Cubesat

This paper presents the processes of developing a physical solution to the structural subsystem of the Brazilian Technological Institute of Aeronautics – ITA CubeSat, the AESP-14 Project. This work also shows static and modal structural analysis through computational methods, in order to predict the structural response to launch environment. The INPE’s capacities for manufacturing CubeSat main structures, are also discussed and proved through Reverse Engineering applied to a Commercial Off The Shelf - COTS structure. Results of analysis showed that in average launch environment levels, the structure developed reaches maximum stresses quite below used material’s limits. Natural frequencies found are also eligible to major piggy-back launch requirements.

This review research examined technical papers covering engineering topics related to small satellites. Papers were selected based on the use case or concept of the spacecraft they pertained to. Papers reviewed focused on niche use cases or concepts, defined for the purposes of this research as those use cases or concepts where no spacecraft filling that use case has ever been launched. From these niches, this review research examined the technical aspects of the use cases which have been explored and become understood, and isolated those which had not, especially those indicated in research papers as areas needing development in order to realize a functioning spacecraft. This review focused particularly on trade studies, mission planning analyses, and analyses of obvious required hardware for mission realization. Several major unsolved engineering problems associated with niche use cases were found, and the specifics of their engineering problems were enumerated where possible.

The NTNU Test Satellite (NUTS-1) is an educational CubeSat project aiming to launch a student designed and manufactured satellite. The project is one of three participants in the Nor-wegian CubeSat program ANSAT. The current primary goal is to have an engineering model ready by August of 2016. Communication with the ground segment will be in the VHF and UHF bands, allowing for full duplex transmission. The ground segment will be based upon a Software Defined Radio (SDR) to enable an easier and more flexible configuration. The SDR-platform used is the Ettus Research USRP, supported by a GNU Radio implementation on a computer. The link layer packet protocol implemented in the prototype is NGHam, a link protocol partly inspired by AX.25. In order to improve the link reliability, it features Reed Solomon codes for Forward Error Correction (FEC). This makes the data transmission more robust compared to i.e. AX.25, which does not implement FEC on the link layer directly. The required GNU Radio modules have been designed and implemented. An end-to-end communication between the USRP and the NUTS VHF module has been proved. A ground station based on traditional HAM radio equipment requires several bits of hardware, such as a radio, TNC or third part modems in order to enable packet transmission. By replacing this with a SDR setup the ground station will be more flexible; it will be easier to receive data from different satellites that might be using different link protocols and message formats. Utilising open source software, such as GNU Radio, gives radio amateurs around the world the opportunity to receive data from NUTS using cheap SDR hardware such as the RTLSDR USB dongles. Finally, as an SDR system can support a wide range of frequency bands, it will be easy for other project groups to implement support for their satellite mission using such an SDR based system. Support for other link protocols can easily be implemented. Messages received from the satellite(s) can easily be made available online.

Emerging technologies of CubeSat communication and navigation systems enable new approaches such as larger bandwidths, spectrum and security decrement and high speed communications. In order to create a vantage point, young professionals and students from the four corners of the earth had performed a comprehensive study at the 2014 Space Generation Congress in Toronto, Canada under "CubeSat Swarms Communication Networks and Policy Challenges" working group. While potential possibilities are endless for the structure of Cubesat networks, decisions made amongst the group were based on existing technologies and guidelines. Therefore, the working group discussed (1) short and long term technical challenges (2) policy requirements, (3) radio communication bandwidth limitations, (4) data collection and transmission regulations and (5) the standardization of the CubeSat communication system. Technical challenges for small satellite missions involve limitations of link budgets, the size of the deployable high gain antennas, optical and laser communication and the restriction of the link budget due to the interferences. In addition, policy issues have immaturities for frequency allocation and registration complimenting the short lifespan of CubeSats. The standardization of mission operations enables a space communication network architecture that of which is similar to the internet, incorporated into CubeSat Swarms. The group suggests a CubeSat network system architecture including inter-swarm and intra-swarm constellations, optical and laser communications and delay-tolerant networks (DTN). The proposed CubeSat communication network also consists of inter-swarm constellation communications along with intra-swarm constellations sustained through four different basic data links, a mother-daughter satellite framework, and net-neutrality throughout the network. In the meantime, policy regulation recommendations allow global communication by reducing data downlink time. Governments, as well as service providers, treat all data used online the same regardless of its origins, platform, and users. The standardization of the CubeSat network system was formed by operator expectations for high downlink speeds, equal priority for data transfers, and streamlined registrations. The simplified registration process for CubeSat-Swarms is more efficient by establishing new baseline legal framework, rules, and standards. This would help all users and operators in this sector, including entrepreneurs, licensing bodies, and end-users. Saving time for everyone while achieving maximum efficiency, utilization of the time and results are the end result of proposed system architecture by the working group.

