CubeSat Development Research Articles

Triangular fin array passively actuated by bimetallic coils for CubeSat thermal control

CubeSat thermal control can be especially demanding due to volume and size constraints, high power dissipation per unit surface area, and highly variable internal and external heat loads. As such, CubeSat developers must rely on thermal control systems that meet the specific requirements of their mission and environmental conditions. Deployable radiators enable satellites to increase their radiative surface area and to reveal highly emissive surfaces during times when increased heat rejection is desired. In colder conditions, when decreased heat loss is preferable, the radiators can be stowed. Passive thermal control systems are unpowered and can increase system reliability by not relying on control electronics while offering decreased weight and power requirements. In this work, we propose a deployable array of triangular radiator panels that are independently and passively actuated by bimetallic coils in response to changes in temperature. This system demonstrates the use of bimetallic coils to passively deploy and stow the radiator fins as well as the use of multiple CubeSat radiator fins with independent actuators to provide increased redundancy. An experimental prototype of the system design was subjected to vacuum chamber testing with panels held in a fixed, deployed position to obtain temperature data used to tune a thermal simulation model. The prototype was then placed in a cryogenically cooled vacuum chamber environment with the panels free to actuate passively in response to varied heating conditions. Both steady state and transient testing were performed. Through this testing and the use of the tuned thermal simulation, the experimental prototype is determined to have a turndown ratio (largest cooling power / smallest cooling power) of 5.4. Deployment of the radiator panels serves to reduce CubeSat body temperatures by 45 °C. Results show the efficacy of the bimetallic coil actuators and radiator fin array in providing passive, dynamic thermal control to small satellites. Recommendations are made to further enhance the performance of the system. Of these recommendations, the most critical is to improve the thermal conductive path from the CubeSat body to the bimetallic coils and to the triangular radiator panels across the deployable radiator hinge. Such changes provide the possibility of increasing the maximum heat rejection, responsiveness of the thermal control system, and turndown ratio to 9 or greater.

Design and Development of a 3D-Printed CubeSat by Go Science

This project outlines the design, development, and construction of a 3D-printed CubeSat, a miniature satellite, equipped with an ESP32 microcontroller, an MPU9250 inertial measurement unit, and a BMP280 barometric pressure sensor module. The CubeSat adheres to standard CubeSat dimensions and incorporates a range of systems, including power management, communication, and data collection, to enable its functionality in space. The CubeSat's structure was meticulously designed using CAD software, and 3D printing technology was employed to fabricate its lightweight, space-grade casing. The ESP32 microcontroller serves as the central processing unit, interfacing with the MPU9250 and BMP280 sensors via I2C communication. Custom firmware was developed to gather sensor data and manage power resources efficiently. Solar Panels are also used for redundant Power Support. The CubeSat features a wireless transceiver for communication with ground stations, facilitating telemetry data transmission and command reception. This CubeSat can collect sensor’s data and transmit it to Ground Station for analysis, contributing valuable insights into its surrounding environment. Maintenance and potential upgrades will be considered to extend its operational lifespan. This project exemplifies the intricate process of designing and developing a CubeSat, highlighting the integration of advanced sensors and microcontrollers in a 3D-printed structure. The CubeSat's deployment underscores its potential for scientific research and data collection in the realm of space exploration. Developed by Go Science Technical Team. IndexTerms – Go Science, CubeSat, ESP32, MPU9250, BMP280, Environmental Monitoring, Space Technology, Sensor Integration, Data Collection, Climate Research, Microsatellites, Miniature Satellites, Space Sensors, Atmospheric Data, Earth Observation, Remote Sensing, Environmental Science, Climate Monitoring, Sensor Fusion, Space Exploration.

