# Cubesat

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# 107 resources related to Cubesat

### IEEE Organizations related to Cubesat

No organizations are currently tagged "Cubesat"

### Conferences related to Cubesat

2020 IEEE International Symposium on Antennas and Propagation and North American Radio Science Meeting

The joint meeting is intended to provide an international forum for the exchange of information on state of the art research in the area of antennas and propagation, electromagnetic engineering and radio science

IGARSS 2020 - 2020 IEEE International Geoscience and Remote Sensing Symposium

All fields of satellite, airborne and ground remote sensing.

2019 13th European Conference on Antennas and Propagation (EuCAP)

The conference provides an overview of the state of the art developments and innovations in Antennas, Propagation, and Measurements, highlighting the latest requirements for future applications.

The main conference scope is latest development in the area of electronics, signal processingand applications, information technologies and systems, computer modeling, and relateddisciplines.

2019 9th International Conference on Recent Advances in Space Technologies (RAST)

RAST 2019 aims providing a forum for the presentation and reviw of recentdevelopments in the space technologies, especially in the Space for the Sustainable Development Goals.

### Periodicals related to Cubesat

No periodicals are currently tagged "Cubesat"

### Xplore Articles related to Cubesat

2019 IEEE Aerospace Conference, 2019

We are developing an inter-satellite omnidirectional optical communicator (ISOC) that will enable cross-link communications between spacecraft at Gbps data rates over distances of up to thousands of kilometers in free space. The ISOC will allow superfast cross-links and will be a technology enabler for swarms and formation flying spacecraft. The ISOC under development features a truncated dodecahedron geometry that can ...

2018 Asia-Pacific Microwave Conference (APMC), 2018

A low-profile, broadband, circularly polarized (CP) antenna integrated with solar cells is proposed for use in CubeSats. The antenna is a single-feed printed crossed-dipole radiator on a metasurface reflector that consists of a lattice of square solar cells mounted on a grounded dielectric substrate. The radiator is designed to allow 100% insolation of the solar cells when directly facing a ...

2018 IEEE International Symposium on Antennas and Propagation & USNC/URSI National Radio Science Meeting, 2018

The aim of this contribution is showing how electromagnetic cloaking may be used to enhance the performances of the telecommunication systems in miniaturized satellites. In particular, with the aid of some relevant examples, it is shown that mantle cloaking allows minimizing the impact of the passive structures of the satellite itself on the antennas performances. Our findings enable the design ...

2019 13th European Conference on Antennas and Propagation (EuCAP), 2019

CNES started developments on miniaturized antennas for small platforms in 2010s (spectrum survey, MASCOT lander). More recently, compact and wideband antennas for TT&C; were designed, manufactured and tested for cubesats needs. Over the last two years, besides the development of Angels nanosatellite, a demonstrator of Argos miniaturized technologies, CNES has supported several activities on this topic. Resulting antenna designs and ...

2019 5th Conference on Knowledge Based Engineering and Innovation (KBEI), 2019

A novel broadband reflectarray (RA) antenna for 3U CubeSat applications is investigated. A novel frequency selective surface (FSS) in the RA as ground plane for reducing radar cross section (RCS) and signals interference with other communication systems working in other frequency bands is applied. The RA divided to three panels and folded on the sides of the CubeSat to reduce ...

### Educational Resources on Cubesat

#### IEEE-USA E-Books

• We are developing an inter-satellite omnidirectional optical communicator (ISOC) that will enable cross-link communications between spacecraft at Gbps data rates over distances of up to thousands of kilometers in free space. The ISOC will allow superfast cross-links and will be a technology enabler for swarms and formation flying spacecraft. The ISOC under development features a truncated dodecahedron geometry that can hold an array of fast photodiode detectors and gimbal-less MEMS scanning mirrors. The main goals of the ISOC development include: 1) full sky coverage, 2) Gbps data rates and 3) the ability to maintain multiple simultaneous links. We have developed two omnidirectional communicator prototypes capable of full-duplex operation. We are using advanced single-mode laser diodes operating at 850 nm capable of producing hundreds of milliwatts of laser radiation. We are also employing MEMS-based beam steering mirrors, and fast PIN photodiodes to achieve long- range communications. The ultimate goal of the project is to achieve full duplex operation at 1 Gbps data rates over 200 km and slightly lower data rates at longer distances. In this paper we describe the overall ISOC architecture and present the design tradeoffs for gigabit data-rate operation. We also present preliminary NRZ On-Off Keying communications simulation results obtained using our optical link budget model. The ISOC is ideally suited for crosslink communications among small spacecraft, especially for those forming a swarm and/or a constellation. Small spacecraft furnished with ISOC communications systems, should be able to communicate at gigabit per second rates over long distances. This data rate enhancement can allow real- time, global science measurements and/or ultra-high fidelity observations from tens or hundreds of Earth-orbiting satellites, or permit high-bandwidth, direct-to-earth communications for planetary missions.

