Small Satellites With Micro-Propulsion For Communications With The Lunar South Pole Aitkens Basin, Samudra E. Haque, Jeremy Straub, David Whalen
A lunar sample return mission to the Lunar South-Pole Aitkens Basin (LSPAB) has been highlighted as a high priority objective of the most recent (2011) Decadal Survey for Planetary Science, by the National Research Council. This class of mission, however, faces a dramatic communications limitation, due to the lack of a frequent, or continuous, line-of-sight communications path to Earthbased ground stations. Brunner and others have proposed a communications system utilizing Low Lunar Polar Orbits (LLPO) and Lunar Halo orbits for this purpose. Ely and others have outlined proposals for using several communication satellites to form a relay network using LLPO ...
Design And Performance Of Circulation Control Geometries, 2013 California Polytechnic State University - San Luis Obispo
Design And Performance Of Circulation Control Geometries, Rory Martin Golden Mr.
Master's Theses and Project Reports
With the pursuit of more advanced and environmentally-friendly technologies of today’s society, the airline industry has been pushed further to investigate solutions that will reduce airport noise and congestion, cut down on emissions, and improve the overall performance of aircraft. These items directly influence airport size (runway length), flight patterns in the community surrounding the airport, cruise speed, and many other aircraft design considerations which are setting the requirements for next generation aircraft. Leading the research in this movement is NASA, which has set specific goals for the next generation regional airliners and has categorized the designs that meet ...
Ad-Hoc Regional Coverage Constellations Of Cubesats Using Secondary Launches, 2013 California Polytechnic State University, San Luis Obispo
Ad-Hoc Regional Coverage Constellations Of Cubesats Using Secondary Launches, Guy G. Zohar
Master's Theses and Project Reports
As development of CubeSat based architectures increase, methods of deploying constellations of CubeSats are required to increase functionality of future systems. Given their low cost and quickly increasing launch opportunities, large numbers of CubeSats can easily be developed and deployed in orbit. However, as secondary payloads, CubeSats are severely limited in their options for deployment into appropriate constellation geometries.
This thesis examines the current methods for deploying cubes and proposes new and efficient geometries using secondary launch opportunities. Due to the current deployment hardware architecture, only the use of different launch opportunities, deployment direction, and deployment timing for individual cubes ...
Open Space Box Model: Service Oriented Architecture Framework For Small Spacecraft Collaboration And Control, Atif F. Mohammad, Jeremy Straub
A Cubesat is a small satellite with very less competence to compute, it requires software engineering techniques, which can enhance the computational power for this small box. A model-driven approach of software engineering, which is called OSBM or Open Space Box Modeling technique, is an excellent solution to this re-source maximization challenge. OSBM facilitates apparition of the key solution pro-cesses computation and satellite related data elements using Service Oriented Ar-chitecture 3.0 (SOA 3.0) as base to work on to design services. The key challenges that can be handled by utilizing OSBM include concurrent operation and tasking of few ...
Visual Attitude Propagation For Small Satellites, 2013 University of Kentucky
Visual Attitude Propagation For Small Satellites, Samir Ahmed Rawashdeh
Theses and Dissertations--Electrical and Computer Engineering
As electronics become smaller and more capable, it has become possible to conduct meaningful and sophisticated satellite missions in a small form factor. However, the capability of small satellites and the range of possible applications are limited by the capabilities of several technologies, including attitude determination and control systems. This dissertation evaluates the use of image-based visual attitude propagation as a compliment or alternative to other attitude determination technologies that are suitable for miniature satellites. The concept lies in using miniature cameras to track image features across frames and extracting the underlying rotation.
The problem of visual attitude propagation as ...
Three-Axis Stabilized Earth Orbiting Spacecraft Simulator, 2012 California Polytechnic State University – San Luis Obispo
Three-Axis Stabilized Earth Orbiting Spacecraft Simulator, Alan F. Ma, Nikola N. Dominikovic
This report details the method and results of the program created for simulating an Earth orbiting spacecraft with control actuators and orbital perturbations. The control actuators modeled are reaction thrusters, reaction/momentum wheels, and control moment gyros (CMG). The perturbations modeled were gravity gradient, electromagnetic torques, solar radiation pressure, gravity gradients, third-body effects, Earth oblateness and atmospheric drag. This simulation allows for satellite control in all 6 degrees of freedom for any Earth orbiting spacecraft. Assumptions include rigid body dynamics, no sensor noise, constant spacecraft cross-sectional area, constant coefficient of drag and reflectivity, ignoring the effects due to the moon ...
An Alternative Dual-Launch Architecture For A Crewed Asteroid Mission, 2012 California Polytechnic State University - San Luis Obispo
An Alternative Dual-Launch Architecture For A Crewed Asteroid Mission, Steven M. Korn
Master's Theses and Project Reports
This thesis is a feasibility study for a crewed mission to a Near Earth Asteroid (NEA). An alternate dual-launch architecture is proposed and analyzed against a more established architecture. Instead of a rendezvous in a low-Earth parking orbit, the new architecture performs the rendezvous while the two spacecraft are on an Earth-escape trajectory to the destination NEA. After selecting a target asteroid, 2000 SG344, each architecture will have its best mission compared to the best mission of the other architecture.