Design And Development of A CubeSat for Atmospheric Research

The paper "Design and Development of CubeSat for Atmospheric Research" presents the development and design of a CubeSat for studying the Earth's atmosphere. CubeSats are miniature satellites that offer a cost-effective option for conducting scientific research in space. The paper discusses the selection of sensors, communication systems, and other subsystems necessary for the successful execution of the mission. The study shows the viability and possible uses of CubeSat missions for atmospheric research, such as tracking weather patterns and examining climate change's consequences

Payload-XL: A Platform for the In-Orbit Validation of the BRAVE FPGA

Design and verification techniques targeting the space environment, are widely used to explore reliability levels of embedded systems for Cubesats. Considering that, we carried out a study to select and to adapt a design flow to be used as a guide for the development of Cubesats. The chosen design and development flow was used in a case study of a board, called Payload-XL, conceived to be the computing module of a Cubesat. The primary purpose of Payload-XL is to validate the BRAVE FPGA from Nanoxplore, in orbit. Research and development activities were carried out to integrate the GOMX-5 mission through a partnership between the Federal University of Santa Catarina, the European Space Agency, Cobham Gaisler, GMV, CBK, and GomSpace. The results demonstrate that Payload-XL innovates as a validation platform for the BRAVE FPGA, and also bringing mechanisms to reconfigure it remotely in orbit. Furthermore, the results show that Payload-XL complies with the power, size, and requirements of the GOMX-5 mission.

On-Board Computer and Testing Platform for CubeSat Development

The design and development of a CubeSat testing platform built from scratch is the focus of this work. The investigation was conducted as part of the Canadian CubeSat Project (CCP), initiative conducted by the Canadian Space Agency (CSA) to support the development of 15 CubeSats across Canada. In this paper, a particular emphasis is placed on three key subsystems: an On-Board Computer (OBC), a GNSS based payload, and a communication board, all connected together through a FlatSat board. The Mission software running on an STM32-microcontroller-based OBC is responsible for managing all CubeSat activities. The OBC was designed to meet a range of requirements, including mechanical, electrical, and thermal requirements. Indeed, due to the intense heat and radiation that the CubeSat will be exposed to in Low Earth Orbit (LEO), the CubeSat may experience many difficulties, potentially leading to mission failure. The risk-reduction techniques used in the design of the OBC will be discussed in detail. The tests performed on the developed OBC were successful, including an initial power test and a vacuum test, where the microcontroller entered low-power mode for a total of 10 seconds, consuming only 0.0528 W of power.

Development of a Low-Cost Multispectral Sensing CubeSat on Amateur Radio Frequency

MESAT1 is a CubeSat that was designed and built at the University of Maine. The purpose of the CubeSat is to use low-cost and low-power CMOS cameras to analyze water turbidity, identify urban heat islands, and predict harmful algal blooms from low Earth orbit (LEO). This work discusses the design of the spacecraft architecture and physical configuration, as well as the design of a multispectral remote sensing instrument based on low-cost consumer-grade cameras, a custom electrical power supply, an onboard computer based on the Raspberry Pi compute module, a custom, low-cost deployable spacecraft antenna system, and a ground station with automated tracking.

3D-Printing for Cube Satellites (CubeSats): Philippines‘ Perspectives

The increase in space exploration missions in recent years gave way to the development of a volume-efficient and cost-effective nanosatellite like the cube satellite (CubeSat) which can be developed and fabricated in a relatively short time. With its size and design, CubeSat parts like casings can be produced and assembled through 3D printing to produce inexpensive satellites. Research in this area is undeniably important to maximize the rapid development of CubeSats. While progress has been made, challenges remain in applying 3D printing technology in the development of CubeSats. In this paper, the current status regarding the advancement of 3D printing for CubeSat applications is discussed. First, important issues about the common materials for CubeSat and potentially 3D printing materials for CubeSats are addressed. Second, 3D printing CubeSat parts through the feasible structure design models by combining material and parameter designs are explored from a wide range of references. And also, 3D printing of cube satellite parts by DOST AMCen and STAMINA4Space has also been demonstrated. Lastly, an outlook on the future direction of the 3D printed CubeSat for the Philippines space program is provided.Keywords: Cube satellite, CubeSat, 3D printing, high-performance polymers

Compact Scintillator Array Detector (ComSAD) for Sounding Rocket and CubeSat Missions

The development of CubeSats and more frequent launch chances of sounding rockets are a total game changer to the space program, and it allows us to build space instruments that are technologically feasible and affordable. Therefore, it gives us a good opportunity to build a small cosmic-ray detector which has capabilities to measure the flux, direction, and even energy of cosmic rays at an altitude above the limitation of balloon experiments, and it may open a new door for building a constellation of detectors to study cosmic-ray physics. Compact Scintillator Array Detector (ComSAD) is a funded sounding rocket mission of Taiwan’s National Space Organization. In this paper, we present the concept, design, and performance of ComSAD which is also suitable for future CubeSat missions.

