Дисертації з теми "Aerospace systems design"
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Pfaender, Jens Holger. "Competitive Assessment of Aerospace Systems using System Dynamics." Diss., Georgia Institute of Technology, 2006. http://hdl.handle.net/1853/14014.
Повний текст джерелаFernandez, Martin Ismael. "Valuation of design adaptability in aerospace systems." Diss., Atlanta, Ga. : Georgia Institute of Technology, 2008. http://hdl.handle.net/1853/22584.
Повний текст джерелаCommittee Chair: Dr. Mavris, Dimitri; Committee Member: Dr. Hollingsworth, Peter; Committee Member: Dr. McMichael, Jim; Committee Member: Dr. Saleh, Joseph; Committee Member: Dr. Schrage, Daniel.
Waslander, Steven L. "Multi-agent systems design for aerospace applications /." May be available electronically:, 2007. http://proquest.umi.com/login?COPT=REJTPTU1MTUmSU5UPTAmVkVSPTI=&clientId=12498.
Повний текст джерелаBorer, Nicholas Keith. "Decision Making Strategies for Probabilistic Aerospace Systems Design." Diss., Georgia Institute of Technology, 2006. http://hdl.handle.net/1853/10469.
Повний текст джерелаWang, Jennifer Y. "Migration of aerospace technologies to adjacent markets." Thesis, Massachusetts Institute of Technology, 2014. http://hdl.handle.net/1721.1/105302.
Повний текст джерелаCataloged from PDF version of thesis.
Includes bibliographical references (pages 51-56).
Shrinking government budgets due to economic woes has aerospace and defense contractors scrambling to sustain their business and minimize the effects of budget sequestration. Given the global economic climate and the level of federal debt, government budget spending is unlikely to recover in the near future to previous levels, where aerospace and defense contractors had enjoyed an abundance of million and billion dollar cost-reimbursable contracts. In current business conditions, company leadership has put a new focus on finding and developing business in adjacent markets, where core competencies can be utilized to generate alternative streams of revenue. In order to provide insight into potential adjacent markets for aerospace technologies and entry strategies that increase chances of success, this thesis analyzes cases of technologies originally developed for an aerospace application that were eventually adopted for use in another (non-aerospace) industry. Analysis of metrics and 35 cases compiled from NASA's Spinoff and Technology Databases reinforce several observations that have been generalized in other literature: 1) a wide variety of industries could be considered adjacent markets, 2) entering established industries may offer the highest technology adoption rate, 3) partnership with an existing firm or organization with knowledge of the adjacent market has played a key role in the successful adoption of the technology in the adjacent market, and 4) building-block technologies at the subsystem, component and base material level most often traversed market boundaries. However, a handful of cases prove that systems can traverse market boundaries in whole under certain conditions. Most importantly, the role of the aerospace industry as advanced analog lead users is a unique advantage that aerospace firms should leverage.
by Jennifer Y. Wang.
S.M. in Engineering and Management
Hart, Peter Bartholomew. "A plm implementation for aerospace systems engineering-conceptual rotorcraft design." Thesis, Georgia Institute of Technology, 2009. http://hdl.handle.net/1853/28278.
Повний текст джерелаAgte, Jeremy S. (Jeremy Sundermeyer). "Multistate analysis and design : case studies in aerospace design and long endurance systems." Thesis, Massachusetts Institute of Technology, 2011. http://hdl.handle.net/1721.1/68167.
Повний текст джерелаThis electronic version was submitted by the student author. The certified thesis is available in the Institute Archives and Special Collections.
"September 2011." Cataloged from student submitted PDF version of thesis.
Includes bibliographical references (p. 221-230).
