Redesign Of Cubesat For Beam Charging,
2019
California Polytechnic State University, San Luis Obispo
Redesign Of Cubesat For Beam Charging, Kuba Preis
Industrial and Manufacturing Engineering
This paper is intended to be a study in the applications of the design freedom granted by additive manufacture in the design of a 1U CubeSat frame. The main loads experienced by a CubeSat are structural (during launch) and thermal (solar radiation). Beam charging is an emerging technology which involves charging a CubeSat using a laser beam. In this paper, a CubeSat frame was redesigned to account for the structural loads induced during launch and the thermal loads induced when beam charging. The thermal, weight, design, and structural requirements for a new CubeSat design were derived. The 1U CubeSat frame …
Effects Of Corrugations On Stiffness Properties Of Composite Beams For Structural Applications,
2019
California Polytechnic State University, San Luis Obispo
Effects Of Corrugations On Stiffness Properties Of Composite Beams For Structural Applications, Jane Xiao
Master's Theses
Composites have high strength-to-weight ratios, which is particularly desired for applications with weight restrictions. Common composite materials such as carbon fiber reinforced plastic (CF) and fiber glass reinforced plastic (FG) were used in this research. While composite materials possess high stiffness and strength properties, the stiffness of composite laminates may be maximized by changing the geometry. By adding corrugations, the flexural stiffness is increased in one direction compared to the stiffness of a flat part with the same amount of material. Thus, stiffness increases without a change in weight. The primary goal of this research was to investigate the stiffness …
Atomic Oxygen Effects On Particulate Contamination And Short Beam Strength Of Carbon Composites,
2019
California Polytechnic State University, San Luis Obispo
Atomic Oxygen Effects On Particulate Contamination And Short Beam Strength Of Carbon Composites, Marlee K. Litzinger
Master's Theses
In order to design a successful space system, the unique challenges of the space environment it will operate in must be considered during the design process. Atomic oxygen (AO) is a detrimental environmental effect found in Low Earth Orbit (LEO) that affects spacecraft surfaces by oxidizing and eroding material over time, particularly polymers. Carbon fiber/epoxy composites are a commonly used spacecraft material affected by AO exposure. Carbon composites are used as a structural material, such as on solar panels; their large surface area therefore is a potential contamination source to sensitive components. The Space Environments and Testing Lab at California …
Development Of A Multi-Probe Kelvin Scanner Device For Industrially-Relevant Characterization Of Surface-Activated Carbon Fiber Reinforced Thermoplastic Composites,
2019
Washington University in St. Louis
Development Of A Multi-Probe Kelvin Scanner Device For Industrially-Relevant Characterization Of Surface-Activated Carbon Fiber Reinforced Thermoplastic Composites, Kirby Simon
McKelvey School of Engineering Graduate Student Theses & Dissertations
Carbon fiber reinforced thermoplastic (CFRTP) composites are becoming increasingly attractive materials in manufacturing due to their lightweight nature, mechanical strength, and corrosion resistance. Surface activation of these materials is usually required during processing to increase the bond strength of assemblies (aerospace and automotive industries) or improve adhesion with implants (biomedical industry). Industrially-relevant, nondestructive quality control methods for assessing the activation state of these materials do not currently exist, however. Applying principles discovered through the use of scanning probe microscopy, a multiple-probe Kelvin scanning (MPKS) device has been developed that can assess the uniformity of the activation state of plasma-treated CFRTP …
Hypervelocity Impact Analysis Of Hybrid Nanocomposite Sensors For Inflatable Space Structures,
2019
Embry-Riddle Aeronautical University
Hypervelocity Impact Analysis Of Hybrid Nanocomposite Sensors For Inflatable Space Structures, Yachna Gola
Doctoral Dissertations and Master's Theses
Future space exploration requires easy-to-transport, and easy-to-build and deploy space habitats. NASA and Bigelow Aerospace have collaborated so that human habitation can be made safe and easy with inflatable space habitats (Litteken, 2017). One of the biggest threats faced by these structures in outer space is impact damage by micrometeoroid orbital debris (MMOD) traveling at velocities as high as 15 km/s (Lemmens, Krag, Rosebrock, & Carnelli, 2013). This work presents fabrication and testing of hybrid nanocomposites with carbon nanotubes (CNT) and coarse graphene nanoplatelets (GNP) as fillers and flexible epoxy matrix, that are proposed to be used for sensing the …
