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Responsible Behavior For Constellations And Clusters, Darren McKnight, Jonathan Rosenblatt, Darren Garber 2018 Integrity Applications, Inc.

Responsible Behavior For Constellations And Clusters, Darren Mcknight, Jonathan Rosenblatt, Darren Garber

Space Traffic Management Conference

Many large constellations are being considered for deployment over the next ten years into low earth orbit (LEO). This paper seeks to quantify the risks that these constellations pose to the debris environment, the risks that the debris environment poses to these constellations, and the risks that these constellations pose to themselves. The three representative constellations examined in detail in this paper are operated (or planned to be operated) by Spire Global, Iridium, and OneWeb. This paper provides a balanced risk analysis including collision risk, operational risk, and non-adherence risk. For perspective, the risk posed by these economically useful constellations ...


Solar Eclipse Induced Atmospheric Turbulence Effects On High Altitude Balloons, Fnu Anamika, Denise Buckner, Peter Henson, Jennifer Fowler, Nanette Valentour 2017 University of North Dakota

Solar Eclipse Induced Atmospheric Turbulence Effects On High Altitude Balloons, Fnu Anamika, Denise Buckner, Peter Henson, Jennifer Fowler, Nanette Valentour

2017 Academic High Altitude Conference

The North Dakota Atmospheric Education Student Initiated Research (ND-AESIR) team launched a balloon during the total solar eclipse in Rexburg, Idaho. After the umbra’s passage, the balloon experienced unexpectedly high levels of atmospheric turbulence. Video footage taken from the payload displays the conditions, and analysis of flight path data models created from the iridium GPS confirm that unusually violent turbulence occurred. These forces caused the key rings holding the bottom of the parachute to the payload train to rip open; the balloon and parachute flew away and the payloads free fell to the surface from an altitude of 68 ...


Mass Estimation Through Fusion Of Astrometric And Photometric Data Collection With Application To High Area-To-Mass Ratio Objects, Matthew Richardson 2017 California Polytechnic State University, San Luis Obispo

Mass Estimation Through Fusion Of Astrometric And Photometric Data Collection With Application To High Area-To-Mass Ratio Objects, Matthew Richardson

Master's Theses and Project Reports

This thesis work presents the formulation for a tool developed in MATLAB to determine the mass of a space object from the fusion of astrometric and photometric data. The application for such a tool is to better model the mass estimation method used for high area-to-mass ratio objects found in high altitude orbit regimes. Typically, the effect of solar radiation pressure is examined with angles observations to deduce area-to-mass ratio calculations for space objects since the area-to-mass ratio can greatly affect its orbital dynamics. On the other hand, photometric data is not sensitive to mass but is a function of ...


The Effect Of Surface Materials And Morphology On Wingsuit Aerodynamics, Timothy Allen Sestak 2017 Embry-Riddle Aeronautical University

The Effect Of Surface Materials And Morphology On Wingsuit Aerodynamics, Timothy Allen Sestak

Dissertations and Theses

This study examines the aerodynamic effects of the materials, textiles, and morphologies currently used in wingsuit design and construction. The experiment was a low-speed wind tunnel investigation using a rigid wing with an aspect ratio of 2, a NACA 4418 airfoil cross section and a smooth, polished painted surface as a baseline. The baseline wing was modified by covering the upper and lower surfaces with various textiles currently used in wingsuit construction. This study is the first step in continued research to design and build a wingsuit with superior glide performance compared to current designs. Surface textures and features on ...


Enceladus Sample Return Mission, Braxton Brakefield, Rekesh Ali, Andrew Bishop, Shelby Honaker, David Taylor 2017 University of Tennessee, Knoxville

Enceladus Sample Return Mission, Braxton Brakefield, Rekesh Ali, Andrew Bishop, Shelby Honaker, David Taylor

University of Tennessee Honors Thesis Projects

No abstract provided.