This research contributes to the field of aerospace engineering by proposing and demonstrating an integrated process for the early-stage, multistate design of aerospace systems. The process takes into early consideration the many partially degraded states that real-world systems experience throughout their operation. Despite advancing efforts aimed at maintaining operation in a state of optimum performance, most systems spend very substantial amounts of time operating in degraded or off-nominal states (e.g. Hubble space telescope, Mars Spirit rover, or aircraft flying under minimum-equipment-list restrictions). There exist relatively few methods and tools to address this at the beginning of the design process. At one end of the spectrum is design optimization, but this typically concentrates on the system in its nominal state of operation, only infrequently considering failure states through piecemeal application of constraints. There is reliability analysis, which focuses on component failure rates and the benefits of redundancy but does not consider how well or poorly the system performs with partial failures. Finally, there is controls theory, where control laws are optimized but the plant is typically assumed to be given a priori. The methodology described within this thesis coordinates elements from each of these three areas into an effective integrated framework. It allows the designer deeper insight into the complex problem of designing cost effective systems that must operate for long durations with little or expensive opportunity for repair or intervention. Specific contributions include: 1) the above methodology, which evaluates responses in system expected performance and availability to changes in static design variables (geometry) and component failure rates, accounting for control design variables (gains) where appropriate, 2) the demonstration of the cost and benefits associated with a multistate design approach as compared to reliability analysis and the nominal design approach, and 3) a multilayer extension of Markov analysis, for translating single sortie vehicle level metrics into measures of multistate campaign performance. The process is demonstrated through three application case studies. The first of these establishes the feasibility of the approach through the multistate analysis of performance for an existing twin-engine aircraft. This analysis was enabled through the development of a multidisciplinary simulation based design model for evaluation of multistate aircraft performance. A medium-altitude long endurance unmanned aerial vehicle is designed in the second case study, first from a single-sortie, ultra long endurance perspective and then from a multiple sortie, mission campaign perspective. Finally, the third case study demonstrates applicability of the approach to a lower level subsystem, that of the lubrication system for a geared turbofan engine. Several major findings result from these case studies, including that: 1) multistate performance output spaces have distinctly unique shapes and boundaries, depending on whether formed through variation of component failure rates, static design variables (geometry), or a multistate combination of both, 2) a region of multistate performance results from the combined variation of failure rates and static design variables that is unachievable through the independent variation of either one, 3) small changes in static design variables may be used to significantly improve system availability, and 4) the general multistate design problem is one of competing objectives between system availability, expected performance, nominal performance, and cost.
by Jeremy S. Agte.
Ph.D.
Hollingsworth, Peter Michael. "Requirements Controlled Design: A Method for Discovery of Discontinuous System Boundaries in the Requirements Hyperspace." Diss., Available online, Georgia Institute of Technology, 2004:, 2004. http://etd.gatech.edu/theses/available/etd-04092004-151914/unrestricted/hollingsworth%5Fpeter%5Fm%5F200405%5Fphd.pdf.
Повний текст джерелаNickol, Craig, Committee Member ; Goodman, Seymour, Committee Member ; Schrage, Daniel, Committee Member ; Craig, James, Committee Member ; Mavris, Dimitri, Committee Chair. Vita. Includes bibliographical references (leaves 272-283).
Papageorgiou, George. "Robust control system design : H∞ loop sharing and aerospace applications." Thesis, University of Cambridge, 1998. https://www.repository.cam.ac.uk/handle/1810/272494.
Повний текст джерелаDaberkow, Debora Daniela. "A formulation of metamodel implementation processes for complex systems design." Diss., Georgia Institute of Technology, 2002. http://hdl.handle.net/1853/12478.
Повний текст джерелаParrish, Jefferson Carter. "Reduced order techniques for sensitivity analysis and design optimization of aerospace systems." Thesis, Mississippi State University, 2014. http://pqdtopen.proquest.com/#viewpdf?dispub=3618312.
Повний текст джерелаThis work proposes a new method for using reduced order models in lieu of high fidelity analysis during the sensitivity analysis step of gradient based design optimization. The method offers a reduction in the computational cost of finite difference based sensitivity analysis in that context.
The method relies on interpolating reduced order models which are based on proper orthogonal decomposition. The interpolation process is performed using radial basis functions and Grassmann manifold projection. It does not require additional high fidelity analyses to interpolate a reduced order model for new points in the design space. The interpolated models are used specifically for points in the finite difference stencil during sensitivity analysis.
The proposed method is applied to an airfoil shape optimization (ASO) problem and a transport wing optimization (TWO) problem. The errors associated with the reduced order models themselves as well as the gradients calculated from them are evaluated. The effects of the method on the overall optimization path, computation times, and function counts are also examined.
The ASO results indicate that the proposed scheme is a viable method for reducing the computational cost of these optimizations. They also indicate that the adaptive step is an effective method of improving interpolated gradient accuracy. The TWO results indicate that the interpolation accuracy can have a strong impact on optimization search direction.
Wu, Marcus Shihong. "Design for affordability in defense and aerospace systems using tradespace-based methods." Thesis, Massachusetts Institute of Technology, 2014. http://hdl.handle.net/1721.1/89937.
Повний текст джерелаThesis: S.M. in Technology and Policy, Massachusetts Institute of Technology, Engineering Systems Division, Technology and Policy Program, 2014.
