Nanosatellite Platforms Research Articles

Methodology for the design of a nanosatellite telecommunication system in S-Band based on Software for Digital Mission Engineering

Abstract A trend in the development of nanosatellite platforms for technology demonstration has increased in both private industry and academic projects. Communication link design plays a crucial role in the success of space missions, enabling efficient and reliable data transmission between satellites and ground stations. In this context, the use of advanced tools such as System Tool Kit (STK) has gained significant importance by enabling a comprehensive analysis of the technical and operational aspects of the communication link. In an effort to make the future design of the communications subsystem payload on a nanosatellite more efficient and accessible, this paper shows a methodology for the efficient use of STK to perform link analysis.

Instrumentation for Ionized Space Environments: New High Time Resolution Instrumental Modes of Mutual Impedance Experiments

AbstractMutual impedance experiments are in situ plasma diagnostic techniques for the identification of the plasma density and the electron temperature. Different versions of mutual impedance instruments were included in past and present space missions (e.g., Rosetta, BepiColombo, JUICE and Comet Interceptor). New versions are currently being devised to fit the strong mass, volume and power constraints on nanosatellite platforms for future multi‐point space missions. In this study, our goal is to define and validate two new instrumental modes (i.e., chirp and multi‐spectral modes) to improve the time resolution of the experiment with respect to typical mutual impedance instrumental modes (i.e., frequency sweep). Higher time resolution measurements are expected to simplify the integration of mutual impedance experiments onboard nanosatellite platforms by facilitating antenna sharing between different experiments. The investigation is performed both (a) numerically, using a 1D‐1V electrostatic full kinetic Vlasov‐Poisson model and, (b) experimentally, with laboratory tests using a vacuum chamber and a plasma source. From a plasma diagnostic point of view, we find that both the chirp and multi‐spectral modes provide measurements identical to the (reference) frequency sweep mode. From an instrumental point of view, multi‐spectral measurements are faster than frequency sweep measurements but they require larger amounts of onboard computing resources (i.e., larger power consumption). Chirp measurements, instead, outperform frequency sweep measurements both in terms of measurement duration (20 times faster) and onboard processor usage (20% less).

Distributed fusion fault-tolerant attitude estimation scheme for nanosatellite using commercial off-the-shelf sensors

The highly reliable nanosatellite platforms have broad application prospects in the construction of satellite Internet. Obtaining accurate attitude information is crucial to enhance the reliability of nanosatellite platforms. However, the traditional attitude sensors are not suitable for nanosatellite and attitude sensor faults are the main ones in space field. Therefore, sensor fault detection and fault-tolerant processing are essential to improve the reliability of platforms. In this paper, the distributed fusion fault-tolerant attitude estimation (FTAE) problems for nanosatellite with commercial off-the-shelf (COTS) sensors are investigated. Considering the low development cost of nanosatellite platforms, a FTAE scheme using COTS sensors is developed, which can acquire high-precision attitude information and improve the fault tolerance of nanosatellite platforms. Moreover, a novel fault detection method is designed and strict mathematical analysis is applied to fault threshold in FTAE scheme, which can significantly reduce complicated debugging work in engineering application and improve the design efficiency of FTAE scheme. Some case studies are given to illustrate the efficacy of the designed distributed fusion FTAE scheme.

Opportunistic Federation of CubeSat Constellations: A Game-Changing Paradigm Enabling Enhanced IoT Services in the Sky

Internet of Space Things (IoST) is a challenging paradigm, which is currently attracting great interest from the scientific and industrial communities. IoST is based on the integration of the space segment into the global Internet-of-Things (IoT) infrastructure. In the relevant literature, reference is generally made to multiple constellations of nanosatellite platforms, used to enable IoT services on a global scale, including also disadvantaged and poorly infrastructured areas. In this article, we focus on multitenant IoT scenarios, wherein multiple CubeSats constellations are enabled to offer services by exploiting a dynamic federation model. The objective is to efficiently provide services in an IoST scenario by leveraging an effective cooperation strategy originally designed for terrestrial IoT networks, the Mobile-IoT-Federation-as-a-Service (MIFaaS) paradigm. We extend this vision to IoT satellite networks in order to allow a constellation of satellites to effectively execute tasks through a tight cooperative behavior with other CubeSats constellations. The reported performance evaluation studies show that better performance, in terms of percentage of tasks successfully completed, can be achieved through the implementation of the proposed cooperation paradigm.