Lessons Learned from Cubesat Development

Lessons Learned from Cubesat Development

Development of the EIRSAT-1 CubeSat through Functional Verification of the Engineering Qualification Model

The Educational Irish Research Satellite (EIRSAT-1) is a 2U CubeSat developed at University College Dublin. The project aims to build, test, launch, and operate Ireland’s first satellite and to perform in-orbit demonstrations of three novel payloads developed in-house. To reduce risk within the mission, the project employs a prototype model philosophy in which two models of the spacecraft exist: an engineering qualification model (EQM) and a flight model (FM). This paper presents the verification approach of the functional tests implemented for the EIRSAT-1 project. The activities of the FlatSat and system level full functional tests of the EQM are presented and the results obtained during the test campaigns are discussed. Four test anomalies were encountered during the full functional test campaign resulting in two minor redesigns, and subsequent reassembly, of the CubeSat. The functional test campaigns highlighted the importance of FlatSat level testing of CubeSats to ensure compatibility of all subsystems prior to assembly and of thorough documentation to diagnose any unexpected behaviour of the hardware efficiently. The functional verification of the EQM proved that the system conformed to its design, verifying 57 mission requirements, and is a crucial step towards the development of the EIRSAT-1 FM.

Analysis of the orbit lifetime of CubeSats in low Earth orbits including periodic variation in drag due to attitude motion

It is estimated that more than 22,300 human-made objects are in orbit around the Earth, with a total mass above 8,400,000 kg. Around 89% of these objects are non-operational and without control, which makes them to be considered orbital debris. These numbers consider only objects with dimensions larger than 10 cm. Besides those numbers, there are also about 2000 operational satellites in orbit nowadays. The space debris represents a hazard to operational satellites and to the space operations. A major concern is that this number is growing, due to new launches and particles generated by collisions. Another important point is that the development of CubeSats has increased exponentially in the last years, increasing the number of objects in space, mainly in the Low Earth Orbits (LEO). Due to the short operational time, CubeSats boost the debris population. One of the requirements for space debris mitigation in LEO is the limitation of the orbital lifetime of the satellites, which needs to be lower than 25 years. However, there are space debris with longer estimated decay time. In LEÓs, the influence of the atmospheric drag is the main orbital perturbation, and is used in maneuvers to increment the losses in the satellite orbital energy, to locate satellites in constellations and to accelerate the decay.The goal of the present research is to study the influence of aerodynamic rotational maneuver in the CubeSat́s orbital lifetime. The rotational axis is orthogonal to the orbital plane of the CubeSat, which generates variations in the ballistic coefficient along the trajectory. The maneuver is proposed to accelerate the decay and to mitigate orbital debris generated by non-operational CubeSats. The panel method is selected to determine the drag coefficient as a function of the flow incident angle and the spinning rate. The pressure distribution is integrated from the satellite faces at hypersonic rarefied flow to calculate the drag coefficient. The mathematical model considers the gravitational potential of the Earth and the deceleration due to drag. To analyze the effects of the rotation during the decay, multiple trajectories were propagated, comparing the results obtained assuming a constant drag coefficient with trajectories where the drag coefficient changes periodically. The initial perigees selected were lower than 400 km of altitude with eccentricities ranging from 0.00 to 0.02. Six values for the angular velocity were applied in the maneuver. The technique of rotating the spacecraft is an interesting solution to increase the orbit decay of a CubeSat without implementing additional de-orbit devices. Significant changes in the decay time are presented due to the increase of the mean drag coefficient calculated by the panel method, when the maneuver is applied, reducing the orbital lifetime, however the results are independent of the angular velocity of the satellite.

