scholarly journals Design, Implementation, and Operation of a Small Satellite Mission to Explore the Space Weather Effects in LEO

Aerospace ◽  
2019 ◽  
Vol 6 (10) ◽  
pp. 108 ◽  
Author(s):  
Isai Fajardo ◽  
Aleksander Lidtke ◽  
Sidi Bendoukha ◽  
Jesus Gonzalez-Llorente ◽  
Rafael Rodríguez ◽  
...  
Keyword(s):  
Space Weather ◽  
Low Cost ◽  
Low Earth Orbit ◽  
Space Environment ◽  
Small Satellite ◽  
Satellite Mission ◽  
Particle Detectors ◽  
Small Satellites ◽  
Environment Effects ◽  
Institute Of Technology

Ten-Koh is a 23.5 kg, low-cost satellite developed to conduct space environment effects research in low-Earth orbit (LEO). Ten-Koh was developed primarily by students of the Kyushu Institute of Technology (Kyutech) and launched on 29 October 2018 on-board HII-A rocket F40, as a piggyback payload of JAXA’s Greenhouse gas Observing Satellite (GOSAT-2). The satellite carries a double Langmuir probe, CMOS-based particle detectors and a Liulin spectrometer as main payloads. This paper reviews the design of the mission, specifies the exact hardware used, and outlines the implementation and operation phases of the project. This work is intended as a reference that other aspiring satellite developers may use to increase their chances of success. Such a reference is expected to be particularly useful to other university teams, which will likely face the same challenges as the Ten-Koh team at Kyutech. Various on-orbit failures of the satellite are also discussed here in order to help avoid them in future small spacecraft. Applicability of small satellites to conduct space-weather research is also illustrated on the Ten-Koh example, which carried out simultaneous measurements with JAXA’s ARASE satellite.

scholarly journals Space Biology Research and Biosensor Technologies: Past, Present, and Future

Biosensors ◽  
2021 ◽  
Vol 11 (2) ◽  
pp. 38
Author(s):  
Ada Kanapskyte ◽  
Elizabeth M. Hawkins ◽  
Lauren C. Liddell ◽  
Shilpa R. Bhardwaj ◽  
Diana Gentry ◽  
...  
Keyword(s):  
Low Cost ◽  
Low Earth Orbit ◽  
Space Environment ◽  
Model Organisms ◽  
Deep Space ◽  
Space Biology ◽  
Small Satellites ◽  
Biological Phenomena ◽  
Space Environments ◽  
The 1960S

In light of future missions beyond low Earth orbit (LEO) and the potential establishment of bases on the Moon and Mars, the effects of the deep space environment on biology need to be examined in order to develop protective countermeasures. Although many biological experiments have been performed in space since the 1960s, most have occurred in LEO and for only short periods of time. These LEO missions have studied many biological phenomena in a variety of model organisms, and have utilized a broad range of technologies. However, given the constraints of the deep space environment, upcoming deep space biological missions will be largely limited to microbial organisms and plant seeds using miniaturized technologies. Small satellites such as CubeSats are capable of querying relevant space environments using novel, miniaturized instruments and biosensors. CubeSats also provide a low-cost alternative to larger, more complex missions, and require minimal crew support, if any. Several have been deployed in LEO, but the next iterations of biological CubeSats will travel beyond LEO. They will utilize biosensors that can better elucidate the effects of the space environment on biology, allowing humanity to return safely to deep space, venturing farther than ever before.

scholarly journals Spectral Correlation for Signal Presence Detection and Frequency Acquisition of Small Satellites

Aerospace ◽  
2021 ◽  
Vol 8 (2) ◽  
pp. 57
Author(s):  
Jonas Hofmann ◽  
Andreas Knopp ◽  
Chad M. Spooner ◽  
Giovanni Minelli ◽  
James Newman
Keyword(s):  
Real World ◽  
Measurement Data ◽  
Low Earth Orbit ◽  
Earth Orbit ◽  
Small Satellite ◽  
Signal To Noise ◽  
Satellite Mission ◽  
Spectral Correlation ◽  
Small Satellites ◽  
Cyclostationary Signal

Challenges in interference-limited satellite detection arising from the low-earth orbit (LEO) and the Industrial, Scientific and Medical (ISM) frequency bands are addressed. In particular, a novel signal presence detector based on cyclostationary signal properties is proposed and analyzed for a low signal-to-noise-plus-interference ratio (SINR) regime. The performance of the proposed detector, which is applicable to various small-satellite scenarios, is evaluated on both simulated and real-world measurement data. This measurement data has been collected from the scientific satellite mission “Picosats Realizing Orbital Propagation Calibrations using Beacon Emitters” (PROPCUBE).