Feasibility Study of Simultaneous Measurement of Multiple Parameters from a Single Monolithic Scintillator Crystal Using the Geant4 Simulation Toolkit

Abstract A feasibility study for the construction of a minimal multi-parameter detector module from a single monolithic CeBr3 scintillator crystal and a SiPM matrix that is capable of simultaneously measuring deposited energy, position of particle interaction and time characteristics was performed by simulation and direct measurements. The results show that the detector module can operate successfully with characteristics that are close to the limits of the physical detector and that such minimal modules can potentially be used on micro- and nano-satellite platforms .

Ionizing Radiation Sensor for Nanosatellites, Microdrones and Small Unmanned Ground Vehicles

The purpose of this paper is to present an ionizing radiation sensor suitable for nanosatellites, small drones and other types of unmanned vehicles. When implemented on an airborne or ground-based unmanned vehicle the sensor is beneficial in disaster management scenarios such as inspection of buildings and facilities for ionizing radiation contamination and measurements of the ionizing radiation dose. Herein, a design and laboratory tests of the sensor are presented. The instrument is a lightweight module having low power consumption suitable for nanosatellite platforms and for mobile use by having it installed in an unmanned system (airborne or ground-based). For test purposes a 36-rotor drone was developed along with a mobile ground based unmanned vehicle. With all implementations the radiological sensor is directly connected to the main processor unit of the platform. In the case of the drone and ground-based vehicle systems the processor unit is the microcontroller of the autopilot. Experimental results of laboratory measurements of different radiation sources are shown and discussed. The experimental setup demonstrates a few advances related to specific problems encountered in the existing ionizing radiation measurement systems.

Usage of Light Emitting Diodes (LEDs) for improved satellite tracking

With the increasing number of satellite launches, especially in Low Earth Orbit (LEO), optical tracking can offer a convenient enhancement of tracking precision and availability. Spaceborne active illumination devices, such as LED payloads, can offer a significant improvement to optical observations, extending the observability interval to the whole eclipse time and performing optimized flash sequences for identification, orbit determination, attitude reconstruction or low data rate communication. The main features of LED panels for optical tracking mounted on small satellites platforms (and with particular regards to nano-satellite platforms) are outlined in this paper, along with the description of the design drivers. The analysis of the performance is referred to Sun-Synchronous (at 700 km of altitude) and International Space Station (400 km) orbits, while the ground segment and the optical link budget reference design relies on a standard university space debris observation station architecture. The paper also outlines the advantages of using different observation techniques and the variety of flashing patterns. The LEDSAT 1U CubeSat, aiming at demonstrating the effectiveness of an LED-based payload for observation and tracking, is used as a study case for examples of the LED payloads and related operations that are reported and described in this paper.

MeznSat—A 3U CubeSat for Monitoring Greenhouse Gases Using Short Wave Infra-Red Spectrometry: Mission Concept and Analysis

Climate change and global warming are attributed to the increased levels of greenhouse Gases in the atmosphere. Miniature low-cost, lightweight instruments on-board low-cost nanosatellite platforms such as CubeSats could be used to provide precise measurements of greenhouse gases levels. CubeSats, which usually have a narrow field of view, cost a fraction of what more expensive satellites with wide swaths cost. MeznSat is a 3U CubeSat that will carry a shortwave infrared (SWIR) micro-spectrometer as its primary payload, with the aim of deriving greenhouse gas concentrations in the atmosphere by making observations in the 1000–1650 nm wavelength region. The satellite, which is planned for launch in March 2020, is the result of a collaborative project between Khalifa University of Science and Technology (KUST) and the American University of Ras Al-Khaimah (AURAK) with a fund from the United Arab Emirates Space Agency (UAE-SA). The primary payload, Argus 2000, is a miniature, low-cost, space-qualified spectrometer that operates in the shortwave infrared (SWIR) bands. Argus 2000 is a ruggedized unit with a mass of less than 230 g and power consumption of less than 1 W. Also, the Argus 2000 has 0.15 degrees viewing angle and 15 mm fore-optics. The secondary payload will consist of a high definition (HD) camera that will allow post-processing to achieve the high geolocation accuracy required for the SWIR spectrometer data. The RGB combination of visible and SWIR bands setup makes MeznSat a unique CubeSat mission that will generate an interesting dataset to explore atmospheric correction algorithms, which employ SWIR data to process visible channels. This paper describes the mission feasibility, mission analysis, design, and status of MeznSat.

