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Suborbital Spaceflight: A Student Team’S Plan To Send A Rocket To Space, Bryce Chanes, William Carpenter, Julio Benavides, Matthew Haslam, Brenda Haven 2015 Embry-Riddle Aeronautical University - Prescott

Suborbital Spaceflight: A Student Team’S Plan To Send A Rocket To Space, Bryce Chanes, William Carpenter, Julio Benavides, Matthew Haslam, Brenda Haven

Aviation / Aeronautics / Aerospace International Research Conference

The Eagle Space Flight Team was created with the goal of becoming the first undergraduate team to design, build, and launch a rocket capable of suborbital spaceflight. In order to achieve this goal, the team will have to design a rocket capable of atmospheric flight at speeds over Mach 5 and launch it on one of the largest amateur rocket motors ever made. Over the next three years, the team will progress towards accomplishing this feat through a series of incremental test flights. Before the space flight, the team will build three sub-scale rockets designed to reach altitudes of 30 ...


Performance Quantification Of Heliogyro Solar Sails Using Structural, Attitude, And Orbital Dynamics And Control Analysis, Daniel Vernon Guerrant 2015 University of Colorado Boulder

Performance Quantification Of Heliogyro Solar Sails Using Structural, Attitude, And Orbital Dynamics And Control Analysis, Daniel Vernon Guerrant

Aerospace Engineering Sciences Graduate Theses & Dissertations

Solar sails enable or enhance exploration of a variety of destinations both within and without the solar system. The heliogyro solar sail architecture divides the sail into blades spun about a central hub and centrifugally stiffened. The resulting structural mass savings can often double acceleration verses kite-type square sails of the same mass. Pitching the blades collectively and cyclically, similar to a helicopter, creates attitude control moments and vectors thrust. The principal hurdle preventing heliogyros' implementation is the uncertainty in their dynamics. This thesis investigates attitude, orbital and structural control using a combination of analytical studies and simulations. Furthermore, it ...


Dissipative Wave Propagation In Phononic Crystals And Metamaterials: Models And Analysis, Michael Joseph Frazier 2015 University of Colorado Boulder

Dissipative Wave Propagation In Phononic Crystals And Metamaterials: Models And Analysis, Michael Joseph Frazier

Aerospace Engineering Sciences Graduate Theses & Dissertations

Through deliberate material and geometrical design of the internal structure, phononic crystals and metamaterials, collectively, phononic materials, elicit fundamental wave phenomena pertaining to acoustic/elastic systems. This unique ability among classical materials and composites has immediate engineering applications including vibration control in structures. Moreover, ongoing research has been directed toward technological improvements in communications, energy harvesting, and acoustic imaging as well as the proposal of new devices for acoustic cloaking, nondestructive super-resolution imaging, and even flow control. Periodicity, emerging from the spatial repetition of a representative structural element, the unit cell, is a characteristic feature of phononic materials and makes ...


A Pareto-Frontier Analysis Of Performance Trends For Small Regional Coverage Leo Constellation Systems, Christopher Alan Hinds 2014 California Polytechnic State University - San Luis Obispo

A Pareto-Frontier Analysis Of Performance Trends For Small Regional Coverage Leo Constellation Systems, Christopher Alan Hinds

Master's Theses and Project Reports

As satellites become smaller, cheaper, and quicker to manufacture, constellation systems will be an increasingly attractive means of meeting mission objectives. Optimizing satellite constellation geometries is therefore a topic of considerable interest. As constellation systems become more achievable, providing coverage to specific regions of the Earth will become more common place. Small countries or companies that are currently unable to afford large and expensive constellation systems will now, or in the near future, be able to afford their own constellation systems to meet their individual requirements for small coverage regions.

The focus of this thesis was to optimize constellation geometries ...


Trajectory Design In The Spatial Circular Restricted Three-Body Problem Exploiting Higher-Dimensional Poincare Maps, Amanda F. Haapala 2014 Purdue University

Trajectory Design In The Spatial Circular Restricted Three-Body Problem Exploiting Higher-Dimensional Poincare Maps, Amanda F. Haapala

Open Access Dissertations

In this investigation, the role of higher-dimensional Poincaré maps in facilitating trajectory design is explored for a variety of applications. To begin, existing strategies to implement Poincaré maps for trajectory design applications in the spatial CR3BP are evaluated. New applications for these strategies are explored, including an analysis of the natural motion of Jupiter-family comets that experience temporary capture about Jupiter, and the search for periodic orbits in the vicinity of the primary bodies in the spatial problem. Because current strategies to represent higher-dimensional maps, generally, lead to a loss of information, new approaches to represent all information contained in ...