DVB-S2 is a CCSDS telemetry standard, called adaptation standard in the CCSDS terminology, fully reusing the ETSI DVB-S2 mass-market telecommunication standard, thus providing the advantage of a wide diversity of very robust commercial mass market receivers, cheaper than the receivers dedicated to space telemetry links. CNES is currently upgrading with Syrlinks an existing X Band Transmitter for cube & nanosatellites (TRL 9) to use DVB-S2 CCSDS telemetry standard. The Variable Coding and Modulation (VCM) mode will provide up to 60% increase of the downloaded data compared to Constant Coding and Modulation (CCM), a link budget improvement of about 2 dB in QPSK for the same transmitted power and a better spectral efficiency.

CubETH is a one unit CubeSat developed in collaboration between EPFL (Lausanne) and ETH Zurich. The main objective of CubETH is to demonstrate the use of commercial GNSS receivers in space and test Precision Orbit Determination algorithms. One of the key driving requirements is to provide nadir pointing with a 20 degrees of precision and rotation rate less than 2 degree / second, in order to track GNSS constellation satellites. In this paper the solutions for the ADCS and the designed operatives modes are described. The ADCS shall provide for the Payload a nadir pointing with relaxed requirements, and in order to do that the team paid particular attention to the validation of the chosen hardware and software solutions. According the experience of SwissCube, its five years of data collected and lessons learned, we have started a vigorous process of design, implementation and validation for ADCS with several test setups and characterizations for sensors and actuators. We present the ADCS focusing mainly in the implementation, in the errors encountered and the process of validation in our test setups. A ball bearing with a Helmotz Cage has been used to validate the functionality of implemented algorithms (B-dot, TRIAD and an Extended Kalman Filter), results will be presented. Sensors calibrations and characterizations are addressed giving particular emphasis on their thermal drifts that can affect the determination process. Tests in Thermal Chambers show some interesting behaviours of the selected COTS sensors. A vigorous test campaign has been done on the first batch of Sun Sensors revealing not negligible effects that should be taken into account during final implementation. Even the actuators (magnetorquers) have been heavily tested to characterize their dipoles; tests revealed a really good match between the theoretical models and the hardware. Several test setups have been designed in order to characterize separately COTS components, and actuators for ADCS but more remarkable is the effort that has been spent for the validation of the whole ADCS system: one of the most challenging subsystem for CubeSat is the ADCS due to the several test setup and validations necessary to prove its functionality.

Swiss Federal Universities of Lausanne and Zurich have initiated a new 1U Cu- beSat project. The main objective of the CubETH is to demonstrate use of com- mercial GNSS receivers in space and test Precision Orbit Determination algo- rithms. One of the key driving requirements is to provide zenith pointing with a 20 degrees of precision and rotation rate less than 2 degree / second, in order to track GNSS constellation satellites. This paper will describe details of Attitude Determination and Control Subsystem (ADCS) based on magnetotorquers in or- der to satisfy the science requirements. We will discuss lessons learned from the ADCS implementation on the first Swiss nanosatellite SwissCube (in operation since 2009) and we present the flat shaped magnetotorquers (MTQs) designed in the laboratories of the Ecole Polytechinque Federale de Lausanne (EPFL) in Switzerland, detailing design, the test setup and t procedures performed.
We present theoretical calculations for the magnetotorquer parameters, simula- tions, details of manufacturing and results of testing done in the shielded room of the Ecole Poly-techinque Federale de Lausanne. Testing shows a 93% of match be-tween the 3D model and tests done with the magnetic probe on the new de-sign prepared for CubETH, where the design slightly changed from the previous shape of SwissCube.
The paper presents the description of the manufacturing and the process fol- lowed in order to highlight the encountered issues on the magnetotorquers fabri- cation. We address the process to select the proper materials and quantities for the manufacturing of flight and engineering models, ad-dressing the required characteristics for the material selected.