Editors' Note

Scientific exploration of the solar system has traditionally been the realm of large and expensive projects known as primary missions. These missions are usually costly, and they tend to have a long development cycle of massive spacecraft carrying scientific payloads. The maturation of mini- and micro-satellites over the past 40 years has allowed space science to be carried out in lower cost missions. In more recent years, the space community has started to consider using even nanosatellite platforms (such as CubeSats that are typically within a few tens of kilograms) for scientific endeavor in the solar system. Robotic exploration of the solar system using nanosatellites is attractive because of their lower cost, less stringent risk posture, and a shorter development schedule compared to traditional primary science missions. Therefore, it is beneficial to facilitate the development of nanosatellite technologies for deep space exploration by providing an opportunity for a largescale demonstration. Motivated by this, NASA is offering free space launch services on Space Launch System (SLS) to 13 deep space 6U CubeSats, as well as is providing the ground network support if the selected CubeSat missions ask for it. The CubeSats have been chosen competitively as secondary payloads on the SLS launch vehicle carrying the Exploration Mission-1 (EM-1), which will be the first integrated flight test of NASA's Deep Space Exploration Systems including the Orion spacecraft, SLS rocket, and the newly upgraded Exploration Ground Systems at Kennedy Space Center in Cape Canaveral, FL, USA. The 13 EM-1 CubeSats are currently going through the final stages of integration and testing to be ready for launch in late 2020. To help showcase the potential impact of the EM-1 CubeSats, this Special Issue within IEEE AEROSPACE AND ELECTRONIC SYSTEMS MAGAZINE (AESM) is organized to present their science objectives, development story, the challenges faced, and lessons learned by the development teams to share with the community. The three Editors of the Special Issue (SI) would like to thank all the authors from the EM-1 CubeSat teams who managed to make our publication schedule, as well as authors from the EM-1 primary mission team and DSN team. The Editors would also like to thank AESM for offering the publication opportunities to this SI and allowing our SI to come in three parts due to a large volume of papers we have to include. The Part 1 of the SI consists of five papers that are briefly introduced.

AVIS Space Experiment: Testing of Technologies for the Development and Use of Multifunction Pico- and Nanosatellite Platforms

The paper briefly describes the Autonomous Video Information System (AVIS) space experiment conducted as part of the Long-Term Program of Applied Scientific Research and Experiments Planned on the Russian Segment of the International Space Station (ISS RS). The program envisages the development, production, and flight tests of a picosatellite prototype and a sequence of three nanosatellite prototypes with gradually increasing functionality. The main stages include the development of methods and instruments for controlling the separation of the spacecraft, monitoring of their state in an autonomous mode, and experimental testing of the technology of separation, rendezvous, and docking of nanosatellites in orbit. The developed onboard equipment also includes a device for launching pico- and nanosatellites from the ISS RS, manually by an astronaut and by an automatic launcher for nanosatellites from the Progress transport cargo vehicle (TCV), at the command of the ISS or a ground control station. Currently, detailed working design documentation for the spacecraft and the launching device has been created within the experimental program, and work has begun on the production of experimental prototypes.

A neutral wind instrument for nano-satellite platforms.

Here we describe the first neutral wind sensor developed specifically for use on resource limited nano-satellite platforms. The instrument is a next generation redesign of the ram wind sensor flown on the Communications/Navigation Outage Forecasting System satellite for measurements of neutral velocity, temperature, and composition. Results of subsystem tests in vacuum conditions show low-power operation, promising design, and good resolution of measured parameters over the operational pressure and energy ranges expected in the low Earth orbit environment.

Experimental validation of tape springs to be used as thin-walled space structures

With the advent of standardised launch geometries and off-the-shelf payloads, space programs utilising nano-satellite platforms are growing worldwide. Thin-walled, flexible and self-deployable structures are commonly used for antennae, instrument booms or solar panels owing to their lightweight, ideal packaging characteristics and near zero energy consumption. However their behaviour in space, in particular in Low Earth Orbits with continually changing environmental conditions, raises many questions. Accurate numerical models, which are often not available due to the difficulty of experimental testing under 1g-conditions, are needed to answer these questions.In this study, we present on-earth experimental validations, as a starting point to study the response of a tape spring as a representative of thin-walled flexible structures under static and vibrational loading. Material parameters of tape springs in a singly (straight, open cylinder) and a doubly curved design, are compared to each other by combining finite element calculations, with experimental laser vibrometry within a single and multi-stage model updating approach. While the determination of the Young's modulus is unproblematic, the damping is found to be inversely proportional to deployment length. With updated material properties the buckling instability margin is calculated using different slenderness ratios. Results indicate a high sensitivity of thin-walled structures to miniscule perturbations, which makes proper experimental testing a key requirement for stability prediction on thin-elastic space structures. The doubly curved tape spring provides closer agreement with experimental results than a straight tape spring design.

Satellite Applications of Electromagnetic Cloaking

We discuss the possibility to exploit electromagnetic cloaking for enhancing the performances of communication antennas installed on nanosatellite platforms. As a case study, we consider a CubeSTAR system and show that properly designed metasurfaces can be effectively used to minimize the impact of its deployable payload sensors on both radiation and electrical characteristics of the antennas. The results discussed here pave the way to new strategies for the design of extremely compact nanosatellite platforms equipped with multifunctional antennas and sensors.