• A low-profile, broadband, circularly polarized (CP) antenna integrated with solar cells is proposed for use in CubeSats. The antenna is a single-feed printed crossed-dipole radiator on a metasurface reflector that consists of a lattice of square solar cells mounted on a grounded dielectric substrate. The radiator is designed to allow 100% insolation of the solar cells when directly facing a light source. The metasurface is used as an artificial reflector of the crossed dipole to achieve a lowprofile as well as broadband characteristics. The low-profile design could also minimize shadowing of the solar cells for oblique angle insolation. The final prototype with an overall size of 100 mm × 100 mm × 5.9 mm (0.75λo × 0.75λo × 0.044λo at 2.25 GHz) yields a |S11| <; -10 dB bandwidth of 2.02-2.58 GHz and a 3dB axial ratio bandwidth of 2.12-2.44 GHz. The antenna radiated a good broadside right-hand CP wave with a high broadside gain and high radiation efficiency within the operational bandwidth.

• The aim of this contribution is showing how electromagnetic cloaking may be used to enhance the performances of the telecommunication systems in miniaturized satellites. In particular, with the aid of some relevant examples, it is shown that mantle cloaking allows minimizing the impact of the passive structures of the satellite itself on the antennas performances. Our findings enable the design of nanosatellite systems equipped with multi quasi- isotropic and multi-band antennas.

• CNES started developments on miniaturized antennas for small platforms in 2010s (spectrum survey, MASCOT lander). More recently, compact and wideband antennas for TT&C; were designed, manufactured and tested for cubesats needs. Over the last two years, besides the development of Angels nanosatellite, a demonstrator of Argos miniaturized technologies, CNES has supported several activities on this topic. Resulting antenna designs and performances are briefly presented in this paper. Finally, new challenges and perspectives for cubesats antennas, as envisioned by CNES, are discussed.

• A novel broadband reflectarray (RA) antenna for 3U CubeSat applications is investigated. A novel frequency selective surface (FSS) in the RA as ground plane for reducing radar cross section (RCS) and signals interference with other communication systems working in other frequency bands is applied. The RA divided to three panels and folded on the sides of the CubeSat to reduce the stowed volume. A novel circular polarization (CP) feed antenna with two stacked patches on two thick substrates with lossy dielectric constant is used to extend the 3dB axial ratio.

• This paper presents a numerical simulation of the air drag force that small spacecraft, specifically a CubeSat, is experimenting during its mission on space. According to air drag force equation, it depends mostly on the air density values and its current speed, other parameters are considered constant due to environment conditions. The natural way a spacecraft deorbits into the Earth is due to the actual air drag force and mostly all institutions such as space agency, universities and research centers build and design their spacecraft following the 25-years rule which states all spacecraft in altitude around 400 km to 500 km must deorbit into the Earth in a maximum time of 25 years. To prove and quantify the actual air drag force, we construct an educational software library that calculates how much drag force is acting on the spacecraft according to the air density values from MSIS-E90 Atmosphere Model. Results are present in this paper.

• None

• This letter advocates the use of mechanical actuation to alter the electrical length of components within antenna elements proposed for implementation onto a CubeSat platform. Such electrical length alteration reconfigures the antenna's frequency operation without affecting its polarization scheme. This concept is first demonstrated on a reconfigurable quadrifilar helix that reconfigures its frequency operation between 750 MHz and 1 GHz, while maintaining a circular polarization behavior. As a second demonstration, a Yagi–Uda antenna is reconfigured by changing the electrical length of its reflector, fed elements, and two directors. Such alteration results in a frequency reconfiguration between 1.2 and 1.5 GHz, while preserving the linear polarization behavior of the antenna array. For both antenna examples, the reconfiguration is implemented through the appropriate mechanical actuators that are integrated within the CubeSat's cavity. As a proof of concept, both structures are fabricated and integrated on the outside chassis of a 6U CubeSat $(\text{10}\times \text{20}\times \text{30}\,\text{cm}^{3})$, where measured results greatly match the simulated data.

• This paper presents a low cost C-band microstrip antenna array with high gain, composed of 2 × 2 patches of 14.38mm by 18.42mm each, and compatible with CubeSat standard at 5.8 GHz center frequency. The feeding method is corporate feed network matched to 50 Ω line by different impedance lines. The patch's Mutual Coupling is decreased by rotating 45° each patch, obtaining a return loss of -32.02 dB, a Voltage Standing Wave Ratio of 0.4 dB and a maximum gain of 13.34 dB. Simulations with a 3U CubeSat structure with deployed VHF and UHF antennas shows little deviations. The final array size is of 74 mm × 74 mm.

• A small size and high gain slot antenna is proposed for 2U CubeSats communications. The main idea is to use a metallic part of 2U CubeSat's surface at distance of 12 mm below the antenna as a reflector to redirect the back radiation forward. This leads to a substantial suppression of back lobe radiation and hence significant increase of the antenna total gain. The simulation results show that the antenna achieves a superior gain of 9.39 dB, wide b-10 dB bandwidth of 370 MHz (2.53-2.90 GHz) and return loss of -22 dB at a resonant frequency of 2.7 GHz.