Orbital Determination Feasibility Of Leo Nanosatellites Using Small Aperture Telescopes, Michael R. Strange 2017 California Polytechnic State University - San Luis Obispo

Orbital Determination Feasibility Of Leo Nanosatellites Using Small Aperture Telescopes, Michael R. Strange

Master's Theses and Project Reports

This thesis is directed toward the feasibility of observing satellites on the nano scale and determining an accurate propagated orbit using a Meade LX600-ACF 14” diameter aperture telescope currently located on the California Polytechnic State University campus. The optical telescope is fitted with an f/6.3 focal reducer, SBIG ST-10XME CCD camera and Optec TCF-S Focuser. This instrumentation allowed for a 22’ X 15’ arcminute FOV in order to accurately image passing LEO satellites. Through the use of the Double-r and Gauss Initial Orbit Determination methods as well as Least Squared Differential Correction and Extended Kalman Filter Orbit Determination ...


The Collisional Evolution Of Orbital Debris In Geopotential Wells And Disposal Orbits, Benjamin Polzine 2017 California Polytechnic State University, San Luis Obispo

The Collisional Evolution Of Orbital Debris In Geopotential Wells And Disposal Orbits, Benjamin Polzine

Master's Theses and Project Reports

This thesis investigates the orbital debris evolution in the geosynchronous disposal orbit regime and within geosynchronous orbits effected by the geopotential wells. A propagator is developed for the accurate simulation of GEO specific orbits and the required perturbations are determined and described. Collisions are then simulated in the selected regimes using a low velocity breakup model derived from the NASA EVOLVE breakup model. The simulations described in this thesis consider a set of perturbations including the geopotential, solar and lunar gravity, and solar radiation pressure forces. This thesis is based on a prior paper and additionally seeks to address an ...


Supporting Autonomous Navigation With Flash Lidar Images In Proximity To Small Celestial Bodies, Ann Brown Dietrich 2017 University of Colorado at Boulder

Supporting Autonomous Navigation With Flash Lidar Images In Proximity To Small Celestial Bodies, Ann Brown Dietrich

Aerospace Engineering Sciences Graduate Theses & Dissertations

Spacecraft navigation in proximity to small celestial bodies, such as asteroids and comets, is challenging due to their complex dynamical environment and the lag in communications from Earth to the spacecraft. Increasing autonomous spacecraft navigation reduces the burden of ground-based planning and modeling, and enables insightful mission profiles. The state-of-the-art of relative spacecraft navigation uses optical images, requires an iterative procedure, and currently must be performed on the ground. A flash lidar instrument instantaneously returns a 3D elevation map of its target and shows promise for advancing autonomous spacecraft navigation. Using this instrument as a relative measurement source for navigation ...


Cubesat Adcs Validation And Testing Apparatus, Jacob Stevens 2016 Western Michigan University

Cubesat Adcs Validation And Testing Apparatus, Jacob Stevens

Honors Theses

The WALI team at Western Michigan University requested a test environment to validate their CubeSat’s de-tumbling control system and hardware. The test environment required a Helmholtz cage and spherical air bearing. The Helmholtz cage provides an adjustable magnetic field to simulate low earth orbit; the spherical air bearing simulates the friction free environment the CubeSat will experience in space. In conjunction, the two components create an adjustable system that simulates a satellite in low earth orbit.


A Novel Approach For Controlled Deorbiting And Reentry Of Small Spacecraft, Larry H. Fineberg, Justin Treptow, Timothy Bass, Scott Clark, Yusef Johnson, Bradley Poffenberger 2016 NASA Launch Services Program

A Novel Approach For Controlled Deorbiting And Reentry Of Small Spacecraft, Larry H. Fineberg, Justin Treptow, Timothy Bass, Scott Clark, Yusef Johnson, Bradley Poffenberger

Space Traffic Management Conference

No abstract provided.


