Propulsion and Power Commons^™

The Robert H. Goddard Papers, Robert H. Goddard

Archives & Special Collections Finding Aids

Dr. Robert H. Goddard was a member of the Clark Physics Department for 29 years. Foremost American pioneer of rocket research, he laid the technical and theoretical foundations for many of the developments in long-range rockets, missiles, satellites and space flight, which collectively put us into the Space Age.

The collection includes correspondence, diaries, journals, patent applications and awards, reports, and photographs. The collection also includes original paintings by Dr. Goddard.

The Creation, Analysis, And Verification Of A Comprehensive Model Of A Micro Ion Thruster, Maxwell J. Bodnar

Master's Theses

A computational model of the micro-ion thruster MiXI has been developed, analyzed, and partially verified. This model includes submodels that govern the physical, magnetic, electrostatic, plasma physics, and power deposition of the thruster. Over the past few years, theses have been conducted with the goal of running tests and analyzing the results; this model is used to understand how the thruster components interact so as to make predictions about, and allow for optimization of, the thruster operation. Testing is then performed on the thruster and the results are compared to the output of the code. The magnetic structure of the …

Inlet Shape Considerations For Split-Wing Electric Distributed Propulsion, Kurt Vonderhaar Papathakis

Master's Theses

This thesis aims to uncover preliminary design relationships for an inlet of a split-wing electric distributed propulsion regional airliner. Several aspects of the inlet design were investigated, including: the overall thickness of the airfoil section with respect to the chord, inlet throat area, and lip radius. These parameters were investigated using several angles of attack and mass flow rates through the fan. Computational fluid dynamics, with a 2^nd Order turbulence model was used and validated against World War II era data from NACA, as those studies were the most pertinent wind tunnel data available. Additionally, other works by Boeing, …

Hybrid Rocket Motor Scaling Process, Joseph B. R. Vanherweg

Master's Theses

Hybrid rocket propulsion technology shows promise for the next generation of sounding rockets and small launch vehicles. This paper seeks to provide details on the process of developing hybrid propulsion systems to the academic and amateur rocket communities to assist in future research and development. Scaling hybrid rocket motors for use in sounding rockets has been a challenge due to the inadequacies in traditional boundary layer analysis. Similarity scaling is an amendment to traditional boundary layer analysis which is helpful in removing some of the past scaling challenges. Maintaining geometric similarity, oxidizer and fuel similarity and mass flow rate to …

Trajectory Analysis And Comparison Of A Linear Aerospike Nozzle To A Conventional Bell Nozzle For Ssto Flight, Elizabeth Lara Lash

Masters Theses

Single-stage to orbit (SSTO) rocket technology offers the potential to substantially reduce launch costs, but has yet to be considered practical for conventional launch vehicles. However, new research in composite propellant tank technology opens the field for renewed evaluation. One technology that increases the efficiency and feasibility of SSTO flight is an altitude compensating rocket engine nozzle, as opposed to a conventional constant area, bell nozzle design. By implementing an altitude compensation nozzle, such as a linear, aerospike nozzle for in-atmosphere flight, the propellant mass fraction (PMF) may be reduced by as much as seven percent compared to a conventional …

Analysis Of Flammability Limits And Gas Properties Of A Solid Rocket Motor Test In A High Altitude Test Facility, Richard Scott Kirkpatrick

Masters Theses

The testing of solid and liquid rocket propulsion systems in a confined test facility often produces explosive or flammable gases which must be safely handled. Often inert gases such as nitrogen are used to lower the molar fraction of oxygen to low enough levels to minimize the probability of an explosion or deflagration. For this thesis, the chemical composition of these rocket exhaust gases mixed with air were used to determine the flammability limits of the gas mixture. Using the ideal gas law and the conservation of mass, the exhaust gas composition and gas properties such as pressure, temperature, volume …

Consideration Of The Use Of An Origami Style Solar Panel Array For A Space Solar Power Generation Satellite, Landon Klein, Tristan Plante, Alex Holland, Benjamin Kading, Jeremy Straub, David Whalen

Jeremy Straub

Since the beginning of the space race, space exploration has been an important part of America’s technological develop-ment. The notion of a power-intensive [1] mission to Mars, which utilizes 3D printing has been proposed. Space Solar Power can supply energy for this mission. This paper presents an Origami solar panel, based on work by [2], that can supply power to an outpost on Mars.