Demonstration of a Solid-State Inflation Balloon Deorbiter

2017 ◽  
Author(s):  
Morgan Roddy ◽  
Haden Hodges ◽  
Larry Roe ◽  
Po-Hao Adam Huang
Keyword(s):  
Solid State ◽  
Aerodynamic Drag ◽  
Low Cost ◽  
Full Range ◽  
Space Environment ◽  
Gas Generator ◽  
Satellite Mission ◽  
Micro Electro Mechanical Systems ◽  
Small Satellites ◽  
Resistive Heater

This paper updates on the recent development of the novel Solid State Inflation Balloon (SSIB), a simple, reliable, low-cost, non-propulsive deorbit mechanism for the full range of small satellites, defined by NASA as less than 180 kg. It aims to focus on the recent demonstration, for the first time, inflation of a ∼10 cm sized balloon in a vacuum chamber. Small satellites typically rely on aerodynamic drag to deorbit within the FAA’s 25 year requirements. The SSIB will enhance aerodynamic drag by inflating a balloon at the end-of-life of a satellite mission. This technology will provide a scalable and non-existing capability, low-cost deorbit, for applications in the full-range of smallsats, from CubeSats to MicroSats. The SSIB system is composed of three major components: a Micro-Electro-Mechanical Systems (MEMS) Solid-State Gas Generator (SSGG) chip, a balloon structure made of thin film compatible with space environment (i.e. Mylar, Kapton, or Teflon), and a sub-system package suitable for spacecraft integration. The SSGG is composed of a 2D addressable array of sodium azide (NaN3) crystals, confined by Su-8 wells, on a glass substrate. Current versions include 2×2 and 8×8 arrays designed for a full range of small satellites. Under each well is a resistive heater and when heated to above 350 °C, the NaN3 spontaneously decomposes to generate N2 gas in time scales on the order of 10 milliseconds. Each well is designed with a typical volume of 10–15 m3 to 10−6 m3 of NaN3 (i.e. 1,500 μm × 1,500 μm × 150 μm on the larger end of the spectrum). The SSIB system is low power (∼1 W per well for less than 10 seconds) and have low mass (∼100 grams, where mass is dominated by the size of the required balloon). Initial simulations have shown that the SSIB with balloons of 1 m2 cross-section can deorbit small satellites from above 1000 km well within 25 years.

scholarly journals Guidance Stabilization of Satellites Using the Geomagnetic Field

2012 ◽  
Vol 2012 ◽  
pp. 1-9
Author(s):  
Francisco Miranda
Keyword(s):  
Geomagnetic Field ◽  
Technological Development ◽  
Low Cost ◽  
Low Earth Orbit ◽  
Earth Orbit ◽  
Small Satellites ◽  
Attitude Stabilization ◽  
Short Period ◽  
Low Earth Orbit Satellite ◽  
Games Theory

In the last years the small satellites have played an important role in the technological development. The attractive short period of design and low cost of them and the capacity to solve problems that are usually considered as problems to big and expensive spacecrafts lead us to study the control problem of these satellites. Active three-axis magnetic attitude stabilization of a low Earth orbit satellite is considered in this work. The control is created by interaction between the magnetic moment generated by magnetorquers mounted on the satellite body and the geomagnetic field. This problem is quite complex and difficult to solve. To overcome this difficulty guidance control is considered, where we use ε-strategies introduced by Pontryagin in the frame of differential games theory. Qualitative analysis and results of numerical simulation are presented.

scholarly journals LATLAUNCH AIR-LAUNCH SYSTEM FOR LOW-COST LAUNCHING OF SMALL SATELLITES INTO LOW EARTH ORBIT

Aviation ◽  
2021 ◽  
Vol 25 (2) ◽  
pp. 73-78
Author(s):  
Aleksandrs Urbahs ◽  
Sergey Kravchenko ◽  
Margarita Urbaha ◽  
Kristine Carjova ◽  
Natalja Panova ◽  
...  
Keyword(s):  
Low Cost ◽  
Low Earth Orbit ◽  
Earth Orbit ◽  
Competitive Advantages ◽  
Characteristic Velocity ◽  
Small Satellites ◽  
Aerial Platform