Autonomous Formation Flying And Proximity Operations Using Differential Drag On The Mars Atmosphere, Andres Eduardo Villa 2016 California Polytechnic State University, San Luis Obispo

Autonomous Formation Flying And Proximity Operations Using Differential Drag On The Mars Atmosphere, Andres Eduardo Villa

Master's Theses and Project Reports

Due to mass and volume constraints on planetary missions, the development of control techniques that do not require fuel are of big interest. For those planets that have a dense enough atmosphere, aerodynamic drag can play an important role. The use of atmospheric differential drag for formation keeping was first proposed by Carolina L. Leonard in 1986, and has been proven to work in Earth atmosphere by many missions. Moreover, atmospheric drag has been used in the Mars atmosphere as aerobraking technique to decelerate landing vehicles, and to circularize the orbit of the spacecraft. Still, no literature was available related ...


A Solution To The Circular Restricted N Body Problem In Planetary Systems, Jay R. Iuliano 2016 California Polytechnic State University – San Luis Obispo

A Solution To The Circular Restricted N Body Problem In Planetary Systems, Jay R. Iuliano

Master's Theses and Project Reports

This thesis is a brief look at a new solution to a problem that has been approached in many different ways in the past - the N body problem. By focusing on planetary systems, satellite dynamics can be modeled in a fashion similar to the Circular Restricted Three Body Problem (CR3BP) with the Circular Restricted N Body Problem (CRNBP). It was found that this new formulation of the dynamics can then utilize the tools created from all the research into the CR3BP to reassess the possibility of different complex trajectories in systems where there are more than just two large gravitational ...


An Autonomous System For Satellite Debris Avoidance, Michael Hlas, Jeremy Straub 2016 Selected Works

An Autonomous System For Satellite Debris Avoidance, Michael Hlas, Jeremy Straub

Jeremy Straub

Since the launch of Sputnik in 1958, thousands of satellites have been launched by governments and commercial entities for a wide range of purposes. Once a satellite has completed its primary mission, most opera-tors de-orbit or move the satellite into a graveyard orbit as to avoid collisions with active satellites. However, some spacecraft do not have any residual propellant. Other satellites suffer failures and become hazards themselves. Non-operational satellites in orbit have be-come an increasing collision risk for operational satellites and this problem will only become worse as the number of satellites launched every year increases. Although finding ways to ...


Development Of A Database For Rapid Approximation Of Spacecraft Radiation Dose During Jupiter Flyby, Sarah Gilbert Stewart 2016 University of Tennessee - Knoxville

Development Of A Database For Rapid Approximation Of Spacecraft Radiation Dose During Jupiter Flyby, Sarah Gilbert Stewart

Masters Theses

Interplanetary and deep space missions greatly benefit from the utilization of gravitational assists to reach their final destinations. By closely “swinging by” a planet, a spacecraft can gain or lose velocity or change directions without requiring any expenditure of propulsion. In today’s budget-driven design environment, gravity assist flybys reduce the need for on-board fuel and propulsion systems, thereby reducing overall cost, increasing payload and mission capacity, increasing mission life, and decreasing travel time. It is expected that many future missions will also be designed to swing by Jupiter in order to utilize a gravity assist. However, there is a ...


Improved Modeling Of Atmospheric Entry For Meteors With Nose Radii Between 5cm And 10m, Jakob Dale Brisby 2016 University of Tennessee - Knoxville

Improved Modeling Of Atmospheric Entry For Meteors With Nose Radii Between 5cm And 10m, Jakob Dale Brisby

Masters Theses

Atmospheric entry studies typically look closely at the peak heating rate that a body encounters during its trajectory. This is an extremely important phenomenon to study because it allows engineers to determine if a trajectory is possible with given materials and craft design specifications. It also allows designers to choose what type of method will be used for mitigating the enormous heat fluxes during entry. In general, it is accepted that during the super-sonic flight regime the body will continue to be heated and an ablative heat shield often is used to deal with these heating processes. The theory outlined ...


