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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 ...


Spacecraft Formation Flight On Quasi-Periodic Invariant Tori, Nicola Baresi 2017 University of Colorado at Boulder

Spacecraft Formation Flight On Quasi-Periodic Invariant Tori, Nicola Baresi

Aerospace Engineering Sciences Graduate Theses & Dissertations

Since the successful rendezvous of the Gemini VI and VII spacecraft in 1965, spacecraft formation flying has attracted the interest of many researchers in the field. Yet, existing methodologies do not currently account for the oblateness of a central body when the distance between the satellites exceeds the reach of standard analytical techniques such as Brouwer-Lyddane theory and thereof.

In this dissertation, the problem of designing bounded relative orbits is approached with a dynamical systems theory perspective in order to overcome the limitations imposed by mean-to-osculating orbit element mappings and linearization errors. We find that the dynamics of satellites in ...


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 ...


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 ...


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 ...


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

Phased Array Antenna Investigation For Cubesat Size Satellites, Kien Dang

Morehead State 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.


Formation Flight Of Earth Satellites On Low-Eccentricity Kam Tori, Christopher T. Craft 2016 Air Force Institute of Technology

Formation Flight Of Earth Satellites On Low-Eccentricity Kam Tori, Christopher T. Craft

Theses and Dissertations

The problem of Earth satellite constellation and formation flight is investigated in the context of Kolmogorov-Arnold-Moser (KAM) theory. KAM tori are constructed utilizing Wiesel’s Low-Eccentricity Earth Satellite Theory, allowing numerical representation of the perturbed tori describing Earth orbits acted upon by geopotential perturbations as sets of Fourier series. A maneuvering strategy using the local linearization of the KAM tangent space is developed and applied, demonstrating the ability to maneuver onto and within desired torus surfaces. Constellation and formation design and maintenance on KAM tori are discussed, along with stability and maneuver error concerns. It is shown that placement of ...


Orbital Resonances In The Vinti Solution, Laura M. Duffy 2016 Air Force Institute of Technology

Orbital Resonances In The Vinti Solution, Laura M. Duffy

Theses and Dissertations

The Vinti Solution offers a more accurate model than the two-body problem as an orbital propagator. Unfortunately, the Vinti solution contains small divisors near orbital resonances in the perturbative terms of the Hamiltonian, which lead to inaccurate orbital predictions. One approach to avoid the small divisors is to apply transformation theory. The methodology of this research is to identify the perturbative terms of the Vinti Solution, perform a coordinate transformation, and derive the new equations of motion for the Vinti system near orbital resonances. The analysis in this research focuses on the 2:1 resonance, which includes the Global Positioning ...


Short Duration Missions To Earth Crossing Asteroids, James B. Millar III 2016 Air Force Institute of Technology

Short Duration Missions To Earth Crossing Asteroids, James B. Millar Iii

Theses and Dissertations

My investigation of the Near Earth Object (NEO) catalog has led to identification of numerous short duration, under 40 days, mission opportunities in the future for three different mission types: uncrewed fly-by, uncrewed arrival, and crewed arrival. 2-body propagation techniques were used to model the orbits of various asteroid candidates and the Earth to determine when a close approach would occur. Once the dates were calculated, distance between the bodies was computed to estimate the ∆V to complete the mission. From the mission ∆V values, a possible mission duration was also computed. The values were analyzed to determine the best ...


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 ...


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 ...


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 ...


Comparison Of Line-Peak And Line-Scanning Excitation In Two-Color Laser-Induced-Fluorescence Thermometry Of Oh, Stanislav Kostka, Sukesh Roy, Patrick J. Lakusta, Terrence R. Meyer, Michael W. Renfro, James R. Gord, Richard Branam 2015 University of Connecticut - Storrs

Comparison Of Line-Peak And Line-Scanning Excitation In Two-Color Laser-Induced-Fluorescence Thermometry Of Oh, Stanislav Kostka, Sukesh Roy, Patrick J. Lakusta, Terrence R. Meyer, Michael W. Renfro, James R. Gord, Richard Branam

Terrence R Meyer

Two-line laser-induced-fluorescence (LIF) thermometry is commonly employed to generate instantaneous planar maps of temperature in unsteady flames. The use of line scanning to extract the ratio of integrated intensities is less common because it precludes instantaneous measurements. Recent advances in the energy output of high-speed, ultraviolet, optical parameter oscillators have made possible the rapid scanning of molecular rovibrational transitions and, hence, the potential to extract information on gas-phase temperatures. In the current study, two-line OH LIF thermometry is performed in a wellcalibrated reacting flow for the purpose of comparing the relative accuracy of various line-pair selections from the literature and ...


Leveraging External Sensor Data For Enhanced Space Situational Awareness, Charlie T. Bellows 2015 Air Force Institute of Technology

Leveraging External Sensor Data For Enhanced Space Situational Awareness, Charlie T. Bellows

Theses and Dissertations

Reliable Space Situational Awareness (SSA) is a recognized requirement in the current congested, contested, and competitive environment of space operations. A shortage of available sensors and reliable data sources are some current limiting factors for maintaining SSA. Unfortunately, cost constraints prohibit drastically increasing the sensor inventory. Alternative methods are sought to enhance current SSA, including utilizing non-traditional data sources (external sensors) to perform basic SSA catalog maintenance functions. Astronomical data, for example, routinely collects serendipitous satellite streaks in the course of observing deep space; but tactics, techniques, and procedures designed to glean useful information from those collects have yet to ...


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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