Cataloged from PDF version of thesis.
Includes bibliographical references (pages 262-270).
Program failures have plagued the defense and aerospace industry for decades, as unanticipated cost and schedule overruns have rendered the development of systems ineffective in terms of time and cost considerations. This raises the need to holistically include performance, cost and schedule considerations during the early-phase design of systems to perform valuable tradeoffs that derive more feasible and affordable solutions. This paradigm is the design for affordability. This design for affordability conundrum is targeted at defense and aerospace systems, which have complex mission requirements and stakeholder involvement that are susceptible to changes and perturbations over time. Without a systematic framework, the design for affordability process can potentially become cognitively challenging to system architects and lead to unsatisfactory results. To resolve affordability, it can first be defined as the property of becoming or remaining feasible relative to resource needs and resource constraints over time. Affordability can then be treated as an ility that drives the design of more affordable yet technically sound architectures. Tradespace-based methods are introduced to drive affordability and incorporate these holistic considerations into the design process. They facilitate the systematic and disciplined search for affordable solutions to the system, program and portfolio of interest. Multi-Attribute Tradespace Exploration (MATE), Epoch-Era Analysis (EEA) and the Multi-Attribute Expense (MAE) function were modified for affordability analysis. Their feasibility was demonstrated through application to two design case studies. Results from both case studies demonstrated the dynamic tradeoffs among performance, cost and schedule parameters. Tradespace-based methods can thus be applied to the progressive design of systems, programs and portfolios using either a bottom-up or top-down approach to deliver affordable solutions in these cases. Affordability is not only an engineering problem; it is also a policy and management problem. Therefore, affordability can be approached through perspectives beyond engineering design. New policies and refined management practices can be used alongside tradespace-based methods for affordability analysis to ensure the continued delivery of affordable systems for the future.
by Marcus Shihong Wu.
S.M.
S.M. in Technology and Policy
Hebbal, Ali. "Deep gaussian processes for the analysis and optimization of complex systems : application to aerospace system design." Thesis, Lille, 2021. http://www.theses.fr/2021LILUI016.
Повний текст джерелаIn engineering, the design of complex systems, such as aerospace launch vehicles, involves the analysis and optimization of problems presenting diverse challenges. Actually, the designer has to take into account different aspects in the design of complex systems, such as the presence of black-box computationally expensive functions, the complex behavior of the optimized performance (e.g., abrupt change of a physical property here referred as non-stationarity), the multiple objectives and constraints involved, the multi-source information handling in a multi-fidelity framework, and the epistemic and aleatory uncertainties affecting the physical models. A wide range of machine learning methods are used to address these various challenges. Among these approaches, Gaussian Processes (GPs), benefiting from their Bayesian and non-parametric formulation, are popular in the literature and diverse state-of-the-art algorithms for the design of complex systems are based on these models.Despite being widely used for the analysis and optimization of complex systems, GPs, still present some limitations. For the optimization of computationally expensive functions, GPs are used within the Bayesian optimization framework as regression models. However, for the optimization of non-stationary problems, they are not suitable due to the use of a prior stationary covariance function. Furthermore, in Bayesian optimization of multiple objectives, a GP is used for each involved objective independently, which prevents the exhibition of a potential correlation between the objectives. Another limitation occurs in multi-fidelity analysis where GP-based models are used to improve high-fidelity models using low-fidelity information. However, these models usually assume that the different fidelity input spaces are identically defined, which is not the case in some design problems.In this thesis, approaches are developed to overcome the limits of GPs in the analysis and optimization of complex systems. These approaches are based on Deep Gaussian Processes (DGPs), the hierarchical generalization of Gaussian processes.To handle non-stationarity in Bayesian optimization, a framework is developed that couples Bayesian optimization with DGPs. The inner layers allow a non-parametric Bayesian mapping of the input space to better represent non-stationary functions. For multi-objective Bayesian optimization, a multi-objective DGP model is developed. Each layer of this model corresponds to an objective and the different layers are connected with undirected edges to encode the potential correlation between objectives. Moreover, a computational approach for the expected hyper-volume improvement is proposed to take into account this correlation at the infill criterion level as well. Finally, to address multi-fidelity analysis for different input space definitions, a two-level DGP model is developed. This model allows a joint optimization of the multi-fidelity model and the input space mapping between fidelities.The different approaches developed are assessed on analytical problems as well as on representative aerospace vehicle design problems with respect to state-of-the-art approaches
Sar, Preeti. "Eco-Inspired Robust Control Design Algorithm For Linear Systems with Real Parameter Uncertainty." The Ohio State University, 2013. http://rave.ohiolink.edu/etdc/view?acc_num=osu1367439491.