Trajectory Optimization For A Misson To The Trojan Asteroids, Shivaji Senapati Gadsing 2014 Western Michigan University

Trajectory Optimization For A Misson To The Trojan Asteroids, Shivaji Senapati Gadsing

Master's Theses

The problem of finding a minimum-fuel trajectory for a mission to the Jovian Trojan asteroids is considered. The problem is formulated as a modified traveling salesman problem. Two different types of algorithms such as an exhaustive search algorithm and a serial rendezvous search algorithm are developed. The General Mission Analysis Tool (GMAT) is employed for finding optimum trajectories with minimal fuel consumption. The selection of a minimum-fuel mission trajectory, and the associated target asteroids, will be a key factor in determining feasibility and scientific value of a Trojan tour and rendezvous mission.

The transfer trajectory followed by a spacecraft between ...


Design And Analysis Of An Attitude Determination And Control Subsystem (Adcs) For Afit's 6u Standard Bus, Erin R. Dannemeyer 2014 Air Force Institute of Technology

Design And Analysis Of An Attitude Determination And Control Subsystem (Adcs) For Afit's 6u Standard Bus, Erin R. Dannemeyer

Theses and Dissertations

The design and testing of AFIT's 6U Attitude Determination and Control Subsystem (ADCS) are explored to establish 3-axis attitude control. The development of AFIT's 6U CubeSat standard bus is an on-going research effort designed to create in-house CubeSat bus components and software. The 6U chassis measures approximately 11 x 24 x 37 cu cm and can have a mass up to 12 kg. The larger bus size (as compared to the more common 3U CubeSat) allows for increased power capabilities and potential to host multiple or larger payloads. Individual ADCS hardware components were either commercially purchased or built ...


An Investigation Of Alternate Transfer Strategies To The Sun-Earth Triangular Lagrangian Points, Brian Wesley Lathrop 2014 University of Colorado Boulder

An Investigation Of Alternate Transfer Strategies To The Sun-Earth Triangular Lagrangian Points, Brian Wesley Lathrop

Aerospace Engineering Sciences Graduate Theses & Dissertations

Techniques for low energy transfers have been applied to constructing trajectories to various locations in the solar system. Previous techniques have concentrated on orbit matching trajectory maneuvers and two-body transfers. This research investigates several strategies for low energy transfers that can be utilized to intersect desirable objects or locate to different equilibrium regions in the solar system. The principle tools utilized in this investigation stem from the three-body problem and the development of Lagrangian equilibrium points, periodic orbits and invariant manifolds. Another principle tool is the use of low thrust propulsion to develop low energy transfer trajectories utilizing long duration ...


Analysis Of An Inflatable Gossamer Device To Efficiently De-Orbit Cubesats, Robert A. Hawkins Jr. 2013 California Polytechnic State University, San Luis Obispo

Analysis Of An Inflatable Gossamer Device To Efficiently De-Orbit Cubesats, Robert A. Hawkins Jr.

Master's Theses and Project Reports

There is an increased need for spacecraft to quickly and efficiently de-orbit themselves as the amount of debris in orbit around Earth grows. Defunct spacecraft pose a significant threat to the LEO environment due to their risk of fragmentation. If these spacecraft are de-orbited at the end of their useful life their risk to future spacecraft is greatly lessened. A proposed method of efficiently de-orbiting spacecraft is to use an inflatable thin-film envelope to increase the body's area to mass ratio and thusly shortening its orbital lifetime. The system and analysis presented in this project is sized for use ...


