Faisel Em M Tubbal

A Survey and Study of Planar Antennas for Pico-Satellites

Works on pico-satellites have gained momentum recently, especially those that consider pico-satellites as part of a much larger constellation or swarm. This feature allows pico-satellites to provide high temporal resolution of observational data and redundancy. In particular, it reduces the need for satellite-to-ground communications and, hence, helps save energy and allows the execution of distributed processing algorithms on the satellites themselves. Consequently, satellite-to-satellite or cross-link communication is critical. To realize these advantages, the cross-link antenna employed on pico-satellites must meet many criteria, namely, small size, lightweight, low-power consumption, high gain, wide bandwidth, circular polarization, and beam steerability. To date, no works have examined the suitability of existing planar antenna designs for the use on pico-satellites. To this end, this paper contributes to the literature by focusing on microstrip patch and slot antennas that have the ability to achieve high gain, beam steering, and wide bandwidth. This paper reviews 66 planar antenna designs, which includes 38-patch and 28-slot antennas. In addition, we provide an extensive qualitative comparison of these antennas in terms of their mass, size, gain, beam steerability, type of polarization, operating frequency band, and return loss. In addition, we have evaluated three antenna designs that best address the pico-satellite challenges on a common platform. We find that the asymmetric E-shaped patch antenna design is the most suitable for the use on 2U CubeSats. This is because of its small size (34 × 13 mm2) and high gain (7.3 dB). In addition, the E-shaped patch antenna yields a wide -10-dB bandwidth of 2300 MHz and a small return loss of -15.2 dB.

S-band shorted patch antenna for inter pico satellite communications

In this paper we study and evaluate shorted patch and CPW-feed square slot antennas, both of which we deem suitable for use in inter pico satellite communications in terms of gain, bandwidth and size. We have simulated both antennas in the High Frequency Structure Simulator (HFSS). Our results show that the shorted patch antenna achieves higher gain; e.g., 4.8 dBi, wider impedance bandwidth; e.g., 3.9-11.1 GHz with Voltage Standing Wave Ratio (VSWR) ≤ 2 at resonance frequencies of 4.4, 6.9 and 10.1 GHz. In addition, the Quasi Newton method is used to shift the shorted patch antennas operating frequency to 2.45 GHz (S-band). This thus enables its use in the unlicensed ISM band without critically affecting its radiation performance. The simulated results show an impedance bandwidth of 3650 MHz (2.05-5.7 GHz) with VSWR ≤ 2 at a resonance frequency of 2.45 GHz.

Telemetry, tracking and command subsystem for LibyaSat-1

In this paper we present the design and the analysis of Telemetry, Tracking and Command Subsystem (TT&CS) for Libyan imaging mini-satellite (LibyaSat-1). This subsystem is the brain and the operating system of any satellite or spacecraft as it performs three important functions; tracking mini-satellite position, monitoring mini-satellite health and status and processing received and transmitted data. Moreover, the uplink and downlink budgets for s-band and x-band antennas are presented. We also designed s-band C-shaped patch antenna for command receiver (2.039 GHz). Electromagnetic simulation was performed to this antenna High Frequency Structure Simulator (HFSS). Our results show that the s-band C-shaped patch antenna achieves high gain of 6.45 dB and wide bandwidth; i.e., 1500 MHz. The achieved simulated return loss is -19.6 dB at a resonant frequency of 2.039 GHz.

A wideband C-shaped patch antenna for LibyaSat-1

This paper presents a wideband C-shaped patch antenna for LibyaSat-1. The two parallel slots of the upper C-shaped path are incorporated to generate a second resonant frequency and hence broaden bandwidth. The folded patch technique is used to reduce the coaxial probe length and inductance at the feed section. In addition, the Quasi Newton method is used to achieve an operating frequency of 2.215 GHz (S-band). Our simulation results show that the antenna achieves a −10-dB impedance bandwidth of 1550 MHz (2.00–3.55 GHz), and has a total gain of 6.45 dB at 2.215GHz.