Using the new architecture, a mission is created to the chosen NEA, 2000 SG344. A back-up Orion MPCV and a ...
High-Fidelity Low-Thrust Trajectory Determination Research And Analysis, 2012 California Polytechnic State University - San Luis Obispo
High-Fidelity Low-Thrust Trajectory Determination Research And Analysis, Tyler Hill
This document discusses a numerical analysis method for low thrust trajectory propagation known as the proximity quotient or Q-Law. The process uses a Lyapunov feedback control law developed by Petropoulos to propagate trajectories of spacecraft by minimizing the user defined function at the target orbit. A simplified propagator is created from the core mechanics of this method in MATLAB and tested in several user defined cases to demonstrate its capabilities. Several anomalies arose in test cases where variations in eccentricity, inclination, right ascension of the ascending node, and argument of perigee were specified. Solutions to these anomalies are discussed ...
Computation Time Comparison Between Matlab And C++ Using Launch Windows, 2012 California Polytechnic State University - San Luis Obispo
Computation Time Comparison Between Matlab And C++ Using Launch Windows, Tyler Andrews
Processing speed between Matlab and C++ was compared by examining launch windows and handling large amounts of data found in pork chop plots. A compilation of code was generated in Matlab to produce the plots and an identical file was created in C++ that was then compiled and run in Matlab to plot the data. This file is known as a MEX-file. This report outlines some of the basics when working with MEX-files and the problems that face users. For Lambert’s solver, multi revolution cases were considered and some pork chop plots of single revolution trajectories were plotted. Three ...
Accelerating Lambert's Problem On The Gpu In Matlab, 2012 California Polytechnic State University - San Luis Obispo
Accelerating Lambert's Problem On The Gpu In Matlab, Nathan Parrish
The challenges and benefits of using the GPU to compute solutions to Lambert’s Problem are discussed. Three algorithms (Universal Variables, Gooding’s algorithm, and Izzo’s algorithm) were adapted for GPU computation directly within MATLAB. The robustness of each algorithm was considered, along with the speed at which it could be computed on each of three computers. All algorithms used were found to be completely robust. Computation time was measured for computation within a for-loop, a parfor-loop, and a call to the MATLAB command ‘arrayfun’ with gpuArray-type inputs. Then, a Universal Variables Lambert’s solver was written in CUDA ...
The Numerical Open-Source Many-Body Simulator (Noms), 2012 California Polytechnic State University - San Luis Obispo
The Numerical Open-Source Many-Body Simulator (Noms), Jason Lloyd Daniel, Javen Kyle Foster-O'Neal
This paper outlines the setup and creation of an object-oriented N-body simulator as part of a continued project to explore physical phenomenon and human-computer natural interaction technologies. The tools and processes required to build an N-body simulator are also included. Several integrators were evaluated based on their ability to maintain system energy The 2nd order integrator Verlet and 3rd order integrator Hermite algorithms had the greatest accuracy to model large-scale N-body dynamics for their given computation time. Other algorithms required significantly shorter time steps to achieve similar short-term accuracy. At present, NOMS can reasonably simulate 10,000 particles at less ...
De-Orbiting Upper Stage Rocket Bodies Using A Deployable High Altitude Drag Sail, 2012 California Polytechnic State University - San Luis Obispo
De-Orbiting Upper Stage Rocket Bodies Using A Deployable High Altitude Drag Sail, Robert A. Hawkins Jr., Joseph A. Palomares
This report examines the effectiveness of a drag sail to de-orbit upper stage rocket bodies. Many other perturbations contribute to the de-orbiting of these rocket bodies, and these perturbations will also be discussed briefly. This paper will show the length of time needed to force the altitudes of various launch vehicle stages with varying drag area sizes to less than 100 km. The upper stage of the Delta IV launch vehicle in an orbit with an altitude of 500 km will naturally de-orbit in 720 days but when equipped with a 20 m2 drag sail, it will de-orbit in ...
Comprehensive Matlab Gui For Determining Barycentric Orbital Trajectories, 2012 California Polytechnic State University - San Luis Obispo
Comprehensive Matlab Gui For Determining Barycentric Orbital Trajectories, Steve Katzman
When a 3-body gravitational system is modeled using a rotating coordinate frame, interesting applications become apparent. This frame, otherwise known as a barycentric coordinate system, rotates about the system’s center of mass. Five unique points known as Lagrange points rotate with the system and have numerous applications for spacecraft operations. The goal of the Matlab GUI was to allow easy manipulation of trajectories in a barycentric coordinate system to achieve one of two end goals: a free-return trajectory or a Lagrange point rendezvous. Through graphical user input and an iterative solver, the GUI is capable of calculating and optimizing ...