Consideration Of The Use Of A Space Solar Power Satellite System For A Manned Mars Mission, Benjamin Kading, Jeremy Straub, Tristan Plante, Alex Holland, Jordan Forbord, Landon Klein, David Whalen

Jeremy Straub

The design of a manned Mars mission has been a point of ongoing interest . Numerous Mars missions have been proposed and designed but major roadblocks impair their completion. Primarily, these issues are related to cost and safety concerns. However, many technologies have been developed and are being developed to make a Mars mission more feasible. One such technology is Space So- lar Power. (SSP) SSP technology involves generating power in space from the sun and beaming it via microwave radia- tion to a ground site for use. This method has immediate usability on Mars due to the minimal atmosphere, …

Cubesat Deployable Solar Panel System, Thomas Mcguire, Skye Leake, Michael Parsons, Michael Hirsch, Benjamin Kading, Jeremy Straub, David Whalen

Jeremy Straub

CubeSats are small spacecraft with a nominal size of 10 cm x 10 cm x 10 cm and a mass of 1.33 kg [1] (though some launch providers are now supporting expanded mass levels). While the CubeSat form factor has re-duced the time and cost of spacecraft development, the required resources are still beyond the grasp of many colleges and universities. The Open Prototype for Educational Nanosats (OPEN) aims to solve this problem. OPEN is an inexpen-sive modular CubeSat that can be produced with a parts budget of less than $5,000 [2]. The OpenOrbiter pro-gram is working to develop this …

Pattern Recognition And Expert Systems For Microwave Wireless Power Transmission Failure Prevention, Cameron Kerbaugh, Allen Mcdermott, Jeremy Straub, Eunjin Kim

Jeremy Straub

Wireless power transfer (WPT) can be used to deliver space-generated power to ground stations through the use of microwave beams. WPT satellite power delivery systems have two major failure states: misdi-recting a beam and failing to send power to a station. This project has implemented an expert system to perform pattern recognition in an effort to prevent failures by analyzing the system state and predicting potential failures before they happen in support of space-based testing [1] and deployment [2].

Design Concept For A Power Generating Satellite For A Manned Mars Mission, Alex Holland, Tristan Plante, Jordan Forbord, Landon Klein, Benjamin Kading, Jeremy Straub, David Whalen

Jeremy Straub

Once proposed work in low-Earth orbit [1] to demonstrate the efficacy of wireless power transmis- sion is a mission is completed, an additional step is needed before the technology is sufficiently tested for use on Earth. A Martian mission (such as [2]) is pro- posed to allow the demonstration of the use of the wireless power transmission technology in support of and proximity to human astronaut operations.

This poster presets a satellite concept intended for use on this Mars mission, to supply power that is need- ed for human habitation and other purposes. This satel- lite is designed to be …

Pattern Recognition For Detecting Failures In Space Solar Power Systems, Allen Mcdermott, Cameron Kerbaugh, Jeremy Straub, Eunjin Kim

Jeremy Straub

This poster covers work relating to the use of expert systems and pattern recognition to attempt to identify, detect and prospectively stop patterns of activity that could potentially lead to failure of a space solar power (SSP) system. A database-based expert system has is presented to identify patterns, which can be used to determine whether a power beam could hit a unintend- ed target and potentially cause a calamity. This has been implemented via a facts-rule network via which supplied and collected facts and a rule set is used to de- termine whether the system is operating correctly (from a …

Detecting Failures In Space Solar Power Systems With Pattern Recognition, Allen Mcdermott, Cameron Kerbaugh, Jeremy Straub

Jeremy Straub

This poster covers work relating to the use of expert systems and pattern recognition to attempt to identify, detect and prospectively stop patterns of activity that could potentially lead to failure of a space solar power (SSP) system. A database-based expert system has is presented to identify patterns, which can be used to determine whether a power beam could hit a unintend-ed target and potentially cause a calamity. This has been implemented via a facts-rule network via which supplied and collected facts and a rule set is used to de-termine whether the system is operating correctly (from a holistic perspective). …

An Expert System For Microwave Wireless Power Transmission Failure Prevention, Cameron Kerbaugh, Allen Mcdermott, Jeremy Straub

Jeremy Straub

Wireless power transfer (WPT) can be used to deliver space-generated power to ground stations through the use of microwave beams. WPT satellite power delivery systems have two major failure states: misdi-recting a beam and failing to send power to a station. This project has implemented an expert system to perform pattern recognition in an effort to prevent failures by analyzing the system state and predicting potential failures before they happen in support of space-based testing [1] and deployment [2].