A 3-Unit CubeSat, called “3USAT”, is developed for voice communication in Low Earth Orbit (LEO). The
spacecraft was launched on 26th of April 2013 from China Jiaquan Satellite Launch centre with a LM2D launch
vehicle. The main payload of the 3USAT is a linear transponder operating in VHF/UHF. The 3USAT includes many
sensors and a camera for taking pictures, as well. Most subsystems of the CubeSat have redundancy which is
provided by COTS equipment and/or in-house developed systems. The two transponders are developed genuinely by
the project team. The project team have gained valuable experience from developing subsystems, integrating COTS
equipment’s, and carrying out space simulation testing. The payload power requirements resulted in temperatures
exceeding 100oC. A remedy was developed to remove heat resulting from high power amplifier. Other problems
encountered and resolved include grounding issues of electronic and RF systems, the transfer of data and power
using PC104 form factor between 1U sections of for 3U COTS structures, thermal vacuum testing of payloads with
supporting equipment outside of the chamber, cabling and "cold solder joint" among others.

For most satellite missions, it is essential to decrease the satellite angular velocity. The Β algorithm is a common algorithm to stabilize the spacecraft by using magnetorquers. Controlling the satellite using the magnetorquers is part of the attitude control subsystem detumbling mode. Due to the oscillating disturbances in the space environment, the required initial conditions needs analysis. As a consequence, the satellite stays in Β detumbling mode for the entire operation. In detumbling mode, the spacecraft oscillates around its spatial axes. The purpose of this paper is to extend the Β algorithm with a disturbances compensation module and to achieve a reduction of satellite's angular velocity. The developed algorithm could reduce satellite's angular velocity up to 10-11 degree. 1. Introduction The success of a space mission depends on sophisticated attitude control subsystem (ACS). As the ACS can only be activated if the spinning about the satellite's own axes remains within certain boundaries, uncontrolled oscillation should be minimized, even if a precisely determined orientation is not required for the particular mission. Due to the increasing importance of small and very small satellites such as CubeSat satellites, which are mainly operating in a low earth orbit (LEO) under a relatively strong earth magnetic field, the relevance of magnetic attitude control systems has also grown [1, 2]. This is pushed by magnetorquers' low prices, their space saving assembly, and the independence of propellant. Therefore, they are often the only actuators in CubeSat missions. They are integrated inside the solar panels to obtain the necessary electrical power [3]. The Β law, a purely magnetic control scheme, was originally proposed in [4]. Since then, this control law has been adopted as the primary detumbling solution in small satellites such as Pico Satellite Solar Cell Testbed-2 (PSSCT 2) [5] and T-SAT1 [6]. While the aforementioned studies present satisfactory detumbling performances, the initial conditions are difficult to estimate in real applications. The tuning factor, for instance, is generally chosen based on trial and error experiments. However, the initial factor chosen may not reject the oscillating disturbances effectively, and the control law may fail in case the disturbances change. Therefore, the satellite is not detumbled effectively. The aim of this work is to present a novel yet convenient Β algorithm to subside the effect of oscillating disturbances in the space environment. The study presents a solution to control the current by a pulse width modulation (PWM) signal and proposes a gain factor function to obtain the optimum torque to reject the disturbance. The method has been simulated and tested further on a CubeSat to validate the feasibility of the proposed scheme. The paper is organized as follows: the conventional and the novel Β algorithms are introduced followed by the description of the mission and the strategy. The validation procedure using the CubeSat and the obtained results are presented later followed by the simulation results. The conclusion describes the findings of the study.

