Lunar Ice Cube: Development of a numerical model for attitude control

https://scholarworks.moreheadstate.edu/student_scholarship_posters/1008/thumbnail.jp

Feasibility of Long Range Wide Area Network (LoRaWAN) Technology for LEO Applications

Long Range (LoRa) is a widely used technology for terrestrial communications and is increasingly utilized for space related applications. On the ground, the LoRaWAN protocol allows gateways connected to the internet to serve as transceivers for any eligible end device in range of LoRa modulated signal. Certified gateways are produced by a variety of manufacturers with a range of capabilities, and publicly available networks contain thousands of gateways distributed around the world. Now, we propose to utilize the worldwide network of LoRaWAN gateways as a distributed ground station network capable of significantly reducing delays in link availability for a satellite in LEO. Using a COTS transceiver based on the LoRaWAN protocol, a module will be developed that functions as an end device in network architecture. As a half-duplex communication subsystem it will be capable of sending small packages of selective telemetry and receiving specific commands for essential functions, and will have worldwide compatibility in the range of 868 MHz to 915 MHz. Currently the module is planned to function as the secondary communication subsystem on the Cosmic X-Ray Background NanoSat-3 (CXBN-3) satellite, a 2U CubeSat mission under construction by students at Morehead State University to explore the diffuse emission of hard X-rays in the Cosmic X-Ray Background (CXB). This paper will describe the feasibility of LoRaWAN technology for LEO applications through the evaluation of a LoRaWAN space-based end device, its development based on a COTS transceiver, and validation testing to simulate LEO range by using LoRaWAN commercial gateways

Lunar IceCube: Development of Thermal Management System

Design of a thermal control system for Lunar IceCube faced several challenges. Firstly, components have vastly different requirements for operational temperature range and heat dissipation. Secondly, the spacecraft does not have enough external surface to reject waste heat by traditionally designed thermal control system. Thirdly, integration of components into a single thermal control system represents a challenge due to several factors: namely, thermal interference between components due to high packing density; incompatibility of some components which are made by different vendors. The paper discusses a successful solution of the mentioned above problems. It shows that customization of thermal control systems for each group of components with similar thermal requirements enables successful resolution of thermal challenges

LunarCube: A Deep Space 6U CubeSat with Mission Enabling Ion Propulsion Technology

Busek, in partnership with Morehead State University (MSU), is developing a versatile 6U CubeSat platform nicknamed “LunarCube” that can undertake missions beyond LEO. The spacecraft can host a variety of science payloads, and its mission capability is highlighted by \u3e3km/s of delta-V maneuverability with a groundbreaking ion propulsion system heretofore unavailable to CubeSats. Salient features of this propulsion system include innovative use of solid iodine propellant and a 60W class mini RF ion thruster that is capable of 1.3mN thrust and 3250sec specific impulse (Isp). The primary objective of the LunarCube program is to support a deep space CubeSat mission to the Moon from GEO or a translunar trajectory (such as the SLS/EM-1 drop-off) and carry out a lunar science campaign as a technology demonstration of the platform. A secondary objective is to showcase that much of the spacecraft’s miniaturized avionics and power system can survive the harsh radiation environment. The LunarCube concept, especially its ion propulsion element, has received significant attention from the CubeSat user community targeting near-term lunar flights. In fact, the platform has already morphed into an EM-1 CubeSat mission known as “Lunar IceCube”, selected for flight by NASA’s Next Space Technologies for Exploration Partnerships (NextSTEP) program

NGC 5291: Implications for the Formation of Dwarf Irregular Galaxies

The possible formation and evolution of dwarf irregular galaxies from material derived from perturbed evolved galaxies is addressed via an HI study of a likely example, the peculiar system NGC 5291. This system, located in the western outskirts of the cluster Abell 3574, contains the lenticular galaxy NGC 5291 which is in close proximity to a disturbed companion and is flanked by an extensive complex of numerous knots extending roughly 4\u27 north and 4\u27 south of the galaxy. In an initial optical and radio study, Longmore et al. (1979, MNRAS, 188, 285) showed that these knots have the spectra of vigorous star-forming regions, and suggested that some may in fact be young dwarf irregular galaxies. High resolution 21-cm line observations taken with the VLA are presented here and reveal that the H I distribution associated with this system encompasses not only the entire N-S complex of optical knots, but also forms an incomplete ring or tail that extends approximately 3\u27 to the west. The HI associated with NGC 5291 itself shows a high velocity range; the Seashell is not detected. The formation mechanism for this unusual system is unclear and two models-a large, low-luminosity ram-swept disk, and a ram-swept interaction-are discussed. The HI in the system contains numerous concentrations, mostly along the N-S arc of the star-forming complexes, which generally coincide with one or more optical knots; the larger HI features contain several X 109 M0 of gas. Each of the knots is compared to a set of criteria designed to determine if these objects are bound against their own internal kinetic energy and are tidally stable relative to the host galaxy. An analysis of the properties of the H I concentrations surrounding the optical star-forming complexes indicates that at least the largest of these is a bound system; it also possesses a stellar component. It is suggested that this object is a genuinely young dwarf irregular galaxy that has evolved from the material associated with the system and that this entire complex contains several proto- or young dwarf irregular galaxies in various stages of development. We are therefore witnessing the early evolution of a number of genuinely young galaxies. Given the evident importance of the NGC 5291 system as a \u27\u27nursery\u27\u27 for young galaxies, careful modeling is required if we are to understand this remarkable galaxy