The paper presents the air-launch system enabling the delivery of small satellites into low Earth orbit. One of the most important advantages of the concept is its cost. Generally, the paper proves that launching a carrier from an aerial platform (a movable launch pad) provides the whole range of competitive advantages. In particular, the total losses during the launch from an aerial platform will reduce by 20–35%, and the characteristic velocity of the maneuver will reduce by 4–7%.

scholarly journals Low-profile tunable radiator for small satellite application

2017 ◽  
Vol 9 (7) ◽  
pp. 1397-1407
Author(s):  
Nevena Šaponjić ◽  
Tomislav Debogović ◽  
Frédéric Bongard ◽  
Pedro Robustillo-Bayon ◽  
Maria Carolina Vigano ◽  
...  
Keyword(s):  
High Frequency ◽  
Low Cost ◽  
Basic Element ◽  
Small Satellite ◽  
High Frequency Band ◽  
Small Satellites ◽  
Low Profile ◽  
Low Mass ◽  
Left And Right ◽  
Vibration Tests

A tunable radiator for space application has been developed to meet stringent requirements in terms of electrical and environmental specifications but also low mass, simple manufacturing and low cost. The element is based on the folded planar inverted F-antenna, with size of one quarter of wavelength. It is mechanically tunable to adjust input impedance for any various positions on the satellite body and possible obstacles and protrusions. Results in terms of radiation pattern, S parameters, shock and vibration tests are presented. The antenna operates in ultra-high frequency band (400 MHz) in linear polarization. It has been designed to act as the basic element for miniaturized multi-function antenna systems on board of small satellites that can operate in three different radiating modes and in both left and right hand circular polarizations.

scholarly journals Developing Technologies for Biological Experiments in Deep Space

Proceedings ◽  
2020 ◽  
Vol 60 (1) ◽  
pp. 28 ◽  
Author(s):  
Elizabeth M. Hawkins ◽  
Ada Kanapskyte ◽  
Sergio R. Santa Maria
Keyword(s):  
Low Cost ◽  
Model Organism ◽  
Low Earth Orbit ◽  
Space Environment ◽  
Model Organisms ◽  
Biological Study ◽  
The Moon ◽  
Deep Space ◽  
Biological Phenomena ◽  
Space Environments

In light of an upcoming series of missions beyond low Earth orbit (LEO) through NASA’s Artemis program and the potential establishment of bases on the Moon and Mars, the effects of the deep space environment on biology need to be examined and protective countermeasures need to be developed. Even though many biological experiments have been performed in space since the 1960s, most of them have occurred in LEO and for only short periods of time. These LEO missions have studied many biological phenomena in a variety of model organisms, as well as utilized a broad range of technologies. Given the constraints of the deep space environment, however, future deep space biological missions will be limited to microbial organisms using miniaturized technologies. Small satellites like CubeSats are capable of querying relevant space environments using novel instruments and biosensors. CubeSats also provide a low-cost alternative to more complex and larger missions, and require minimal crew support, if any. Several have been deployed in LEO, but the next iteration of biological CubeSats will go farther. BioSentinel will be the first interplanetary CubeSat and the first biological study NASA has sent beyond Earth’s magnetosphere in 50 years. BioSentinel is an autonomous free-flyer platform able to support biology and to investigate the effects of radiation on a model organism in interplanetary deep space. The BioSensor payload contained within the free-flyer is also an adaptable instrument that can perform biologically relevant measurements with different microorganisms and in multiple space environments, including the ISS, lunar gateway, and on the surface of the Moon. Nanosatellites like BioSentinel can be used to study the effects of both reduced gravity and space radiation and can house different organisms or biosensors to answer specific scientific questions. Utilizing these biosensors will allow us to better understand the effects of the space environment on biology so humanity may return safely to deep space and venture farther than ever before.

scholarly journals Introduction to Plasma Based Propulsion System: Hall Thrusters

2021 ◽  
Author(s):  
Sukhmander Singh ◽  
Sanjeev Kumar ◽  
Shravan Kumar Meena ◽  
Sujit Kumar Saini
Keyword(s):  
Electric Propulsion ◽  
Low Earth Orbit ◽  
Current Status ◽  
Earth Orbit ◽  
Hall Thrusters ◽  
Small Satellite ◽  
Propulsion Systems ◽  
Small Satellites ◽  
Long Time ◽  
The Cost

