天线装置2通过对4个上述星载VHF天线装置1进行组阵而构成。具体而言，在反射板201上沿着X和Y方向进行等间距布阵，将4个实施方式1中的星载VHF天线装置1依次旋转90°进行配置，从而构成4元低剖面、轻量化平面阵列。该阵列外形包络尺寸为370mm×370mm。此处，以对4个线极化天线装置进行组阵来构成圆极化天线装置为例进行了说明，但并不限于此。As shown in FIG. 3 , the circularly polarized space-borne VHF antenna device 2 , which is the space-borne VHF antenna device 2 according to the second embodiment of the present invention, is constituted by arraying four above-mentioned space-borne VHF antenna devices 1 . Specifically, arrays are arranged at equal intervals along the X and Y directions on the reflector 201, and the four spaceborne VHF antenna devices 1 in Embodiment 1 are sequentially rotated by 90° to form a quaternary low-profile, lightweight Quantize a planar array. The envelope size of the array is 370mm×370mm. Here, an example in which four linearly polarized antenna devices are arrayed to form a circularly polarized antenna device has been described, but the present invention is not limited thereto.
此外，通过改变各个线极化(LP)模式天线装置的馈电相位关系可以实现右旋圆极化(RHCP)和左旋圆极化(LHCP)来切换工作模式，满足星载VHF天线对不同极化的应用需求。In addition, right-handed circular polarization (RHCP) and left-handed circular polarization (LHCP) can be switched by changing the feed phase relationship of each linearly polarized (LP) mode antenna device to meet the needs of spaceborne VHF antennas for different poles. customized application requirements.
图5是表示本发明的实施方式2的星载VHF天线装置2的全向性能仿真结果的图。FIG. 5 is a diagram showing the omnidirectional performance simulation results of the spaceborne VHF antenna device 2 according to Embodiment 2 of the present invention.
如图5所示，在阵列前向方向，星载VHF天线装置2辐射左旋圆极化(LHCP)波，天线增益约为3.3dB；在后向方向，星载VHF天线装置2辐射右旋圆极化(RHCP)波，增益约为-4dB，由此实现了全向覆盖能力。As shown in Figure 5, in the forward direction of the array, the spaceborne VHF antenna device 2 radiates left-handed circularly polarized (LHCP) waves, and the antenna gain is about 3.3dB; in the backward direction, the spaceborne VHF antenna device 2 radiates right-handed circular polarization Polarized (RHCP) waves, the gain is about -4dB, thereby achieving omnidirectional coverage.
根据本实施方式2，对多个上述星载VHF天线装置1进行组阵，即对线极化星载VHF天线装置应用正交旋转和差分馈电组阵技术，能够获得圆极化星载VHF天线装置，并能实现天线辐射性能增强，并实现波束扫描性能，还能够实现阵列方向图全向覆盖。According to Embodiment 2, a plurality of above-mentioned spaceborne VHF antenna devices 1 are arrayed, that is, the orthogonal rotation and differential feed array technology is applied to linearly polarized spaceborne VHF antenna devices, and circularly polarized spaceborne VHF antennas can be obtained. The antenna device can enhance the radiation performance of the antenna, realize the beam scanning performance, and realize the omnidirectional coverage of the array pattern.
如上所述，根据本发明，通过采用全金属结构来去除微带基板对星载VHF天线装置的性能及环境适应性的约束，并在常规微带设计基础上增加中心短路墙结构及末端多片式加载技术，从而大幅缩减星载VHF天线装置的包络尺寸，并且通过底板缩减及参与辐射一体化设计技术实现星载VHF天线主面方向全向辐射成形。由此，能使得星载VHF天线装置在满足现有天线主要电性能指标要求的同时，兼具小型化、轻量化、对各类卫星(尤其是微小卫星、微纳卫星)适应性高等要求。As mentioned above, according to the present invention, the restriction of the microstrip substrate on the performance and environmental adaptability of the spaceborne VHF antenna device is removed by adopting an all-metal structure, and the center short-circuit wall structure and the terminal multi-chip are added on the basis of the conventional microstrip design Type loading technology, thereby greatly reducing the envelope size of the spaceborne VHF antenna device, and realizing omnidirectional radiation shaping in the direction of the main surface of the spaceborne VHF antenna through the reduction of the base plate and the integrated design technology of participating in the radiation. As a result, the spaceborne VHF antenna device can meet the requirements of the main electrical performance indicators of existing antennas, and at the same time meet the requirements of miniaturization, light weight, and high adaptability to various satellites (especially micro-satellites and micro-nano satellites).
以上对本发明的实施方式进行了说明，实施方式仅作为示例示出，并不限定发明范围。另外，实施方式能以各种形式进行实施，在不脱离发明主旨的范围内，能进行各种省略，置换，变更。实施方式都包含于发明的范围及其主旨内，同样地包含在权利要求保护范围所记载的发明及其等效范围内。As mentioned above, although embodiment of this invention was described, embodiment is shown only as an example, and does not limit the scope of invention. In addition, the embodiments can be implemented in various forms, and various omissions, substitutions, and changes can be made without departing from the spirit of the invention. Embodiments are included in the scope and gist of the invention, and are also included in the invention described in the claims and their equivalents.
工业上的实用性Industrial Applicability
本发明涉及的星载VHF天线装置能在满足现有天线主要电性能指标要求的同时，兼具小型化、轻量化、对各类卫星(尤其是微小卫星、微纳卫星))适应性高等优点，可以广泛应用于航空、航天等领域，但不限于该领域。The space-borne VHF antenna device involved in the present invention can meet the main electrical performance index requirements of existing antennas, and at the same time have the advantages of miniaturization, light weight, and high adaptability to various satellites (especially micro-satellites, micro-nano-satellites), etc. , can be widely used in aviation, aerospace and other fields, but not limited to this field.
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