On The Anisotropic Behavior Of Electrodes For Electrical-Based Monitoring Of Cfrp Laminated Composites,
2019
Missouri University of Science and Technlogy
On The Anisotropic Behavior Of Electrodes For Electrical-Based Monitoring Of Cfrp Laminated Composites, Khaled Almuhammadi, Arief Yudhanto, Gilles Lubineau
Mechanical and Aerospace Engineering Faculty Research & Creative Works
Electrical impedance tomography (EIT) is a promising structural health monitoring technique for carbon fiber-reinforced polymer (CFRP) composites. EIT technique has been specifically adopted as a non-destructive testing method along with the electrical characterization methods. Electrodes are the primary component in any EIT system because they act as an interface connecting the instrument/hardware to the structure under inspection. Simulation of electrical inspection of CFRP usually assumes the electrodes to be electrically isotropic interfaces. We show here that such isotropic assumption is a very poor approximation. We experimentally investigated the electrodes contact impedance behavior on CFRP-laminated composite specimens for different surface processing …
Internal Strain Assessment Using Fbgs In A Thermoplastic Composite Subjected To Quasi-Static Indentation And Low-Velocity Impact,
2019
Missouri University of Science and Technlogy
Internal Strain Assessment Using Fbgs In A Thermoplastic Composite Subjected To Quasi-Static Indentation And Low-Velocity Impact, M. Mulle, A. Yudhanto, G. Lubineau, R. Yaldiz, W. Schijve, N. Verghese
Mechanical and Aerospace Engineering Faculty Research & Creative Works
We present, for the first time, an experimental investigation of internal strain monitoring in thermoplastic composites subjected to quasi-static indentation and low-velocity impact using embedded fiber Bragg gratings (FBGs). The goal is to highlight the interest and limitations of the in-core instrumentation of glass fiber-reinforced polypropylene laminates subjected to these two classical loading conditions. We propose an instrumentation strategy utilizing FBGs that is expected to provide a reliable set of internal strain values and strain rates, which can be used for the analysis of the damage behavior and the validation of a numerical mesoscale model of laminates. Based on a …
Non-Linear Bending Analysis Of Functionally Graded Beams With Spring Constraints And Thermal Effects,
2019
Embry-Riddle Aeronautical University
Non-Linear Bending Analysis Of Functionally Graded Beams With Spring Constraints And Thermal Effects, Swetha Suresh
Doctoral Dissertations and Master's Theses
No abstract provided.
Piezoelectric Sensor Crack Detection On Airframe Systems,
2019
Air Force Institute of Technology
Piezoelectric Sensor Crack Detection On Airframe Systems, Kevin J. Lin
Theses and Dissertations
In 2008, the Department of Defense published a guidebook for a methodology named Condition-Based Maintenance Plus (CBM+) which capabilities include improving productivity, shortening maintenance cycles, lowering costs, and increasing availability and reliability. This push replaces existing inspection criteria, often conducted as non-destructive testing (NDT), with structural health monitoring (SHM) systems. The SHM system addressed utilizes guided Lamb waves generated by piezoelectric wafer active sensors (PWAS) to detect the existence, size, and location of damage from through-thickness cracks around a rivet hole. The SHM field lacks an experiment testing how small changes in receiver sensor distances affect damage detection. In addition, …
Initial Stage Of Fluid-Structure Interaction Of A Celestial Icosahedron Shaped Vacuum Lighter Than Air Vehicle,
2019
Air Force Institute of Technology
Initial Stage Of Fluid-Structure Interaction Of A Celestial Icosahedron Shaped Vacuum Lighter Than Air Vehicle, Dustin P. Graves
Theses and Dissertations
The analysis of a celestial icosahedron geometry is considered as a potential design for a Vacuum Lighter than Air Vehicle (VLTAV). The goal of the analysis is ultimately to understand the initial fluid-structure interaction of the VLTAV and the surrounding airflow. Up to this point, previous research analyzed the celestial icosahedron VLTAV in relation to withstanding a symmetric sea-level pressure applied to the membrane of the structure. This scenario simulates an internal vacuum being applied in the worst-case atmospheric environmental condition. The next step in analysis is to determine the aerodynamic effects of the geometry. The experimental setup for obtaining …
Revealing The Effects Of Matrix Behavior On Low-Velocity Impact Response Of Continuous Fiber-Reinforced Thermoplastic Laminates,
2019
Missouri University of Science and Technlogy
Revealing The Effects Of Matrix Behavior On Low-Velocity Impact Response Of Continuous Fiber-Reinforced Thermoplastic Laminates, A. Yudhanto, H. Wafai, G. Lubineau, S. Goutham, M. Mulle, R. Yaldiz, N. Verghese