Investigation Into The Mitigation Of The Effects Of Uncertain Optical Degradation On An Interplanetary Solar Sail Mission Using A Single Model Update, Jordan Smiroldo 2013 California Polytechnic State University - San Luis Obispo

Investigation Into The Mitigation Of The Effects Of Uncertain Optical Degradation On An Interplanetary Solar Sail Mission Using A Single Model Update, Jordan Smiroldo

Master's Theses and Project Reports

The renewed academic interest in using solar sails as a source of spacecraft propulsion has been accompanied by a recent fervor of investigations into non-ideal and off-nominal sail performance considerations. One of the most influential considerations, uncertain optical degradation, has been shown to present significant trajectory design difficulties. This paper investigates the potential of using a mid-course degradation model update to mitigate the risk of missing the target destination in a sample 300 day Earth-Venus trajectory. Using a range of potential degradation profiles, it is shown that correcting in the first half of the mission is highly likely to result ...


Light Curve Generation For Satellites In Geostationary Orbits, Kimberly Andersen 2013 California Polytechnic State University, San Luis Obispo

Light Curve Generation For Satellites In Geostationary Orbits, Kimberly Andersen

Aerospace Engineering

This research were conducted at California Polytechnic State University San Luis Obispo throughout the Winter, Spring, and Fall quarters of 2013. The data presented in this paper was taken on the night of October 20, 2013 at the Cal Poly San Luis Obispo Astronomical Observatory and was reduced using IRAF software available on campus. This report describes the results of an observation of two bright XM geostationary satellites and the steps taken to get to those results. The average magnitude values of the XM-1 and XM-2 satellites were 13.753±0.007 and 14.015±0.007 respectively. The magnitude ...


Attitude Estimation For A Gravity Gradient Momentum Biased Nanosatellite, Arash Mehrparvar 2013 California Polytechnic State University, San Luis Obispo

Attitude Estimation For A Gravity Gradient Momentum Biased Nanosatellite, Arash Mehrparvar

Master's Theses and Project Reports

Attitude determination and estimation algorithms are developed and implemented in simulation for the Exocube satellite currently under development by PolySat at Cal Poly. A mission requirement of ±5˚ of attitude knowledge has been flowed down from the NASA Goddard developed payload, and this requirement is to be met with a basic sensor suite and the appropriate algorithms. The algorithms selected in this work are TRIAD and an Extended Kalman Filter, both of which are placed in a simulation structure along with models for orbit propagation, spacecraft kinematics and dynamics, and sensor and reference vector models. Errors inherent from sensors, orbit ...


A Study Of The Collisional Evolution Of Orbital Debris In Geopotential Wells And Geo Disposal Orbits, Christina R. Diaz 2013 California Polytechnic State University, San Luis Obispo

A Study Of The Collisional Evolution Of Orbital Debris In Geopotential Wells And Geo Disposal Orbits, Christina R. Diaz

Master's Theses and Project Reports

This thesis will present the effects of the orbital debris evolution in two key areas: the geosynchronous disposal orbit regime known as “graveyard” and the two geopotential wells found in 105◦ W and 75◦ E longitude bins. After developing a GEO specific orbit propagator for NASA Johnson Space Center’s Orbital Debris Of- fice, collisions were simulated throughout these regimes using a low velocity breakup model. This model considered the effects of perturbations particularly non-spherical Earth effects (specifically sectorial and zonal harmonics), lunar effects, third body effects and solar radiation pressure effects. The results show that CDPROP does well in ...


Non-Destructive Testing (Ndt) By Laser Shearography And Fringe Projection, Xiaoran Chen, Morteza Khaleghi, Ivo Dobrev, Cosme Furlong 2013 Selected Works

Non-Destructive Testing (Ndt) By Laser Shearography And Fringe Projection, Xiaoran Chen, Morteza Khaleghi, Ivo Dobrev, Cosme Furlong

Morteza Khaleghi

Non-destructive testing (NDT) is critical to many precision industries because it can provide important information about the structural health of critical components and systems. In addition, NDT can also identify situations that could potentially lead to critical failures. Specifically, NDT by optical methods have become popular because of their non-contact and non-invasive nature. Shearography is a high-resolution optical NDT method for identification and characterization of structural defects in components and has gained wide acceptance over the last decade; however, as a drawback, shearography cannot locate the position of defects in 3D. To overcome this limitation, we are combining shearography with ...