Use of Mantle Cloaks to Increase Reliability of Satellite-to-Ground Communication Link

In this paper, we show how mantle cloaking can be effectively used in satellite scenarios to reduce the deteriorating effects of the deployable equipment on the link budget between a miniaturized satellite and its ground station. The proposed idea is applied to a nanosatellite scenario and is validated through a simple analytical analysis of its communication link with the ground. The effectiveness of the designed cloaking metasurfaces is evaluated through a proper combination of numerical strategies taking into account the electrically large domain of the problem and the electrically small features of the metasurfaces. This innovative solution can be used to enhance the performances of existing satellite communication systems or to design new extremely compact nanosatellite platforms equipped with multifunctional antennas and sensors.

A versatile retarding potential analyzer for nano-satellite platforms.

The design of the first retarding potential analyzer (RPA) built specifically for use on resource-limited cubesat platforms is described. The size, mass, and power consumption are consistent with the limitations of a nano-satellite, but the performance specifications are commensurate with those of RPAs flown on much larger platforms. The instrument is capable of measuring the ion density, temperature, and the ram component of the ion velocity in the spacecraft reference frame, while also providing estimates of the ion composition. The mechanical and electrical designs are described, as are the operating modes, command and data structure, and timing scheme. Test data obtained using an ion source inside a laboratory vacuum chamber are presented to validate the performance of the new design.

Erratum for: Electrically small printed antenna for applications on cubesat and nano-satellite platforms

Received 15 September 2014 In the above-mentioned article, which appeared in Microwave and Optical Technology Letters, © 2015 Wiley Periodicals, Inc. Microwave Opt Technol Lett 57:891–896, 2015; View this article online at wileyonlinelibrary.com. DOI 10.1002/mop.28989. © 2015 Wiley Periodicals, Inc. Microwave Opt Technol Lett 57:1522, 2015; View this article online at wileyonlinelibrary.com. DOI:10.1002/mop.29128, the author's name was incorrectly shown as A. K. A. N. Volkan. The correct name is listed below: Volkan Akan We regret any confusion that was the result of this error.

Guest Editorial Introduction to the Special Issue on Plasma Propulsion

This Special Issue is dedicated to the physics, technology, and application of plasma propulsion for spacecraft. The field of plasma propulsion includes a broad variety of thrusters that can achieve high propellant exhaust velocity, thereby offering a large mass savings for space vehicles compared to chemical (combustion) rockets. These thrusters are broadly categorized by their propellant acceleration mechanism into three groups: 1) electrothermal; 2) electrostatic; and 3) electromagnetic <xref ref-type="bibr" rid="ref1" xmlns:mml="http://www.w3.org/1998/Math/MathML" xmlns:xlink="http://www.w3.org/1999/xlink">[1]</xref> . Research into plasma propulsion dates back several decades, with a first application in space in 1964 on the Soviet Zond-2, which used an ablative pulsed plasma thruster to control the spacecraft orientation. Today, plasma propulsion is a very rapidly growing area of plasma science and technology, with over 250 operational spacecraft employing plasma propulsion in a variety of applications. Many new plasma thrusters have been recently developed, including numerous successful attempts to scale previously known systems to lower and higher power levels, ranging from a few watts to over 100 kW <xref ref-type="bibr" rid="ref2" xmlns:mml="http://www.w3.org/1998/Math/MathML" xmlns:xlink="http://www.w3.org/1999/xlink">[2]</xref> , <xref ref-type="bibr" rid="ref3" xmlns:mml="http://www.w3.org/1998/Math/MathML" xmlns:xlink="http://www.w3.org/1999/xlink">[3]</xref> . As space exploration shifts toward small and efficient satellites, or micro and nanosatellites <xref ref-type="bibr" rid="ref4" xmlns:mml="http://www.w3.org/1998/Math/MathML" xmlns:xlink="http://www.w3.org/1999/xlink">[4]</xref> , <xref ref-type="bibr" rid="ref5" xmlns:mml="http://www.w3.org/1998/Math/MathML" xmlns:xlink="http://www.w3.org/1999/xlink">[5]</xref> , there are many near-future space missions involving science, military, and commercial payloads utilizing micro and nanosatellite platforms. These platforms require very small levels of thrust for very fine attitude control, high resolution. Earth imaging and astronomy, as well as very precise positioning requirements and other very precise positioning requirements for spacecraft performing formation flying and interferometry missions. Miniaturized propulsion systems are required to satisfy these emerging needs for both the low-thrust missions and the propulsion on small-sized spacecraft.