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![The illustration of the compact circular polarized crossed dipole antenna with high impedance surface (HIS) on the back of the antenna [48].](publication/316603828/figure/fig5/AS:1086507226005504@1636054917035/The-illustration-of-the-compact-circular-polarized-crossed-dipole-antenna-with-high.jpg)
The illustration of the compact circular polarized crossed dipole antenna with high impedance surface (HIS) on the back of the antenna [48].
Source publication
![A CubeSat with Ka-band reflector antenna for deep space mission [37].](publication/316603828/figure/fig1/AS:1086507221819392@1636054916867/A-CubeSat-with-Ka-band-reflector-antenna-for-deep-space-mission-37_Q320.jpg)
![CP antenna with phase shifter. (a) Front view and (b) rear view [39].](publication/316603828/figure/fig2/AS:1086507221823490@1636054916941/CP-antenna-with-phase-shifter-a-Front-view-and-b-rear-view-39_Q320.jpg)
![CP antenna with phase shifter. (a) Front view and (b) rear view [39].](publication/316603828/figure/fig3/AS:1086507221819395@1636054916969/CP-antenna-with-phase-shifter-a-Front-view-and-b-rear-view-39_Q320.jpg)
![Compact antenna with symmetrical slit [46].](publication/316603828/figure/fig4/AS:1086507221819402@1636054916998/Compact-antenna-with-symmetrical-slit-46_Q320.jpg)
Cube Satellite (CubeSat) technology is an attractive emerging alternative to conventional satellites in radio astronomy, earth observation, weather forecasting, space research, and communications. Its size, however, poses a more challenging restriction on the circuitry and components as they are expected to be closely spaced and very power efficien...
Citations
... The performance and reliability of on-board computer systems in picosatellites, especially significant during data processing in the descent phase, are highlighted in recent analyses [7]. The impact of payload diversity on the design considerations for picosatellites' descent phases is also a topic of current research [8]. ...
In this research, we evaluate the effectiveness of two Pico satellite designs - a can-satellite model and a cubesatellite model - focusing on their performance during controlled parachute descents from a specific altitude. The study centers on embedded sensors in these satellites, which collect environmental and kinematic data throughout the descent. These sensors track temperature, humidity, barometric pressure, gyroscope readings, acceleration, and magnetometer data, offering detailed insights into each design’s descent dynamics. The primary goal is to assess how the can and cubePico satellites withstand descent pressures and their data gathering efficacy during parachute-assisted landings. This evaluation is crucial for understanding how different sensor integration impact the performance and adaptability of picosatellites in freefall conditions. Additionally, the research includes a comparative analysis of two communication devices: the cube satellite equipped with an NRF24L01+LNA, and the can satellite with an ESP32S wireless development board. This comparison aims to identify which communication technology is more suitable for the challenging environment of parachute-assisted descent, with a focus on the reliability and quality of data transmission.
... One factor that has contributed to this trend is that technology has allowed satellites to become increasingly lighter and, therefore, less expensive to launch. An example of how satellites have become lighter is the advent of the CubeSat, which first launched in 2003 and has since become a standard platform for simple space missions [2][3][4][5]. CubeSats, along with other "PicoSats", rely on antennas to establish radio transmission, as well as solar panels to power the satellite [6]. Because the performance of antennas and solar panels is directly related to their surface area, engineers have turned to various methods, including origami, to increase their ratio of deployed surface area to stowed volume [3,7]. ...
... With the advancement of technology, nanosatellite has drawn remarkable contemplation from space researchers due to the feasibility of payload missions within a few cubic centimeter's size satellite structure and minimal expense. Nowadays, this type of small satellite is widely used in various sectors, like astronomy, astrobiology, earth observation, atmospheric science, ecology, meteorology, telecommunications, disasters mitigation and management, education, and training [1][2][3][4]. Smooth data communication is very crucial for nanosatellite missions, where the antenna plays a key role in establishing communication between the satellite and the earth. The nanosatellite antenna design becomes complex to antenna researchers due to the inverse proportionality relation between antenna performance and size [5][6][7]. ...