Swiss Federal Universities of Lausanne and Zurich have initiated a new 1U CubeSat project. The main objective of the CubETH is to demon- strate use of commercial GNSS receivers in space and test Precision Or- bit Determination algorithms. One of the key driving requirements is to provide zenith pointing with a 20 degrees of precision and rotation rate less than 2 degree / second, in order to track GNSS constellation satel- lites. This paper will describe details of Attitude Determination and Con- trol Subsystem (ADCS) based on magnetotorquers in order to satisfy the science requirements. We will discuss lessons learned from the ADCS implementation on the first Swiss nanosatellite SwissCube (in operation since 2009) and we present the flat shaped magnetotorquers (MTQs) de- signed in the laboratories of the Ecole Polytechinque Federale de Lau- sanne (EPFL) in Switzerland, detailing design, test setup and procedures performed. The main lesson learned from SwissCube is to establish vig- orous testing procedures for all sensors. This paper will present tests set- up and procedures used for the present and the future tests in the labora- tories of the Swiss Space Center that take experience from the lessons learned. We describe tests set-up, interfaces and procedures performed to establish trade-off study for the sensors: static and dynamic characteriza- tions, temperature behaviors and others. The paper gives to the CubeSat community a validated and simple process to characterize the sensors for the attitude determination.

BeEagleSat uydusu ülkemizde üniversiteler, büyük sanayi ve KOBİ işbirliğinde, Avrupa Birliği QB50 projesi kapsamında geliştirilmekte olan iki birim bir küp uydudur. QB50 projesi ile ilk defa küp uydular birincil yük olarak uzaya erişim olanağı bulacaktır. Ayrıca, çok uluslu ve çok kurumlu bir yapılanma içerisinde uzay sistem geliştirme tecrübesi bulunan birçok büyük uzay kurumunun deneyiminin de kullanarak küp uydular kümesi geliştirme birikimi oluşturulmaktadır. Uyduların ana amacı henüz yeterince incelenmemiş termosfer tabakasında proje kapsamında geliştirilmekte olan duyargalar ile ortam ölçümleri yapılması, yapılan ölçümlerin dünya çapındaki yer istasyonları tarafından toplanması ve bilginin paylaşılmasıdır. Ölçülen veriler ile daha doğru termosfer modellemesi yapılması öngörülmektedir. BeEagleSat uydusu ortakları da QB50 projesinin uluslararası ortamı içerisinde dünya deneyimlerini kendi tecrübeleri ile birleştirmektedir. Uydunun yönelim kontrol ve duyarga sistemleri proje kapsamında QB50 konsorsiyumu tarafından sağlanmakta, ikinci ana yük ve diğer alt sistemler ise proje ekibi tarafından geliştirilmektedir.

This paper aims at providing a performances comparison of different High Data Rate Telemetry (HDRT) solutions dedicated to high data volume downloading. Links in X and Ka bands are considered in order to fulfill the future missions needs such as Earth Observation. Considering the expected wide data amount to be downloaded for these missions embedded on satellites in Low Earth Orbits, LEO Direct To Earth solutions have been considered for this comparative study.

Heterogeneous Spacecraft Networks (HSNs) are network environments in which spacecraft from different missions and institutions can communicate with each other at low cost and with low impact on overall system resources. The Mission Design Center (MDC) at NASA Ames Research Center has been studying solutions for low cost multi-spacecraft systems for a number of years. One may now build on the idea to interconnect clusters of spacecraft with each other to have them act as mobile nodes belonging to the same collaborative mission. Recent progress in small satellite technology is significant, and one of the advantages of small satellites lies precisely in the large quantity of spacecraft that can be produced at accessible costs. It follows naturally that small satellites are an interesting candidate platform for development and demonstration of the HSN concept. This paper is the second in a series of three companion papers. The general concept of operations for HSNs in LEO and a number of future applications are proposed in the first paper [6], while enabling technology such as devices and lower layer protocols are discussed in paper three [7]. In this paper, we pick up the scenario of a low-cost and multi-institutional network of Earth Observation (EO) missions in LEO and conduct network performance analysis using the AGI System Tool Kit (STK) and the open-source Network Simulator (NS-3). A multi-spacecraft network consolidates the individual capabilities of each spacecraft from different institutions by combining benefits of both frequent revisit and concentrated observation. Complementary and correlated data could be collected simultaneously from a large set of distributed spacecraft utilizing HSN capability. In this specific configuration, communication distance between spacecraft, related delays and error rate are the major factors in network performance. Also, average duration of communication opportunities between spacecraft is usually very limited. Thus, it is i- portant to simulate orbital dynamics, link margins, and protocols simultaneously to analyze network performances. In this paper, we compare some existing protocols to obtain a measure for the practical performance of the candidate network. We focus on best-effort data delivery, an approach necessitated by the severe constraints on communications resulting from low-cost and low system resource small spacecraft. In the application layer, we show that packet size and data rate of a source node also affect overall performance of the network. We present the resulting figures of merit from our simulations. The paper concludes with a summary of the simulation results.