A Survey Of Mission Opportunities To Trans-Neptunian Objects – Part Ii, 2012 University of Tennessee - Knoxville
A Survey Of Mission Opportunities To Trans-Neptunian Objects – Part Ii, Ashley M. Gleaves
Chancellor’s Honors Program Projects
No abstract provided.
Sun-Synchronous Orbit Slot Architecture Analysis And Development, 2012 California Polytechnic State University - San Luis Obispo
Sun-Synchronous Orbit Slot Architecture Analysis And Development, Eric Watson
Master's Theses and Project Reports
Space debris growth and an influx in space traffic will create a need for increased space traffic management. Due to orbital population density and likely future growth, the implementation of a slot architecture to Sun-synchronous orbit is considered in order to mitigate conjunctions among active satellites. This paper furthers work done in Sun-synchronous orbit slot architecture design and focuses on two main aspects. First, an in-depth relative motion analysis of satellites with respect to their assigned slots is presented. Then, a method for developing a slot architecture from a specific set of user defined inputs is derived.
Optimization And Design For Heavy Lift Launch Vehicles, 2012 University of Tennessee - Knoxville
Optimization And Design For Heavy Lift Launch Vehicles, Paul Andreas Ritter
The simulation and evaluation of an orbital launch vehicle requires consideration of numerous factors. These factors include, but are not limited to the propulsion system, aerodynamic effects, rotation of the earth, oblateness, and gravity. A trajectory simulation that considers these different factors is generated by a code developed for this thesis titled Trajectories for Heavy-lift Evaluation and Optimization (THEO). THEO is a validated trajectory simulation code with the ability to model numerous launch configurations. THEO also has the capability to provide the means for an optimization objective. Optimization of a launch vehicle can be specified in terms of many different ...
Asteroid Retrieval Feasibility Study, 2012 California Institute of Technology
Asteroid Retrieval Feasibility Study, John Brophy, Fred Culick, Louis Friedman, Pedro Llanos, Et Al.
This report describes the results of a study sponsored by the Keck Institute for Space Studies (KISS) to investigate the feasibility of identifying, robotically capturing, and returning an entire Near-Earth Asteroid (NEA) to the vicinity of the Earth by the middle of the next decade. The KISS study was performed by people from Ames Research Center, Glenn Research Center, Goddard Space Flight Center, Jet Propulsion Laboratory, Johnson Space Center, Langley Research Center, the California Institute of Technology, Carnegie Mellon, Harvard University, the Naval Postgraduate School, University of California at Los Angeles, University of California at Santa Cruz, University of Southern ...
Applications Of Aerodynamic Forces For Spacecraft Orbit Maneuverability In Operationally Responsive Space And Space Reconstitution Needs, 2012 Air Force Institute of Technology
Applications Of Aerodynamic Forces For Spacecraft Orbit Maneuverability In Operationally Responsive Space And Space Reconstitution Needs, Matthew N. Goodson
Theses and Dissertations
Each year multiple satellites are launched to provide end users key pieces of information. This information ranges from remote sensing data for military or civilian purposes (e.g., weather forecasting, troop movements, agricultural production, etc.) to large bandwidth telecommunications sensors. No matter the type of information needed, society is demanding more. Because of this continual rise in information needs, the current model of launching one satellite for one mission is not sustainable. To satisfy the information needs of nations across the globe, a means for satellites to transition from one mission type to another must be developed. One means of ...
Trajectory Control And Optimization For Responsive Spacecraft, 2012 Air Force Institute of Technology
Trajectory Control And Optimization For Responsive Spacecraft, Constantinos Zagaris
Theses and Dissertations
The concept of responsive space has been gaining interest, and growing to include systems that can be re-tasked to complete multiple missions within their lifetime. The purpose of this study is to develop an algorithm that produces a maneuver trajectory that will cause a spacecraft to arrive at a particular location within its orbit earlier than expected. The time difference, delta t, is used as a metric to quantify the effects of the maneuver. Two separate algorithms are developed. The first algorithm is an optimal control method and is developed through Optimal Control Theory. The second algorithm is a feedback ...
Investigating Various Propulsion Systems For An External Attachment For A Controlled-Manual De-Orbit Of The Hubble Space Telescope, 2012 California Polytechnic State University - San Luis Obispo
Investigating Various Propulsion Systems For An External Attachment For A Controlled-Manual De-Orbit Of The Hubble Space Telescope, Nelson De Guia
This reports explains the results for a proposed senior project. This project concerns the Hubble Space Telescope, and exploring the possibility of having an external propulsion attachment for a manual de-orbit. The Hubble Space Telescope was proposed to return to Earth via the Space Shuttle. Although, through the current U.S. Space Administration, the Space Shuttle has been retired before the Hubble Space Telescope was retrieved. By completing this project, the results could provide insight to what type of propulsion would best de-orbit the Hubble upon its retirement. Different propulsion systems were considered to attempt to determine an optimal attachment ...