The concept of nanosatellite technology becomes a viable platform for earth and space observation research to minimize cost and build time for the payload. The communication approach is the essential fundamental attribute of a satellite, of which the antenna is a crucial component for forming a communication link between the nanosatellite and the earth. The nanosatellite antenna must comply with some special requirements like compact size, lightweight, and high gain with a space-compatible structure. This paper proposes a compact metamaterial-based Ku-band antenna with circular polarization for the nanosatellite communication system. The designed antenna obtained an impedance bandwidth of 2.275 GHz with a realized gain of 6.74 dBi and 3 dB axial beamwidth of 165° at 12.10 GHz. The overall antenna size of the designed is 0.51λ × 0.51λ × 0.17λ, which is fabricated on Rogers 5880 substrate material. The antenna results performance has been examined with a 1 U nanosatellite structure and found suitable to integrate with metallic and nonmetallic surfaces of any miniature nanosatellite structure.
... Efficient antenna designing is one of the major research areas for small satellites. These small satellites require lightweight small size antennas [5]- [9]. Small satellites operate at various frequencies depending on the applications. ...
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Future small satellites require the development of reconfigurable antennas. Designing such antennas, especially single port patch antennas with circular polarization (CP) is a challenging task. Therefore, we propose both right-hand/left- hand circularly polarized (RHCP/LHCP) antenna which can reconfigure. The proposed antenna follows patch topology with E-shape that is single-layer and single-feed with two RF switches. The switches can alter the polarization in real-time. We also show various properties of the proposed antenna, such as radiation pattern, impedance matching, axial ratio, and bandwidth through simulations and measurements. The proposed model shows excellent performance and agrees well with the measurements. The performance of the antenna shows an effective bandwidth of 2.45 GHz to 2.82 GHz with a maximum gain of 9.88 dB at 2.55 GHz. The symmetry of the antenna radiation is preserved by switching between the LHCP and RHCP polarization modes.
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... Efficient antenna designing is one of the major research areas for small satellites. These small satellites require lightweight small size antennas [5]- [9]. Small satellites operate at various frequencies depending on the applications. ...
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Future small satellites require the development of reconfigurable antennas. Designing such antennas, especially single port patch antennas with circular polarization (CP) is a challenging task. Therefore, we propose both right-hand/left- hand circularly polarized (RHCP/LHCP) antenna which can reconfigure. The proposed antenna follows patch topology with E-shape that is single-layer and single-feed with two RF switches. The switches can alter the polarization in real-time. We also show various properties of the proposed antenna, such as radiation pattern, impedance matching, axial ratio, and bandwidth through simulations and measurements. The proposed model shows excellent performance and agrees well with the measurements. The performance of the antenna shows an effective bandwidth of 2.45 GHz to 2.82 GHz with a maximum gain of 9.88 dB at 2.55 GHz. The symmetry of the antenna radiation is preserved by switching between the LHCP and RHCP polarization modes.
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... In particular, CubeSats have attracted much attention from both the commercial and academic sectors [1]. This has motivated the recent development of numerous deployable antennas for small-satellite applications [1,3,4]. ...
Trends in the aerospace industry are driving payloads to be smaller and less expensive while yet delivering comparatively large antennas. Deployable reflectarray antennas are often used to meet these demands. The more that a deployable reflectarray fills an allotted volume in the stowed state, the greater the surface area it will realize in the deployed state. Thick, flat-foldable origami designs are therefore excellent design candidates for reflectarray antennas, as they stow as efficiently as possible. This is desirable for antennas as surface area is directly proportional to gain. Gain is also affected by efficiency, which is a function of the geometry of the antenna aperture. As the most efficient rectangular reflectarray profile is a square, this work develops the metrics and relationships that enable an optimization problem seeking to maximize surface area subject to the constraints of an allotted cuboid volume and a deployed aspect ratio of one. The source origami is a modified thickness-accommodating Miura-ori pattern herein termed volume-efficient Miura-ori (VEMO), selected for its ability to fold into a rectangular profile and easily adapt to different aspect ratios. A case study is presented with an allotted 1U CubeSat volume and a panel thickness of 2.5 mm.
... CubeSats are economical and easy to manufacture as compared to the traditional satellites systems [1]. It has numerous advantage and has many applications in industry as well as in academia [2]. ...