New Moon Explorer Mission Concept

New Moon Explorer (NME) is a smallsat reconnaissance mission concept to explore Earths New Moon, the recently discovered Earth orbital companion asteroid 469219 Kamooalewa (formerly 2016HO3), using solar sail propulsion. NME would determine Kamooalewas spin rate, pole position, shape, structure, mass, density, chemical composition, temperature, thermal inertia, regolith characteristics, and spectral type using onboard instrumentation. If flown, NME would demonstrate multiple enabling technologies, including solar sail propulsion, large-area thin film power generation, and small spacecraft technology tailored for interplanetary space missions. Leveraging the solar sail technology and mission expertise developed by NASA for the Near Earth Asteroid (NEA) Scout mission, affordably learning more about our newest near neighbor is now a possibility. The mission is not yet planned for flight

Nature of and Lessons Learned from Lunar Ice Cube and the First Deep Space Cubesat 'Cluster'

Cubesats operating in deep space face challenges Earth-orbiting cubesats do not. 15 deep space cubesat 'prototypes' will be launched over the next two years including the two MarCO cubesats, the 2018 demonstration of dual communication system at Mars, and the 13 diverse cubesats being deployed from the SLS EM1 mission within the next two years. Three of the EM1 cubesat missions, including the first deep space cubesat 'cluster', will be lunar orbiters with remote sensing instruments for lunar surface/regolith measurements. These include: Lunar Ice Cube, with its 1-4 micron broadband IR spectrometer, BIRCHES, to determine volatile distribution as a function of time of day; Lunar Flashlight, to confirm the presence of surface ice at the lunar poles, utilizing an active source (laser), and looking for absorption features in the returning signal; and LunaH-Map to characterize ice at or below the surface at the poles with a compact neutron spectrometer. In addition, the BIRCHES instrument on Lunar Ice Cube will provide the first demonstration of a microcryocooler (AIM/IRIS) in deep space. Although not originally required to do so, all will be delivering science data to the Planetary Data System, the first formal archiving effort for cubesats. 4 of the 20 recently NASA-sponsored (PSDS3) study groups for deep space cubesat/smallsat mission concepts were lunar mission concepts, most involving 12U cubesats. NASA SIMPLEX 2/SALMON 3 AO will create ongoing opportunities for low-cost missions as 'rides' on government space program or private sector vehicles as these become available

AERO & VISTA: Demonstrating HF Radio Interferometry with Vector Sensors

AERO (Auroral Emission Radio Observer) and VISTA (Vector Interferometry Space Technology using AERO) are recently selected NASA HTIDeS CubeSat missions for terrestrial auroral science and radio interferometric technology demonstration. The AERO and VISTA CubeSats both host vector sensing antenna systems providing advanced electromagnetic capabilities. Together, they will provide the first in-space demonstration of interferometric imaging, beamforming, and nulling using electromagnetic vector sensors at low frequencies (100 kHz –15 MHz). A key goal of the joint missions’ technology demonstration is to validate theoretical sensor performance modeling indicating that interferometric arrays composed of vector sensors will be able to maintain sensitivity even in the presence of terrestrial interference. If validated in flight, this capability would relax the requirement that space-based low frequency interferometers be placed far from the Earth (e.g. lunar orbit), and the closer communications range will significantly increase the data volume returned from space-based radio telescope systems. The two-spacecraft AERO+VISTA mission will address the auroral science goals of AERO (Erickson et al. 2018, SSC18) while adding three additional technology demonstration goals enabled by the second CubeSat, VISTA

New Moon Explorer (NME) Robotic Mission Concept

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