Printed Yagi-Uda antenna array on CubeSat

CubeSats are now becoming increasingly popular for space programs. This is because of their affordability. Moreover, CubeSats can be built using commercial Off-the Shelf (COTS) components. They are cost effective compared with traditional satellites. CubeSats can communicate with each other within a swarm, and with ground station. These capabilities require CubeSats to be equipped with small antennas to facilitate cross-link or downlink communications. Therefore, in this paper, we present a novel design of high gain printed Yagi-Uda antenna and a two element Yagi-Uda antenna array which can be perfectly attached on 3U CubeSats aluminum bodies to avoid deployment. We have shown a numerical analysis of Yagi antenna array and simulated the antenna using the High Frequency Simulator Structure (HFSS). The simulation model is completed with the existing of CubeSat mental body. Our results show that the antenna array achieves good impedance matching with a return loss of − 26.47 dB at the desired frequency of 2.47 GHz, a −10dB impedance bandwidth of 134 MHz (2.396–2.530 GHz) and has a total gain of 6.41dB.

A low profile high gain CPW-fed slot antenna with a cavity backed reflector for CubeSats

A low profile, high gain, CPW-fed, slot antenna is proposed for CubeSats. The proposed antenna is backed with a low profile metallic reflector. The cavity reflector is utilized to significantly improve gain and reduce back lobe radiation. The antenna has a compact size of 36×36 mm2, meaning it is compatible with any CubeSats standard structure. We have simulated the antenna on a 2U CubeSat (10cm×10cm×20cm). Our results show that the antenna achieves good impedance matching with a return loss of −30 dB at the desired frequency of 2.45 GHz, a −10-dB impedance bandwidth of 109 MHz (2.391–2.50 GHz) and has a total gain of 8.62 dB.

Dipole antenna array cluster for CubeSats

CubeSats are attracting interest from both the industry and academia because of their affordability. Specifically, they are made from commercial Off-The-Shelf (COTS) electronic circuit chips, and are thus seen as a cost effective replacement for traditional, expensive satellites. Moreover, they are expected to have higher capabilities to better support demanding missions. To date, most CubeSats rely on a single element antenna that usually has a relatively low gain and are not steerable. Thus, they are not suitable for long-distance communications and for use by missions requiring high-speed links and adjustable radiation patterns. Existing single element antennas also increase the probability of failure when establishing communication links, as the failure of the single element would lead to a disconnection. In this paper, we propose a 3×1 dipole antenna array and a cluster of three 3×1 dipole antenna arrays for CubeSats. Each array can theoretically be used on a separate frequency. Advantageously, all three arrays can be combined to enhance directivity. Our simulation results show that the proposed antenna cluster has a high gain of 5.03dB and wide directivity.

A wideband F-shaped patch antenna for S-band CubeSats communications

A wideband S-band F-shaped patch antenna is proposed for CubeSats communications. To broaden bandwidth, it uses two arms with different lengths to generate a second resonant frequency. The effect of the arm length and width on the return loss, resonant frequency and impedance bandwidth on a 3U CubeSat is studied. The simulation results show that the antenna achieves a wideband of 1121 MHz (1.606–2.727 GHz) with a return loss below −10 dB over the entire frequency band from 1.606 to 2.727 GHz. The antenna has a high gain of 8.51 dB and a small return loss of −32.85 dB at 2.45 GHz.

The design requirements for Libyan imaging mini-satellite (LibyaSat-1)

In this paper we present the conceptual design of Libyan remote sensing satellite (LibyaSat-1) and its sub-systems requirements. LibyaSat-1 is a 300 kg mini satellite, which will be used to support high resolution multi-spectral earth imaging camera to fulfill the civilian needs. This satellite will operate at LEO of 775 km and will provide a resolution of 2.5 m for the panchromatic band and 10 m for the VIS/NIR bands with 30 km swath. We have presented the mission overview, mission operation concept and mission requirements. Moreover, the System Tool Kit (STK) simulation is used to show the ground trucks of LibyaSat-1 for three days and to find the contact numbers between LibyaSat-1 and both Murezeq and Tripoli stations. We have also presented the design of telemetry and command subsystem, code and data handling subsystem, electrical power subsystem, altitude orbit control subsystem, and structure subsystem.