Comparison Of Radiation Dosage For Human Piloted Mars Missions Using Chemical, Nuclear Thermal, And Fusion Propulsion Systems, Steven Doyle

Research Horizons Day Posters

No abstract provided.

Lift Generating Device, Juan A. Alvarado

Publications

A lift generating device is provided enabling vertical flight. The lift generating device includes a first revolution structure having a funnel shape and a second revolution structure hav­ing a funnel shape. Each revolution structure includes a cir­cular open surface and an open stem. The second revolution structure is attached to the first revolution structure by a plurality of connectors so as to form a gap between the first revolution structure and the second revolution structure. A propeller is coupled to an open stem at a bottom end of the first revolution structure and a motor is operatively connected to the …

Unmanned Aerial Vehicle (Uav) Propulsion Research: Conceptual Studies Of “Ultra-Compact Shaft-Less Jet Engines” For Next Generation Uavs, Tyler Eiguren, Trevor Douglas, Tre Buchanan

Publications

Unmanned Aerial Vehicles are becoming more commonly used in today’s society, ranging anywhere from military applications to entertainment for enthusiasts and hobbyists. The complexity of current generation UAV’s propulsive devices, based upon a scaled turbine engine and separate gas & electrically powered rotating fan blades, require regular maintenance for every 24 hours of flight. This added cost coupled with necessary intricate machinery deters UAV designers from such engines, leaving a void in current production. Our research team believes that by combining a simplified alternative compression & combustion process with an electrically driven fan, we can develop an energy efficient, reliable, …

The Panther: 2015 Aiaa Design Build Fly, Bryce Milnes, Chris Crawford

Publications

The ERAU Prescott chapter of AIAA participated in the 2015 AIAA Design Build Fly competition at Raytheon Missile Systems in Tucson from April 10-12. A remote controlled aircraft meeting and exceeding all competition performance requirements was designed and fabricated by the 30+ students of the team. Additionally, a 60 page report was submitted detailing the project starting from initial considerations and advancing through flight test verification of aircraft capabilities. The success of this project was enabled by the E-Prize and SGA funding received to support our efforts throughout the year. The lessons learned regarding management and planning, engineering design approaches, …

Overall Effectiveness Measurement At Engine Temperatures With Reactive Film Cooling And Surface Curvature, Andrew J. Lynch

Theses and Dissertations

The thesis presented here details the design, construction and initial testing of rig for use with high temperature film cooling testing. The film cooling rig was supplied with hot mainstream gas from a well-stirred reactor operating on a propane/air mixture capable of multiple equivalence ratios. The Hastelloy test plates contained an internal cooling channel to allow for overall effectiveness measurements. Thermocouples on both the freestream and internal surfaces of the test plate provided temperature differences for heat flux calculations. The test plates had a quarter circle leading edge with a tapered trailing edge to provide surface curvature for the film …

Computer Modeling Of A Rotating Detonation Engine In A Rocket Configuration, Nihar Shah

Theses and Dissertations

Detonation-based combustors leverage the higher thermodynamic efficiency of the Atkinson cycle compared to the traditional deflagration-based combustion of the Brayton cycle. The rotating detonation engine (RDE) has one or more shock waves rotating around an annulus. The RDE can theoretically be 20% more thermally efficient than a traditional deflagration-based cycle. A RDE was modeled in Numerical Propulsion System Simulation (NPSS) based on a model developed in Microsoft Excel. The thermodynamic analysis of the RDE in these models is broken into four streams. Empirical models were used to find the percentage of the total flow in each stream. The pre-detonation pressure …