Phased Array Antenna Investigation For Cubesat Size Satellites, Kien Dang 2016 Morehead State University

Phased Array Antenna Investigation For Cubesat Size Satellites, Kien Dang

Theses and Dissertations

A Thesis Presented to the Faculty of the College of Science Morehead State University in Partial Fulfillment of the Requirements for the Degree Master of Science by Kien Dang on April 18, 2016.


Autonomous Mission Design In Extreme Orbit Environments, David Allen Surovik 2016 University of Colorado at Boulder

Autonomous Mission Design In Extreme Orbit Environments, David Allen Surovik

Aerospace Engineering Sciences Graduate Theses & Dissertations

An algorithm for autonomous online mission design at asteroids, comets, and small moons is developed to meet the novel challenges of their complex non-Keplerian orbit environments, which render traditional methods inapplicable. The core concept of abstract reachability analysis, in which a set of impulsive maneuvering options is mapped onto a space of high-level mission outcomes, is applied to enable goal-oriented decision-making with robustness to uncertainty. These nuanced analyses are efficiently computed by utilizing a heuristic-based adaptive sampling scheme that either maximizes an objective function for autonomous planning or resolves details of interest for preliminary analysis and general study. Illustrative examples ...


Spacecraft Trajectory Optimization Suite (Stops): Optimization Of Multiple Gravity Assist Spacecraft Trajectories Using Modern Optimization Techniques, Timothy J. Fitzgerald 2015 California Polytechnic State University, San Luis Obispo

Spacecraft Trajectory Optimization Suite (Stops): Optimization Of Multiple Gravity Assist Spacecraft Trajectories Using Modern Optimization Techniques, Timothy J. Fitzgerald

Master's Theses and Project Reports

In trajectory optimization, a common objective is to minimize propellant mass via multiple gravity assist maneuvers (MGAs). Some computer programs have been developed to analyze MGA trajectories. One of these programs, Parallel Global Multiobjective Optimization (PaGMO), uses an interesting technique known as the Island Model Paradigm. This work provides the community with a MATLAB optimizer, STOpS, that utilizes this same Island Model Paradigm with five different optimization algorithms. STOpS allows optimization of a weighted combination of many parameters. This work contains a study on optimization algorithm performance and how each algorithm is affected by its available settings.

STOpS successfully found ...


Computation Of Hypersonic Flows With Lateral Jets Using K-Ω Turbulence Model, Spatika Dasharati Iyengar 2015 Embry-Riddle Aeronautical University

Computation Of Hypersonic Flows With Lateral Jets Using K-Ω Turbulence Model, Spatika Dasharati Iyengar

Dissertations and Theses

Thermal Protection systems (TPS) are used as shields in space vehicles which encounter high heat and temperatures at the reentry altitudes. Among them, the cooling techniques and the ablative coatings are most popular. However, they have their own weight limitations. In the recent decade, another classification of TPS called the Non-Ablative Thermal Protection systems (NaTPS) have gained significance. The spike-lateral jet method is an NaTPS concept proposed for drag and heat flux reduction in hypersonic nose cones. Numerical simulations are conducted to analyze the effectiveness of spike-lateral jet concept at re-entry altitudes. The spike attached to the hemispherical nose has ...


Earth Magnetosphere Model Investigations For Coupled Orbit-Attitude Space Debris Perturbations, Eiji Shibata, Carolin Frueh Dr. 2015 Purdue University

Earth Magnetosphere Model Investigations For Coupled Orbit-Attitude Space Debris Perturbations, Eiji Shibata, Carolin Frueh Dr.

The Summer Undergraduate Research Fellowship (SURF) Symposium

As more objects are placed into orbit, collisions become increasingly more likely, leading to a so-called Kessler Syndrome: collisions between existing debris creates more debris, causing a cascading effect of larger amounts of debris being put into orbit, even in the absence of launches, making future space fairing difficult or impossible. Natural forces influence the orbit and attitude of uncontrolled debris objects. The natural plasma environment can lead to space object charging. The subsequent orbital movement in the geomagnetosphere induces Lorentz forces that act both on the orbit and attitude of the space object. Those forces have not been investigated ...


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