This paper gives an overview of CNES activities in the field of very High Data Rate Telemetry (HDRT) for new very high resolution Earth observation satellites.

A CNES technological program 'OTOS' (former 'CXCI') was committed in 2011 to develop and demonstrate key technologies for a new generation of optical observation satellites system ('Pléiades' follow-on system), among them in particular an active telescope demonstrator.

A part of the program was allocated to HDRT developments:

- a 'DVB-S2 transmitter' and a 'DVB-S2 receiver' using CCSDS recommended standard 131.3 [1] (calling ETSI DVB-2 standard [2])

- an Antenna Pointing System (APS) based on an Antenna Pointing Mechanism (APM).

This paper describes a mathematical model developed for a Sun sensor as well as an embedded algorithm and electronic design with space-qualified characteristics to compensate voltage changes in the response of a set of four silicon solar cells, which are essential detecting elements in this sensor. This development was implemented due to temperature variations present in the outer space. Silicon solar cells were characterized and calibrated; however, on orbit, changes in their response are expected. Tests results performed with this sensor in laboratory conditions are described.

A CdZnTe based semiconductor X-ray detector (XRD) and its associated readout electronics is developed by the
Space Systems Design Laboratory of Istanbul Technical University and High Energy Astrophysics Detector
Laboratory of Sabanci University along with an SME partner. The detector will utilize 30 orthogonal cross strip
electrodes (and 3 steering electrodes in between anodes) whose geometry is optimized by an extensive set of
simulations and energy resolution measurements. The signals will be read by RENA 3b ASIC controlled by MSP
430 microcontroller. The system will have its own battery and will be turned on intermittently due to power
constraints. CdZnTe based X-ray detectors have been utilized in space, but they are either pixelated (NuStar), or they
consist of many individual crystal pieces (BAT in Swift satellite). The aim of the XRD is to show that large volume
crystals with orthogonal strips are viable alternatives, especially for small satellite systems with medium energy
resolution requirement. XRD will also characterize the hard X-ray background in 20-200 keV at low Earth orbit
conditions as a function of altitude. Due to power and telemetry constraints, the individual events will be corrected
for hole trapping on-board, histogrammed, and only the X-ray spectra will be transmitted to the ground station along
with a small set of raw data for diagnostic purposes.
The XRD is planned to travel into space, as a secondary science mission, on board BeEagleSat which is a 2U
CubeSat developed as one of the possible double (2U) CubeSats for the QB50 project. QB50 is a European
Framework 7 (FP7) project carried out by a number of international organizations led by the von Karman Institute of
Belgium. Its main scientific objective is to study in situ the temporal and spatial variations of a number of key
constituents and parameters in the lower thermosphere with a network of about 50 double and triple CubeSats,
separated by few hundred kilometers and carrying a determined set of sensors.

In the recent years, nanosatellites based missions are becoming of great interest in the space programs panorama, since they offer the possibility of a wider hardware distribution, costs reduction and losses mitigation in case of failures. A distribution of nanosatellites would also grant a wide coverage of the space region under study, allowing better mapping or sampling, together with an enhancement of communications thanks to a distributed links net. The achievement of these objectives requires, however, the distribution of the spacecraft to have peculiar configuration geometries or to satisfy particular constraints, therefore deep study on the formation flying strategies has to be conducted. With reference to the future mission AIDA (Asteroid Impact and Deflection Assessment) and the target binary asteroid system " Dydimos " , the present study shows results of the research on periodic orbits in the Circular Restricted Three Body Problem frame, applied to irregular gravitational fields generated by the asteroids, to provide a set of suitable trajectories to maintain a formation of nanosatellites. After a general overview on the algorithms and computational strategies adopted, various orbit families in the asteroids environment are shown, highlighting differences with their equivalent in the point masses model. Then, configurations of a two satellites formation are searched to maximize the shape maintenance while satisfying the mission requirements. Finally, suggestions of possible improvements of the research are given.