Mechanical and Aerospace Engineering Faculty Research & Creative Works
Matrix behavior is expected to widely influence the impact response of composites, but detailed conclusions in the case of thermoplastic laminates are still needed. In this paper, we investigated the effect of using either ductile homopolymer PP or less-ductile impact copolymer PP matrices on the low-velocity impact responses of continuous glass fiber-reinforced polypropylene (PP) laminate. These PP types represent two variants in the same family of thermoplastic matrix. A thorough experimental campaign was first performed to provide the tensile properties (for PP and glass/PP) and fracture toughness (Mode-I and Mode-II, glass/PP only) of the employed materials. Then, low-velocity impact tests …
In Situ Micro-Scale High-Speed Imaging For Evaluation Of Fracture Propagation And Fracture Toughness Of Thermoplastic Laminates Subjected To Impact,
2019
Missouri University of Science and Technlogy
In Situ Micro-Scale High-Speed Imaging For Evaluation Of Fracture Propagation And Fracture Toughness Of Thermoplastic Laminates Subjected To Impact, H. Wafai, A. Yudhanto, G. Lubineau, M. Mulle, T. Alghamdi, S. T. Thoroddsen, R. Yaldiz, N. Verghese
Mechanical and Aerospace Engineering Faculty Research & Creative Works
Measuring parameters related to each damage mode of composites subjected to impact is very challenging because of the complex damage phenomenology. Here, we developed an experimental methodology for evaluating the micro-scale fracture characteristics of two principal damage modes, i.e., transverse crack and delamination, and providing the corresponding fracture toughness. We demonstrated the capability of the method by comparing and providing additional insights about two materials, namely homopolymer-based (ductile) and copolymer-based (less-ductile) glass/polypropylene thermoplastic composites. We found that (i) transverse crack behavior of both composites is similar as indicated by a small difference in their fracture toughness, (ii) delamination growth in …
W&B Problems For Far/Cs 25 Airplanes Tutorial,
2019
Minnesota State University, Mankato
W&B Problems For Far/Cs 25 Airplanes Tutorial, Nihad E. Daidzic
Aviation Department Publications
Weight and Balance (W&B) computations are essential step in ensuring that the aircraft (in this case FAR/CS 25 Transport-category airplanes) is properly loaded with its Center of Mass (CM) of Center of Weight/Gravity (CG) in the proper range.
Influence Of Process-Induced Shrinkage And Annealing On The Thermomechanical Behavior Of Glass Fiber-Reinforced Polypropylene,
2019
Missouri University of Science and Technlogy
Influence Of Process-Induced Shrinkage And Annealing On The Thermomechanical Behavior Of Glass Fiber-Reinforced Polypropylene, M. Mulle, H. Wafai, A. Yudhanto, G. Lubineau, R. Yaldiz, W. Schijve, N. Verghese
Mechanical and Aerospace Engineering Faculty Research & Creative Works
We investigate the influence of process-induced shrinkage and subsequent annealing on the thermomechanical behavior of unidirectional laminates made of continuous glass fiber-reinforced polypropylene (GFPP). We use two different industrial lamination processes: static hot-presses (SHP), and double-belt press (DBP) that are characterized by different cooling rates and pressure levels and most importantly, by the use of a closed mold in the case of SHP manufacturing. We measure the longitudinal and transverse shrinkage during the manufacturing and annealing processes using embedded fiber Bragg gratings (FBGs). The SHP molding reveals much lower induced shrinkage in GFPP as compared to the DBP process, although …
Composite Recycler: Delamination,
2019
Central Washington University
Composite Recycler: Delamination, Nathan Sauer
All Undergraduate Projects
A great deal of composite waste is generated in the construction of wings for the Boeing 777. These carbon fiber “wing trimmings” are currently being disposed of in a landfill. These carbon fiber boards are made of several layers laminated together, making them very rigid and hard to recycle. This report proposes a method to delaminate the layers of these composite wing trimmings using a hydraulic press and a V-shaped steel die so that they may be more easily shredded and thus recycled. A top, “male” die with two points is pressed into a bottom, “female” die with three points …
3d Textile Preforms And Composites For Aircraft Strcutures: A Review,
2019
University of sistan and baluchestan, Zahedan, Iran
3d Textile Preforms And Composites For Aircraft Strcutures: A Review, Abbasali Saboktakin
International Journal of Aviation, Aeronautics, and Aerospace
