The Dynamics of Near-Surface Dust on Airless Bodies

The behavior of dust particles under the influence of electrostatic forces has been investigated near the surface of asteroids and the Moon. Dust particle motion on airless bodies has important implications for our understanding of the evolution of these bodies as well as the design of future exploration vehicles. Electrostatically-dominated dust motion has been hypothesized to cause the observed Lunar Horizon Glow and dust ponds on the asteroid Eros. The first major contribution of this thesis is the identification of the electric field strength required in order to electrostatically loft dust particles off the surface of the Moon and asteroids Eros and Itokawa, taking into account the gravity of the body (assumed to be spherical) and the cohesion between dust grains (assumed to have the material properties of lunar regolith). In order to solve for the electric field strength required as a function of dust particle size (assumed to be spherical), we assumed that the charge on the dust particle was given by Gauss\u27 law. It can be seen that it is easiest to launch intermediate-sized particles, rather than the submicron-micron sized particles that have been previously considered due to the dominance of cohesion for small particle sizes. Additionally, the electric field strength required to loft particles is orders of magnitude larger than is likely to be present in situ, unless grain charging is amplified beyond the levels predicted by Gauss\u27 law. The dynamics of dust particles moving in the plasma sheath, independent of the launching mechanism, is of interest since dust particle levitation could significantly change our understanding of the evolution of asteroids as well as pose a hazard to future exploration vehicles. By studying the levitation behavior in a 1D system for a range of particle sizes, a range of central body masses and three different plasma sheath models, we have gained a more detailed understanding of the drivers of the dynamics of the particles. The equilibria about which dust particles are expected to levitate are identified. The equilibria can be generalized to non-spherical grains (as actual lunar and asteroidal grains are highly angular) by presenting the results as a function of the particle\u27s charge-to-weight ratio. Notably, we see that the behavior of levitating dust is driven by the particle size rather than the mass of the central body. Additionally, we can begin to constrain the range of initial launching conditions that result in levitation. Finally, we expand our 1D analysis of dust levitation to a 3D system. Due to the rotation of the central body (particularly with fast rotating asteroids), the plasma environment will be changing radically through a particle\u27s trajectory. Additionally, asteroids have highly non-spherical shapes, thus variations in the body\u27s gravity may significantly influence the trajectory of a given particle. For the case of a spherical asteroid, it can be seen that the time variation of the plasma environment will not cause the particle to reimpact prematurely. We also find that the transverse electric fields present in a 3D model noticeably influence particle trajectories. This thesis presents detailed investigations of electrostatic dust lofting and the dynamics of electrostatic levitation. The results have implications for understanding the evolution of airless bodies, the interpretation of spacecraft observations, and the design of future spacecraft. It is possible to expand the experimental work presented here by testing the influence of grain shape and polydispersity on electrostatic dust lofting. Our theoretical studies of dust levitation in a 3D model could be improved by using an accurate asteroid shape model coupled with a high fidelity plasma simulation

Asteroid Redirect Mission (ARM) Formulation Assessment and Support Team (FAST) Final Report

The Asteroid Redirect Mission (ARM) Formulation Assessment and Support Team (FAST) was a two-month effort, chartered by NASA, to provide timely inputs for mission requirement formulation in support of the Asteroid Redirect Robotic Mission (ARRM) Requirements Closure Technical Interchange Meeting held December 15-16, 2015, to assist in developing an initial list of potential mission investigations, and to provide input on potential hosted payloads and partnerships. The FAST explored several aspects of potential science benefits and knowledge gain from the ARM. Expertise from the science, engineering, and technology communities was represented in exploring lines of inquiry related to key characteristics of the ARRM reference target asteroid (2008 EV5) for engineering design purposes. Specific areas of interest included target origin, spatial distribution and size of boulders, surface geotechnical properties, boulder physical properties, and considerations for boulder handling, crew safety, and containment. In order to increase knowledge gain potential from the mission, opportunities for partnerships and accompanying payloads were also investigated. Potential investigations could be conducted to reduce mission risks and increase knowledge return in the areas of science, planetary defense, asteroid resources and in-situ resource utilization, and capability and technology demonstrations. This report represents the FAST"TM"s final product for the ARM

GTasb3D: A Novel 3D Framework for Modeling Thermal Evolution and Rarefied Flows in Porous Active Small Bodies with Various Shapes

Volatiles in small bodies provide important clues to solar system evolution and are of in-situ-resource-utilization interest. Explicit modeling of small bodies’ global thermophysical process is essential to assess volatiles’ evolution and abundance. Previous numerical studies commonly use a finite difference/volume method, which has limited capability in simulating the interior thermal dynamics of small bodies with realistic shapes. Here we developed a novel 3D framework using the generalized finite difference method for modeling thermal evolution of active small bodies (GTasb3D). By fully solving the energy and mass conservation equations using a mesh-free, Cartesian-coordinate-based method, this framework can evaluate the heat and mass transport in a porous cometary body of various shapes. Several tests and comparisons with previous studies have been carried out to verify this framework's accuracy and efficiency. We show that the timescale to achieve thermal equilibrium and the global temperature distribution are in good agreement with previous theoretical and numerical estimates. The GTasb3D simulations show that ice sublimation mainly occurs near the ice front, and parts of the resulting vapor recondense beneath the ice front. The surface gas density dramatically decreases as the ice retreats. For a 1 km radius object located at 3 au with initially homogeneous dust-ice distribution, the depth to ice at the equator is >∼2 cm after ∼10 yr, assuming that a dust mantle is left behind after ice depletion. At this stage, the global gas production rate is below the gas emission detection capability but is capable of lifting submillimeter-sized dust from the nucleus’s near-subsurface