ICEPS (Irvine-Class Electrical Power Supply) is the system core that EXA designed for the 1U IRVINE-03 satellite, currently in construction and in the late stages of development for the Irvine Cubesat STEM Program under a 12-year plan to provide satellite parts. It was designed based on Ecuador's first satellite NEE-01 PEGASUS's PCEPS launched in 2013, and its newer counterpart has modernized capabilities including an EPIQ Z2 Sidekick OBC (On-Board Computer) running Linux IIOS, 2 SDRs (Software Defined Radio) with a frequency range from 70 MHz to 6 GHz being able to adapt to any communications network or application, 512GB of storage, 50 W power delivery up to 100W peak power for 2.5 seconds and able to operate in temperatures between-50 C and +125 C. It has an IMU (Inertial Measurement Unit) with a 6-axis Motion Tracking Device for ADCS precise operations, includes 4 UMPPT channels, each one with 16 V @ 2 A and with a total of 20 internal sensors for data collection and system monitoring purposes. It has been designed to be on the cutting edge of modern mission requirements, with a total height of 25 mm and a total mass of 100 grams in a single board. The native architecture of the entire digital system is USB 2.0. Due to the high mission requirements of IRVINE-03, this enables the use of more modern devices and components, with a much faster data transfer rate than traditional cubesat digital systems. The system core includes the capability to mount a 2W communication laser with a speed of 10Mbps and supports a 5W laser at 100 Mbps, which enables cubesats to perform previously unattainable communication goals and data download requirements, previously impeded by slow data download rates. Its first technological readiness test will be IRVINE-03, and has become the default system core of all the next IRVINE cubesat missions. In addition, ICEPS will also be used in the upcoming Spacebit's Asagumo robotic walker, as a payload on Astrobotic's Peregrine lunar lander on 2021. This paper will describe all the features and characteristics of ICEPS, along with all electrical and dimensional specifications, as well as its potential for expansion and improvement.

During the development of the first Ecuadorian satellite once mission objectives and payload design was complete, the power budget calculations indicated that we would need a large amount of energy to run the main payload which was a real time video transmission system, our system design guidelines dictated that such power matrix should be robust, redundant and would need a backup system in order to ensure a continuous operation over the longest period of time possible, considering that our solar arrays were composed of solar cells with an efficiency of only 19 percent. We needed a power supply of at least 26.64 Watts per bank, and as per our system safety guidelines the power matrix turned into 4 of this banks, giving a total of 106.56 Watts, the challenge was to pack this much power into an space small enough to fit into a 1U structure. The benefits of having this much power available for the spacecraft became obvious as we calculated the expected life of the power matrix and simulated/tested the illumination-eclipse cycle and charge-discharge periods, thus reducing the load on each cell and maximizing the expected battery life, each array was composed of 16 cells each, and our spacecrafts carry 2 of this arrays on board, also each array uses the waste heat of the spacecraft electronics to warm itself by the use of a carbon nanotubes based thermal transfer system and a micro MLI layer that allows the arrays to avoid radiating this heat back into the neighboring internal electronics. Now after more than 3 years operating in space in 2 spacecrafts, NEE-01 PEGASUS and NEE-02 KRYSAOR, this battery array design has demonstrated to exceed the expectations of the system design guidelines. This paper will describe the system; discuss testing and operation data as well as a new thin design to flight in one upcoming U.S. cubesat mission next year and more follow-up missions of this program.

The exploration of NEA (Near Earth Asteroids) is characterized by many problematics such as collision risks, irregular gravity fields and, in case of binary systems, multibody gravity perturbations, whose negative effects on mission design could be mitigated by the exploitation of multiple spacecraft in formation, with lower weights, dimensions and costs. Nanosatellite fully meet these needs, however, the poor control capabilities, and the strict requirements on relative dynamics to ensure the same performances of a single heavy spacecraft, request an efficient strategy to determine the suitable trajectories in this chaotic environment. The paper proposes a simple technique, based on orbit sampling and local optimization, to define a set of suitable configurations for a two-nanosatellite formation. After a quick review on the orbits determination and combination in binary asteroid environments, and the presentation of the objectives derived from the conceptual mission AIM (Asteroid Impact Mission), the local optimization algorithm is explained, paying attention to the selection of the method and its modification to best adapt to the specific problem. Then, results are presented, showing the strength and weakness points of the overall procedure, for the definition of future improvements.

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.