Повний текст джерелаDiller, Nathan P. (Nathan Philip) 1978. "Utilizing Multiple Attribute Tradespace Exploration with Concurrent Design for creating aerospace systems requirements." Thesis, Massachusetts Institute of Technology, 2002. http://hdl.handle.net/1721.1/83680.
Повний текст джерелаTseng, Yuan-Wei. "Control design of linear dynamic systems with matrix differential equations for aerospace applications /." The Ohio State University, 1997. http://rave.ohiolink.edu/etdc/view?acc_num=osu1487943610783999.
Повний текст джерелаBandte, Oliver. "A probabilistic multi-criteria decision making technique for conceptual and preliminary aerospace systems design." Diss., Georgia Institute of Technology, 2000. http://hdl.handle.net/1853/12503.
Повний текст джерелаKnox, Lenora A. "Use of Model-Based Design Methods for Enhancing Resiliency Analysis of Unmanned Aerial Vehicles." Thesis, The George Washington University, 2017. http://pqdtopen.proquest.com/#viewpdf?dispub=10265223.
Повний текст джерелаThe most common traditional non-functional requirement analysis is reliability. With systems becoming more complex, networked, and adaptive to environmental uncertainties, system resiliency has recently become the non-functional requirement analysis of choice. Analysis of system resiliency has challenges; which include, defining resilience for domain areas, identifying resilience metrics, determining resilience modeling strategies, and understanding how to best integrate the concepts of risk and reliability into resiliency. Formal methods that integrate all of these concepts do not currently exist in specific domain areas. Leveraging RAMSoS, a model-based reliability analysis methodology for Systems of Systems (SoS), we propose an extension that accounts for resiliency analysis through evaluation of mission performance, risk, and cost using multi-criteria decision-making (MCDM) modeling and design trade study variability modeling evaluation techniques. This proposed methodology, coined RAMSoS-RESIL, is applied to a case study in the multi-agent unmanned aerial vehicle (UAV) domain to investigate the potential benefits of a mission architecture where functionality to complete a mission is disseminated across multiple UAVs (distributed) opposed to being contained in a single UAV (monolithic). The case study based research demonstrates proof of concept for the proposed model-based technique and provides sufficient preliminary evidence to conclude which architectural design (distributed vs. monolithic) is most resilient based on insight into mission resilience performance, risk, and cost in addition to the traditional analysis of reliability.
Thomas, Victoria Katherine. "A Method for Scenario-based Risk Assessment for Robust Aerospace Systems." Diss., Georgia Institute of Technology, 2007. http://hdl.handle.net/1853/14536.
Повний текст джерелаSaranathan, Harish. "Algorithmic Advances to Increase the Fidelity of Conceptual Hypersonic Mission Design." Thesis, Purdue University, 2018. http://pqdtopen.proquest.com/#viewpdf?dispub=10792495.
Повний текст джерелаThe contributions of this dissertation increase the fidelity of conceptual hypersonic mission design through the following innovations: 1) the introduction of coupling between the effects of ablation of the thermal protection system (TPS) and flight dynamics, 2) the introduction of rigid body dynamics into trajectory design, and 3) simplifying the design of hypersonic missions that involve multiple phases of flight. These contributions are combined into a unified conceptual mission design framework, which is in turn applicable to slender hypersonic vehicles with ablative TPS. Such vehicles are employed in military applications, wherein speed and terminal energy are of critical importance.
The fundamental observation that results from these contributions is the substantial reduction in the maximum terminal energy that is achievable when compared to the state-of-the art conceptual design process. Additionally, the control history that is required to follow the maximum terminal energy trajectory is also significantly altered, which will in turn bear consequence on the design of the control actuators.
The other important accomplishment of this dissertation is the demonstration of the ability to solve these class of problems using indirect methods. Despite being built on a strong foundation of the calculus of variations, the state-of-the-art entirely neglects indirect methods because of the challenge associated with solving the resulting boundary value problem (BVP) in a system of differential-algebraic equations (DAEs). Instead, it employs direct methods, wherein the optimality of the calculated trajectory is not guaranteed. The ability to employ indirect methods to solve for optimal trajectories that are comprised of multiple phases of flight while also accounting for the effects of ablation of the TPS and rigid body dynamics is a substantial advancement in the state-of-the-art.