Feasibility Of Cubesat Formation Flight Using Rotation To Achieve Differential Drag, Skyler M. Shuford 2013 California Polytechnic State University - San Luis Obispo

Feasibility Of Cubesat Formation Flight Using Rotation To Achieve Differential Drag, Skyler M. Shuford

Aerospace Engineering

This paper presents the results of a study conducted to understand the feasibility of CubeSat formation flight. The mechanism for separation and formation studied was differential drag, achieved by rotating the CubeSats to give them different cross-sectional areas. Intuitively, lower altitude orbits provide much higher separation effects. Although the most influential orbital effects occur with maximum and minimum cross-sectional areas, an attitude-controlled and a tumbling CubeSat may provide enough differential drag to meet separation requirements of a mission. Formation flight is possible, but due to the non-linearity of the system, gain scheduling may be the most effective method of long ...


Characterization Of The Effects Of A Sun-Synchronous Orbit Slot Architecture On The Earth's Orbital Debris Environment, Connor David Noyes 2013 California Polytechnic State University - San Luis Obispo

Characterization Of The Effects Of A Sun-Synchronous Orbit Slot Architecture On The Earth's Orbital Debris Environment, Connor David Noyes

Master's Theses and Project Reports

Low Earth orbit represents a valuable limited natural resource. Of particular interest are sun-synchronous orbits; it is estimated that approximately 44% of low Earth satellites are sun-synchronous. A previously developed sun-synchronous orbit slot architecture is considered. An in-depth analysis of the relative motion between satellites and their corresponding slots is performed. The long-term evolution of Earth's orbital environment is modeled by a set of coupled ordinary differential equations. A metric for quantifying the benefit, if any, of implementing a sun-synchronous architecture is developed. The results indicate that the proposed slot architecture would reduce the frequency of collisions between satellites ...


Design, Fabrication, And Testing Of An Emr Based Orbital Debris Impact Testing Platform, Jeffrey J. Maniglia Jr 2013 California Polytechnic State University - San Luis Obispo

Design, Fabrication, And Testing Of An Emr Based Orbital Debris Impact Testing Platform, Jeffrey J. Maniglia Jr

Master's Theses and Project Reports

This paper describes the changes made from Cal Poly’s initial railgun system, the Mk. 1 railgun, to the Mk. 1.1 system, as well as the design, fabrication, and testing of a newer and larger Mk. 2 railgun system. The Mk. 1.1 system is developed as a more efficient alteration of the original Mk. 1 system, but is found to be defective due to hardware deficiencies and failure, as well as unforeseen efficiency losses. A Mk. 2 system is developed and built around donated hardware from the Naval Postgraduate School. The Mk. 2 system strove to implement an ...


Feasibility Of Microsatellite Active Debris Removal Systems, Karsten J. James 2013 California Polytechnic State University - San Luis Obispo

Feasibility Of Microsatellite Active Debris Removal Systems, Karsten J. James

Master's Theses and Project Reports

Space debris has become an increasingly hazardous obstacle to continued spaceflight operations. In an effort to mitigate this problem an investigation of the feasibility of a microsatellite active debris removal system was conducted. Through proposing a novel concept of operation, utilizing a grapple-and-tug system architecture, and by analyzing each resultant mission phase in the frame of a representative example, it was found that microsatellite scale systems are capable of fulfilling the active debris removal mission. Analysis of rendezvous, docking, control and deorbit mission requirements determined that the design of a grapple-and-tug system will be driven by sizing of the propellant ...


Spatial Computing In An Orbital Environment: An Exploration Of The Unique Constraints Of This Special Case To Other Spatial Computing Environments, Jeremy Straub 2013 Selected Works

Spatial Computing In An Orbital Environment: An Exploration Of The Unique Constraints Of This Special Case To Other Spatial Computing Environments, Jeremy Straub

Jeremy Straub

The creation of an orbital services model (where spacecraft expose their capabilities for use by other spacecraft as part of a service-for-hire or barter system) requires effective determination of how to best transmit information between the two collaborating spacecraft. Existing approaches developed for ad hoc networking (e.g., wireless networks with users entering and departing in a pseudo-random fashion) exist; however, these fail to generate optimal solutions as they ignore a critical piece of available information. This additional piece of information is the orbital characteristics of the spacecraft. A spacecraft’s orbit is nearly deterministic if the magnitude and direction ...


Design Of Economical Upper Stage Hybrid Rocket Engine, Christopher R. Potter 2013 University of Tennessee - Knoxville

Design Of Economical Upper Stage Hybrid Rocket Engine, Christopher R. Potter

Chancellor’s Honors Program Projects

No abstract provided.


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