Requirements for CubeSat on-board sensors for identification of design and inertial characteristics

In this paper, we discuss requirements formulation for CubeSat on-board sensors characteristics for solving identification problem. The problem is to estimate design and inertial parameters of CubeSat-format nanosatellite using on-board sensor measurements. Identification problem for CubeSats becomes more and more actual every year because CubeSat design becomes more complicated due to complex missions requirements. Modern CubeSats can be equipped with deployable solar panels, propulsion units and different types of transformable structures. This fact makes it necessary to study CubeSats as bodies with variable inertial and design characteristics. In this article the design parameter is fuel level in the CubeSat propulsion system and inertial parameters are inertial coefficients (inertia moments analog). We study requirements formulation for magnetometer and angular rate sensor, as this combination of sensors is the most popular in CubeSat development. The main idea of this paper is to study the sensitivity of measurements to estimated parameters. This sensitivity depends on time and measurement noise, large sensitivity leads to low estimation error. We conducted a numerical study and provide an algorithm which allows to define sensitivity-time-noise dependence for each type of sensors and formulate the requirements for their characteristics.

Software-Defined Radios for CubeSat Applications: A Brief Review and Methodology

CubeSats have revolutionized the way scientists and students perceive space. The majority of CubeSat communication is greatly limited by the AX.25 standards, the small communication window, the available transmission power, and the available bandwidth at VHF/UHF band. As a result, CubeSat radios could only establish low data rate links which restrict the communication capabilities of a CubeSat mission. In this article, a brief review of current software-defined radios (SDRs) used in space missions is given. In addition, two different design methodologies for SDRs for CubeSats are proposed that can be used as a guideline for CubeSat developers. Finally, a high data rate SDR for the UOW CubeSat project is presented that address all the above limitations. The radio operates at S-band, employs quadrature amplitude modulation with a maximum data rate of 60 Mb/s consuming 2.6 Watts in transmit mode and 0.4 Watts in receive mode. The digital signal processing functions and the mode control of the radio are orchestrated by a field programmable gate array system-on-chip. The analog radio frequency domain is accommodated by a 4-layer printed circuit board with dimensions of 92 mm × 88 mm. The goal of the UOW CubeSat radio is an adaptive, on-flight reconfigurable communication platform that will revolutionize the current communication capabilities of the CubeSats and expand nanosatellites mission perspectives.

High-Accuracy and Low-Cost Attitude Measurement Unit of the CubeSat

This paper proposes high-accuracy and reliable attitude measurement methods exclusive for CubeSat with restrictions of low cost, limited space, and low power consumption. The attitude measurement unit is equipped with Commercial Off-The-Shelf (COTS) components including Micro-Electro-Mechanical System (MEMS) gyro and two simultaneously operating star trackers (STR) to enhance the measurement accuracy. The Multiplicative Extended Kalman Filter (MEKF) is used to estimate the attitude of CubeSat, and four kinds of attitude estimation layouts are put forward according to the idea of weighted average of two quaternions from two STR and different architectures of information fusion. Using the proposed methods, the attitude measurement unit can continuously provide accurate and reliable attitude knowledge for attitude control unit when the CubeSat is running in orbit. Numerical simulation is performed to verify the effectiveness of the proposed methods, and it offers a reference for CubeSat developers from the perspective of engineering application.

The Experimental Albertan Satellite #1 (Ex-Alta 1) Cube-Satellite Mission

The Experimental Albertan satellite #1 (Ex-Alta 1) was a three-unit cube satellite (CubeSat) developed at the University of Alberta (UAlberta). As the first ‘made in Alberta’ spacecraft, the Ex-Alta 1 CubeSat was the Canadian contribution to the international QB50 CubeSat constellation mission ( www.qb50.eu ). Ex-Alta 1’s mission incorporated four science objectives, two technical objectives, and one educational outreach objective. These are reviewed in the context of the Ex-Alta 1 mission design, as well as future CubeSat constellation missions that may follow demonstration missions such as Ex-Alta 1 and the experiences of the QB50 project. In support of its objectives, Ex-Alta 1 flew the multi-needle Langmuir probe (m-NLP) QB50 standardized payload, a UAlberta developed miniaturized digital fluxgate magnetometer (DFGM) mounted on a two-element articulated deployable boom, a radiation dosimeter from Teledyne, and an open source onboard computer (OBC) developed at UAlberta. Ex-Alta 1 was released by a NanoRacks deployer from the International Space Station on May 26, 2017, and commanded and controlled from a ground-station developed and operated at UAlberta. Ex-Alta 1 operated continuously throughout its mission until it burned up in the atmosphere on November 14, 2018. The last two-way contact occurred on that day at 07:49:29 UTC, when the spacecraft reported an onboard temperature of 47 °C in eclipse at an altitude of 152 km and which marked the effective end of the mission. This paper provides an overview of the Ex-Alta 1 mission, its development, the spacecraft and mission design, and reports preliminary results from the payload focusing on the DFGM instrument. We also report briefly on related education and outreach activities, including the development and delivery of curriculum-targeted and CubeSat focused classroom sessions inspired by the Ex-Alta 1 mission to school pupils in Alberta.

