Identification of Design Considerations for Small Satellite Remote Sensing Systems in Low Earth Orbit

Triana, Juan Sebastián; Bautista, Sebastián; González, Freddy Alexander Díaz

doi:10.5028/jatm.v7i1.405

Cited by 13 publications

(9 citation statements)

References 22 publications

(17 reference statements)

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“…As shown in Figure 2, reflector, driven and director elements are printed on FR4 substrate and form a Yagi shape. FR4 dielectric is adopted in this antenna design, as it has been widely used, both in PCBs and antennas on low earth orbit (LEO) CubeSat missions, providing a low cost alternative to other expensive low loss dielectrics [20,21]. The operating frequency of the proposed antenna can be adjusted so that the antenna operates at L-band and S-band by rotating the antenna around its x-axis.…”

Section: Discussionmentioning

confidence: 99%

A Printed Yagi Antenna for CubeSat with Multi-Frequency Tilt Operation

et al. 2020

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In this paper, a printed Yagi antenna with an integrated balun is proposed for CubeSat communications. The printed antenna is mechanically adjustable to realize three functional states at different operating frequencies in the L-band and S-band respectively. Three different angle deployments are proposed at 10°, 50° and 90°, so that the antenna operates at three different operating frequencies, namely 1.3 GHz (L-band), 2.4 GHz (S-band) and 3 GHz (S-band). The measured results of the fabricated antenna are well matched with the simulation, having frequencies of 2.82–3.07 GHz, 1.3–1.4 GHz and 2.38–2.57 GHz, with similar radiation patterns. The measured gain of the antenna is 8.167 dBi at 2.4 GHz, 5.278 dBi at 1.3 GHz and 6.120 dBi at 3 GHz. Keeping within the general theme of cheap off the shelf components for CubeSats, this antenna design allows the CubeSat designers to choose from three popular frequencies, through a simple angle configuration. The main contribution of this work lies with the reconfigurable frequency, relatively high gain and simplicity of design.

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Section: Discussionmentioning

confidence: 99%

A Printed Yagi Antenna for CubeSat with Multi-Frequency Tilt Operation

et al. 2020

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“…This methodology pretends that the subsystems of the satellite are designed with the same communication bus and are not subject to the design of a single mission, for example, EPS (Electrical Power Supply), C&DH (Command and Data Handling), COMM (Communications), and ADCS (Attitude Determination and Control System). These subsystems are characterized by enabling the execution of functions for an experiment or a payload in particular and typically make up the architecture of any modern satellite system, such as CubeSats or satellites in a one-liter volume cube [6]. An exciting field for testing experimental payloads is the mea-surement of atmospheric variables through high-altitude balloons since they involve handling a large amount of data and maintaining a long-range telecommunication downlink.…”

Section: Introductionmentioning

confidence: 99%

Experimental Approach for the Evaluation of the Performance of a Satellite Module in the CanSat Form Factor for In Situ Monitoring and Remote Sensing Applications

Rodríguez

Botero

Valle

et al. 2021

International Journal of Aerospace Engineering

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This article includes the phases of conceptualization and validation of a picosatellite prototype named Simple-2 for remote sensing activities using COTS (Commercial-Off-The-Shelf) components and the modular design methodology. To evaluate its performance and ensure the precision and accuracy of the measurements made by the satellite prototype, a methodology was designed and implemented for the characterization and qualification of CanSats (soda can satellites) through statistical tests and techniques of DoE (Design of Experiments) based on CubeSat aerospace standards and regulations, in the absence of official test procedures for these kinds of satellite form factor. For the above, two experimental units were used, and all the performance variables of the different satellite subsystems were discriminated. For the above, two experimental units were used, and all the performance variables of the different satellite subsystems were discriminated against. These were grouped according to the dependence of the treatments formulated in thermal and dynamic variables. For the tests of the first variables, a one-factor design was established using dependent samples on each of the treatments. Then, hypothesis tests were performed for equality of medians, using nonparametric analysis of the Kruskal-Wallis variance. Additionally, multivariate analysis of variance was carried out for nonparametric samples (nonparametric multivariate tests), and the application of post hoc multiple-range tests to identify the treatments that presented significant differences within a margin of acceptability. To know the dynamic response and ensure the structural integrity of the satellite module, shock, oscillation, and sinusoidal tests were applied through a shaker. Having applied the experimental methodology to the different units, the results of a real experiment are illustrated in which a high-altitude balloon was used through the application of nonparametric regression methods. This experiment’s interest measured thermodynamic variables and the concentration of pollutants in the stratosphere to corroborate the operating ranges planned in the above experiments using on-flight conditions and estimate the TLR (technology readiness level) of future prototypes.

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“…When it comes to LEO path, there are several radiations that is present. This radiation may lead to some single event effect (SEE) which consists of single event upset (SEU), single event-latchup (SEL), single event burnout (SEB), and single event gate rupture (SEGR) [4][5][6][7][8][9]. This paper is focusing on SEL effects and mitigating it.…”

Section: Introductionmentioning

confidence: 99%

Single event latch-up detection for nano-satellite external solar radiation mitigation system

et al. 2021

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This paper presents the single event latch-up (SEL) detection for nano-satellite external solar radiation mitigation system. In this study, the SEL detection analysis was conducted using circuit test and simulation. An electrical power subsystem (EPS) is a part of all CubeSat bus subsystems and it comprises solar arrays, rechargeable batteries, and a power control and distribution unit (PCDU). In order to extract the maximum power generated by the solar arrays, a peak power tracking topology is required. This may lead to the SEL with the presence of high voltage produced by solar. To overcome the SEL problems, the circuit test and simulation must be done so that the flow of SEL will be easily detected and mitigate. The method that been used are by using microcontroller, the SEL will be created in the certain time. The programable integrated circuit (PIC) are used to mitigate SEL effect. It indicates that, the SEL occur very fast in certain time. When the simulation is conducted by using SPENVIS, the result shows, only single event upset (SEU) was affected on UiTMSAT-1.

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Identification of Design Considerations for Small Satellite Remote Sensing Systems in Low Earth Orbit

Cited by 13 publications

References 22 publications

A Printed Yagi Antenna for CubeSat with Multi-Frequency Tilt Operation

A Printed Yagi Antenna for CubeSat with Multi-Frequency Tilt Operation

Experimental Approach for the Evaluation of the Performance of a Satellite Module in the CanSat Form Factor for In Situ Monitoring and Remote Sensing Applications

Single event latch-up detection for nano-satellite external solar radiation mitigation system

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