Technically, there are two types of propulsion systems namely chemical and electric depending on the sources of the fuel. Electrostatic thrusters are used for launching small satellites in low earth orbit which are capable to provide thrust for long time intervals. These thrusters consume less fuel compared to chemical propulsion systems. Therefore for the cost reduction interests, space scientists are interested to develop thrusters based on electric propulsion technology. This chapter is intended to serve as a general overview of the technology of electric propulsion (EP) and its applications. Plasma based electric propulsion technology used for space missions with regard to the spacecraft station keeping, rephrasing and orbit topping applications. Typical thrusters have a lifespan of 10,000 h and produce thrust of 0.1–1 N. These devices have E→×B→ configurations which is used to confine electrons, increasing the electron residence time and allowing more ionization in the channel. Almost 2500 satellites have been launched into orbit till 2020. For example, the ESA SMART-1 mission (Small Mission for Advanced Research in Technology) used a Hall thruster to escape Earth orbit and reach the moon with a small satellite that weighed 367 kg. These satellites carrying small Hall thrusters for orbital corrections in space as thrust is needed to compensate for various ambient forces including atmospheric drag and radiation pressure. The chapter outlines the electric propulsion thruster systems and technologies and their shortcomings. Moreover, the current status of potential research to improve the electric propulsion systems for small satellite has been discussed.

scholarly journals Nonlinear analysis of thermal behavior for a small satellite in Low Earth Orbit using many-node model

2017 ◽  
Vol 20 (K2) ◽  
pp. 66-76
Author(s):  
Chung Ngoc Pham ◽  
Anh Dong Nguyen ◽  
Hieu Nhu Nguyen
Keyword(s):  
Temperature Limit ◽  
Low Earth Orbit ◽  
Space Environment ◽  
Solar Irradiation ◽  
Solar Array ◽  
Earth Orbit ◽  
Small Satellite ◽  
Simulation Purpose ◽  
Allowable Temperature ◽  
Cover Plates

In this paper, nonlinear thermal responses of a small satellite in Low Earth Orbit (LEO) are analyzed using many-node model. The main elements of primary structure of the satellite include six rectangular cover plates and a solar array linking with satellite's body. These elements can be modeled as different lumped thermal nodes. We use an eight-node model for estimating temperatures at nodal elements i.e. six nodes for cover plates, and two nodes for front and rear surfaces of the solar array. The nodes absorb three major heat energy sources from the space environment consisting of solar irradiation, Earth’s albedo and infrared radiation. The established system of thermal balance equations for nodes is nonlinear and is solved by a numerical algorithm. For simulation purpose, it is assumed that the satellite always remains Earth-pointing attitude during motion. Temperature evolutions of nodes in time are explored in details. The obtained results show that the predictive temperature values of nodes are within the allowable temperature limit range of the satellite.

Space Based Applications for FEA Cathodes (FEAC)

2000 ◽  
Vol 621 ◽  
Author(s):  
B. E. Gilchrist ◽  
U. Michigan ◽  
Ann Arbor ◽  
K. L. Jensen ◽  
A. D. Gallimore ◽  
...  
Keyword(s):  
Low Power ◽  
Electric Propulsion ◽  
Low Cost ◽  
Zirconium Carbide ◽  
Low Earth Orbit ◽  
Space Environment ◽  
Space Applications ◽  
Field Emitter ◽  
Cold Cathodes ◽  
Field Emitter Arrays

ABSTRACTCold cathodes such as field emitter arrays offer the potential to benefit or enable space-based applications of critical commercial, government, or military importance by providing an electron source that is low power, low cost, requires no consumables, potentially robust as well as highly reliable. Applications that would especially benefit from such cold cathodes include low power electric propulsion (EP) thruster technology, electrodyanamic tethers (ED) for propellantless propulsion in low-Earth orbit, and spacecraft negative potential charge control. In controlled environments, field emitter arrays have shown substantial capability, but have failed in harsher environments more typical of space applications. We argue that a combination of localized arc suppression coupled with a low work function, but nevertheless robust, coating such as zirconium carbide would provide the needed ruggedness to withstand energetic ions, oxygen fluxes, and adsorbates typical of a spacecraft environment. We have found that arc-protected and coated FEACs that can operate in a 1-10 microTorr pressure environment with current densities of less than 0.1 Amps/cm^2 and gate voltages between 50-100 Volts, would enable reliable, lowcost devices capable of operating in the required space environment.

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