A Robust Framework for Low-Cost Cubesat Scientific Missions

Cubesats have been effective at lowering the barriers for entry to space for educational institutions and small private players resulting in new and innovative missions and concepts. Novel, potentially powerful, space science projects such as QB50 can now be undertaken with limited budgets and resources. However, the failure rate of Cubesats has been quite high with many failing to establish any communications at all, leaving little opportunity for teams to debug and recover the satellite. Due to the time and cost restrictions faced by Cubesat projects, traditional verification and validation testing processes are not feasible, giving rise to the high failure rate. In this paper, we describe the experience gained during the development, launch and operation of the UNSW-EC0 Cubesat, which was deployed in 2017 as part of the QB50 mission. In particular, we present a robust framework derived from Failure Mitigation Effects and Criticality Analysis (FMECA) for Cubesat testing that is practical for typically resource and time constrained missions. We also describe robustness testing performed during development combined with additional functionality that was built into the satellite, which allowed in-orbit troubleshooting and mission recovery. Following its recovery, UNSW-EC0 was able to perform nominally for the remaining duration of its lifetime. Some preliminary in orbit mission results are also described in the paper. Two UNSW-built Single Event Upset (SEU) resistant experiments as well as the RAMSES payload successfully demonstrated long endurance operations in orbit.

A Development of a Model CubeSat with an Amateur Radio Transceiver for Education on Satellite Communication

A Development of a Model CubeSat with an Amateur Radio Transceiver for Education on Satellite Communication

Development and Application of a 2U CubeSat Ground Model for Space Technology Education

For space technology education, National Institute of Technology (KOSEN) students gathered from across the country worked on group production using a CubeSat ground model equipped with a sensor-selective mission system. After drafting a mission and setting success criteria, each group produced a model CubeSat for the realization of each mission and competed via experiments, analyses, and presentations. In addition to the power supply, communication, and attitude competitions that were conducted last year, a new competition related to the mission system was conducted. For students, this included a model production with a high degree of freedom, and thus they were able to experience manufacturing that is more similar to actual CubeSat development by participating in competitions with assignments.

Structural Dynamics Analysis of 3-U CubeSat

The development of CubeSats has been advanced significantly during the past two decades for both scientific research and industrial purposes. During the manufacturing process, every CubeSat must satisfy various system requirements in which the structural analysis is one of the most vital necessity in order to assure a normal operation of the CubeSat during its working time in space. In the conceptual design phase, structural dynamics is a mandatory step to determine the natural frequencies of individual bodies, the deformation and stress induced at the corresponding vibration modes to prevent structural failure. In this work, IGOSat, a 3-Unit CubeSat, which was developed at the Paris Diderot University is exanimated in term of modal, harmonic response, and random vibration analysis at the time of ground testing as well as the launching phase using ANSYS software. These numerical simulations conducted according to the CubeSat Design Specification and the system requirements of QB50 project. The minimum natural frequency of the CubSat obtained to be 363.17 (Hz), which passed the required frequency of 90 (Hz). Moreover, the Harmonic and Random vibration analyses indicate that the peak response of normal stress, as well as deformation values obtained, are far lesser compared to the yield strength of the frame structure and subsystem materials. Hence, our numerical analysis found that the CubeSat remains intact during the launch environment.

CubeSat Mission: From Design to Operation

The current success rate of CubeSat missions, particularly for first-time developers, may discourage non-profit organizations to start new projects. CubeSat development teams may not be able to dedicate the resources that are necessary to maintain Quality Assurance as it is performed for the reliable conventional satellite projects. This paper discusses the structured life-cycle of a CubeSat project, using as a reference the authors’ recent experience of developing and operating a 2U CubeSat, called qbee50-LTU-OC, as part of the QB50 mission. This paper also provides a critique of some of the current poor practices and methodologies while carrying out CubeSat projects.