... Most of the CubeSats use Radioamateur frequency band for the main communication [8], but licensed bands are now often used due to the commercial nature of some missions. Due to the reduced launch costs and the inspiring increase in complex applications, this platform started to attract many commercial, military, and governmental organizations [6,9]. These applications increased the need for larger transfer rates. ...
There is a great potential in small satellite technology for testing new sensors, processes, and technologies for space applications. Antennas need careful design when developing a small satellite to establish stable communication between the ground station and the satellite. This work is motivated by the design of an antenna array for a future rotatorless base station for the VZLUSAT group of Czech nano-satellites. The realized antenna array must cover a relatively broad range of elevation and azimuth angles, and the control must be fast enough to track the satellite in low Earth orbits. The paper deals with possibilities of synthesis of quantized control of the antenna array. It compares quantization influence for well-known deterministic synthesis methods. It shows the method for decreasing computational cost of synthesis using optimization approach and presents the multi-criteria optimization as a tool for reaching required radiation pattern shape and low sensitivity to quantization at the same time.
... In [44], various types and applications of antennas for picosatellites are presented. Design challenges of such antennas are considered together with possible innovative methods used to solve the space and power limitations in these compact satellites. ...
The rapid development of wireless technology has sparked interest in multi-band reconfigurable antennas as devices and satellites are innovating toward miniaturization. With limited space, reliable and efficient high bandwidth antenna systems are needed for current and next-generation wireless technology as well as for the revolutionary small satellites. The fifth generation of mobile communication technology promises high data rates, low latency and good spectrum efficiency. One of the key enablers of this technology is the integration of satellite technology-particularly CubeSats with terrestrial communication technologies. Next-generation antennas that can meet functional requirements for 5G and CubeSat applications are therefore of fundamental importance. These antenna systems should have large bandwidth, high gain and efficiency and be compact in size. Reconfigurable antennas can provide different configurations in terms of the operating frequency, radiation pattern and polarization. Tuning reconfigurable antennas can be done by changing the physical parameters of the antenna elements through electronic switches, optical switches and the use of meta-materials. The most popular implementation method for reconfigurable antennas for wireless and satellite communication is the electronic switching method due to its high reliability, efficiency, and ease of integration with microwave circuitry. In this article, different techniques for implementing reconfigurable and multi-band antennas are reviewed, with emphasis on two main application areas; 5G wireless communication and CubeSat application. Different reconfiguration techniques have been studied for application in various wireless communication systems such as satellite communication, multiple-input multiple-output (MIMO) systems, cognitive radio and 5G communication. It has been found that reconfigurable antennas have favourable properties for next-generation wireless technology and small satellites. These properties include low cost, less volume requirements and good isolation between wireless standards.
... They include reflector and reflectarray antennas, horn antennas, and planar antennas. The major challenge of high gain antenna design is stowage restrictions due to highly constrained volume; given the size available in Cubesats, several deployment mechanisms for larger antennas have been investigated in the literature for each antenna type [1][2][3][4][5][6][7][8]. Table II enumerates their pros and cons. ...
Antenna systems play a critical role in establishing wireless communication links and sustaining remote sensing requirements for Cubesat applications. In addition to the usual antenna design requirements, Cubesat-based spacecrafts impose additional stringent constraints related to the on-board available space, power consumption and development costs. To develop optimal antenna prototypes while considering all these constraints and decrease trial and error related costs, computational electromagnetics (CEM) simulation tools are used. The accuracy of simulation results depends to a great extent on the choice of the appropriate CEM tool for the particular antenna problem to be analyzed; ergo, identifying and answering key questions about design objectives and requirements is necessary for informed decision-making throughout the selection and design processes. However, this could be quite challenging because of existing gaps both in the practitioners' knowledge about different CEM tools capabilities, limitations, and design know-how. This is especially true for non-specialists such as students and academics involved in student driven Cubesat projects. Therefore, the rationale of this manuscript is to bridge those gaps and clarify some common misconception commonly encountered during the selection and design processes. In that regard, first, an overview of existing antenna configurations commonly used in Cubesat communications is provided. Next, antenna design general workflow is presented. Then, capabilities and limitations of different CEM solving methods are presented. After that, CEM software selection process trade-offs and possible sources of errors are discussed from a practical viewpoint. Finally, a case study of Masat-1 antenna system design is presented as practical example.