Over the last decades, the development of 3D textile composites has been driven the structures developed to overcome disadvantages of 2D laminates such as the needs of reducing fabrication cost, increasing through-thickness mechanical properties, and improving impact damage tolerance. 3D woven, stitched, knitted and braided preforms have been used as composites reinforcement for these types of composites. In this paper, advantages and disadvantages of each of them have been comprehensively discussed. The fabric architects and their specification in particular stitched preforms and their deformation mode for aerospace applications have been reviewed. Exact insight into various types of damage in textile …
Real-Time Electrical Impedance Monitoring Of Carbon Fiber-Reinforced Polymer Laminates Undergoing Quasi-Static Indentation,
2019
Missouri University of Science and Technlogy
Real-Time Electrical Impedance Monitoring Of Carbon Fiber-Reinforced Polymer Laminates Undergoing Quasi-Static Indentation, Khaled Almuhammadi, Arief Yudhanto, Gilles Lubineau
Mechanical and Aerospace Engineering Faculty Research & Creative Works
Laminated composites are vulnerable to damage from out-of-plane loading, particularly impact loading, and the incurred damage is often only detected by evaluating the post-impact condition of the composites. Real-time monitoring techniques are desirable for early detection of damage. Utilizing changes in the electrical properties of composites to track incurred damage is promising, but the interpretation of such measurements is still challenging. Here, an electro-mechanical system is introduced to understand how well we could detect mechanical degradation in carbon-fiber-reinforced polymer (CFRP) plates undergoing a quasi-static indentation (QSI) test, which is representative of an impact load. The system measures the in situ, …
An Experimental Approach That Assesses In-Situ Micro-Scale Damage Mechanisms And Fracture Toughness In Thermoplastic Laminates Under Out-Of-Plane Loading,
2019
Missouri University of Science and Technlogy
An Experimental Approach That Assesses In-Situ Micro-Scale Damage Mechanisms And Fracture Toughness In Thermoplastic Laminates Under Out-Of-Plane Loading, H. Wafai, A. Yudhanto, G. Lubineau, R. Yaldiz, N. Verghese
Mechanical and Aerospace Engineering Faculty Research & Creative Works
Studying the response of laminated composites under out-of-plane loading routinely involves mechanical tests, such as quasi-static indentation or impact. The phenomenology during these tests is so complex that it is difficult to identify different material properties related to each failure mechanism (damage mode). We aim at providing an experimental approach, which is practical and fast, for assessing the in-situ micro-scale damage mechanism and extracting the fracture toughness in thermoplastic laminates under out-of-plane loading. To this end, we developed a dedicated, micro-scale, three-point bending (micro-3PB) test fitted inside a scanning electron microscope (SEM). In a single experiment, we were able: (i) …
Enhanced Surface Integrity With Thermally Stable Residual Stress Fields And Nanostructures In Cryogenic Processing Of Titanium Alloy Ti-6al-4v,
2019
University of Kentucky
Enhanced Surface Integrity With Thermally Stable Residual Stress Fields And Nanostructures In Cryogenic Processing Of Titanium Alloy Ti-6al-4v, James R. Caudill
Theses and Dissertations--Mechanical and Aerospace Engineering
Burnishing is a chipless finishing process used to improve surface integrity by severe plastic deformation (SPD) of surface asperities. As surface integrity in large measure defines the functional performance and fatigue life of aerospace alloys, burnishing is thus a means of increasing the fatigue life of critical components, such as turbine and compressor blades in gas turbine engines. Therefore, the primary objective of this dissertation is to characterize the burnishing-induced surface integrity of Ti-6Al-4V alloy in terms of the implemented processing parameters. As the impact of cooling mechanisms on surface integrity from SPD processing is largely unexplored, a particular emphasis …
Fe Modeling Methodology For Load Analysis And Preliminary Sizing Of Aircraft Wing Structure,
2019
Defense Acquisition Program Administration
Fe Modeling Methodology For Load Analysis And Preliminary Sizing Of Aircraft Wing Structure, Jun Hwan Jang, Sang Ho Ahn
International Journal of Aviation, Aeronautics, and Aerospace
It is a critical part at the basic design phase of aircraft structural design to build a finite element model and it will have a direct impact on time and cost for airframe structure development. In addition, the objective of finite element model will be varied depending on each design review phase and the modelling methodology varied accordingly. In order to build an effective and economic finite element model, it is required to develop adequate level of modelling methodology based on each design phase and its objectives. Therefore, in this paper, the finite element modeling methodology was presented for internal …