Entry, Descent, and Landing System Design for the Mars Gravity Biosatellite

This presentation was part of the session : Cross Cutting TechnologiesSixth International Planetary Probe WorkshopMars Gravity Biosatellite is a novel program aimed at providing data on the effects of partial gravity on mammalian physiology. A collaboration between MIT and Georgia Tech, this student-developed free-flyer spacecraft is designed to carry a payload of 15 mice into low Earth orbit, rotating to generate accelerations equivalent to Martian gravity. After 35 days, the payload will re-enter the atmosphere and be recovered for study. Having engaged more than 500 students to date in space life science, systems engineering, and hardware development, the Mars Gravity Biosatellite program offers a unique, interdisciplinary educational opportunity to address a critical challenge in the next steps in human space exploration through the development of a free-flyer platform for partial gravity science with full entry, descent, and landing (EDL) capability. Execution of a full entry, descent, and landing from low Earth orbit is a rare requirement among university-class spacecraft. The EDL design for the Mars Gravity Biosatellite is driven by requirements on the allowable deceleration profile for a payload of de-conditioned mice and maximum allowable recovery time. The 260 kg entry vehicle follows a ballistic trajectory from low Earth orbit to a target recovery site at the Utah Test and Training Range. Reflecting an emphasis on design simplicity and the use of heritage technology, the entry vehicle uses the Discoverer aeroshell geometry and leverages aerodynamic decelerators for mid-air recovery and operations originally developed for the Genesis mission. This paper presents the student-developed EDL design for the Mars Gravity Biosatellite, with emphasis on trajectory design, dispersion analysis, and mechanical design and performance analysis of the thermal protection and parachute systems. Also included is discussion on EDL event sequencing and triggers, contingency operations, the deorbit of the spacecraft bus, plans for further work, and the educational impact of the Mars Gravity Biosatellite program

Gripping characteristics of an electromagnetically activated magnetorheological fluid-based gripper

The design and test of a magnetorheological fluid (MRF)-based universal gripper (MR gripper) are presented in this study. The MR gripper was developed to have a simple design, but with the ability to produce reliable gripping and handling of a wide range of simple objects. The MR gripper design consists of a bladder mounted atop an electromagnet, where the bladder is filled with an MRF, which was formulated to have long-term stable sedimentation stability, that was synthesized using a high viscosity linear polysiloxane (HVLP) carrier fluid with a carbonyl iron particle (CIP) volume fraction of 35%. Two bladders were fabricated: a magnetizable bladder using a magnetorheological elastomer (MRE), and a passive (non-magnetizable) silicone rubber bladder. The holding force and applied (initial compression) force of the MR gripper for a bladder fill volume of 75% were experimentally measured, for both magnetizable and passive bladders, using a servohydraulic material testing machine for a range of objects. The gripping performance of the MR gripper using an MRE bladder was compared to that of the MR gripper using a passive bladder

Geotechnical Properties Of Asteroids Affecting Surface Operations, Mining, And In Situ Resource Utilization Activities

Geotechnical properties of a granular material affect all surface operations from mobility to landing and excavation. As such, significant efforts to study and model these properties are necessary before sending a spacecraft. Lack of knowledge of regolith material properties adversely affected Apollo, Lunokhod, and Mars Exploration Rover missions; hence additional measures need to be undertaken to prevent potential failures or delays of future missions, in particular missions to explore low-gravity asteroidal surfaces. Geotechnical properties of regolith include cohesion and friction angle, which affect material strength. Friction angle is gravity-dependent, whereas cohesion is not. It is therefore much easier to study and model surface regolith on planetary bodies with significant gravity such as the Moon or Mars. If gravity becomes extremely low, for example, on asteroids, cohesive forces start to dominate. This chapter addresses geotechnical properties of asteroid regolith and their implications for safe mission surface operations. The chapter starts with a high-level overview of soil mechanics followed by an overview of asteroid’s regolith from past and current missions. Models related to regolith are presented with specific emphasis on sources of cohesion. Several examples of surface operations are given (landing, boulder retrieval, excavation) to illustrate the effect of various properties on the hardware

Electrostatic dust remediation for future exploration of the Moon

Dust accumulation is one of the critical issues that must be mitigated on in-situ lunar explorations because an in-situ probe is exposed to small dust particles, which are easily attached to it, during its operations. The Lunar Dust Science Definition Team is organized by the Jet Propulsion Lab/California Institute of Technology through NASA's Biological and Physical Sciences Division to define key science questions and assess dust remediation techniques. Here, we assess three electrostatic remediation technology concepts: electrostatic dust shield; surface electrostatically collecting dust, later called attractive surface; and electron beam - plasma jet inducing electrostatic dust lofting from a surface. We qualitatively investigate their maturity by defining six operational factors: Time and location; Amount of dust removal; Contamination of target surfaces; Operation duration; Installation; and Safety. In addition to these techniques, we discuss a supporting system that loads dust particles onto a test article to examine dust removal efficiency. The results show that further development increases the maturity of all the technologies. While laboratory and theoretical demonstrations reported whether each technology robustly work on the Moon, which hosts a complex, heterogeneous dust environment, we find that it is still uncertain if this is the case because none has been tested in the lunar environment. Particularly, operation duration and safety are critical to be addressed further on both laboratory and spaceflight scales