Miao, Cheng Hsi. "The design of phased synthetic aperture imaging systems using a minimum number of elements." Diss., The University of Arizona, 1991. http://hdl.handle.net/10150/185625.
Повний текст джерелаBradley, Thomas Heenan. "Modeling, design and energy management of fuel cell systems for aircraft." Diss., Atlanta, Ga. : Georgia Institute of Technology, 2008. http://hdl.handle.net/1853/26592.
Повний текст джерелаCommittee Chair: Parekh, David; Committee Member: Fuller, Thomas; Committee Member: Joshi, Yogendra; Committee Member: Mavris, Dimitri; Committee Member: Wepfer, William. Part of the SMARTech Electronic Thesis and Dissertation Collection.
Paxton, Brendan. "Systems Design and Experimental Evaluation of a High-Altitude Relight Test Facility." University of Cincinnati / OhioLINK, 2015. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1448037233.
Повний текст джерелаSolodilova-Whiteley, I. "A design strategy for human-system integration in aerospace : where to start and how to design information integration for dynamic, time and safety critical systems." Thesis, University of Bath, 2005. https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.428372.
Повний текст джерелаMarchiori, Rodolfo Henrique. "Framework Design for System of Systems : A Bottom Up Approach Applied to Search and Rescue Missions." Thesis, Linköpings universitet, Fluida och mekatroniska system, 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-149607.
Повний текст джерелаJackson, David Wayne. "Robust aircraft subsystem conceptual architecting." Diss., Georgia Institute of Technology, 2013. http://hdl.handle.net/1853/50202.
Повний текст джерелаChoi, Taeyun Paul. "A recourse-based solution approach to the design of fuel cell aeropropulsion systems." Diss., Atlanta, Ga. : Georgia Institute of Technology, 2008. http://hdl.handle.net/1853/22676.
Повний текст джерелаCommittee Chair: Mavris, Dimitri; Committee Member: German, Brian; Committee Member: Haynes, Comas; Committee Member: Masson, Philippe; Committee Member: Soban, Danielle.
Yuan, Xin. "Model-based feedback control of subsonic cavity flows - control design." Columbus, Ohio : Ohio State University, 2006. http://rave.ohiolink.edu/etdc/view?acc%5Fnum=osu1158032317.
Повний текст джерелаBelben, Joel Brian. "ENABLING RAPID CONCEPTUAL DESIGN USING GEOMETRY- BASED MULTI-FIDELITY MODELS IN VSP." DigitalCommons@CalPoly, 2013. https://digitalcommons.calpoly.edu/theses/969.
Повний текст джерелаMiller, Adam J. "Methodology for Cost Estimation of Systems at a Preliminary Stage of Design." Ohio University / OhioLINK, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=ohiou1344259852.
Повний текст джерелаDevarakonda, Nagini. "Eco-inspired Robust Control Design for Linear Dynamical Systems with Applications." The Ohio State University, 2011. http://rave.ohiolink.edu/etdc/view?acc_num=osu1313519615.
Повний текст джерелаRichardson, Matthew. "Mass Estimation through Fusion of Astrometric and Photometric Data Collection with Application to High Area-to-Mass Ratio Objects." DigitalCommons@CalPoly, 2017. https://digitalcommons.calpoly.edu/theses/1742.
Повний текст джерелаSeitz, Timothy M. "Linearizing and Distributing Engine Models for Control Design." The Ohio State University, 2013. http://rave.ohiolink.edu/etdc/view?acc_num=osu1373728747.
Повний текст джерелаYost, Morgan. "An Iteration on the Horizon Simulation Framework to Include .NET and Python Scripting." DigitalCommons@CalPoly, 2016. https://digitalcommons.calpoly.edu/theses/1607.
Повний текст джерелаUmaretiya, Jagdish R. "Specifications extraction and synthesis: Their correlations with preliminary design." Diss., The University of Arizona, 1990. http://hdl.handle.net/10150/185035.
Повний текст джерелаFulcher, Jared T. "A DESIGN PATHFINDER WITH MATERIAL CORRELATION POINTS FOR INFLATABLE SYSTEMS." UKnowledge, 2014. http://uknowledge.uky.edu/me_etds/39.
Повний текст джерелаMincolla, Andrea. "Space Systems of Systems Generative Design Using Concurrent MBSE: An Application of ECSS-E-TM-10-25 and the GCD Tool to Copernicus Next Generation." Thesis, KTH, Rymdteknik, 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-286332.
Повний текст джерелаConcurrent Design Platform 4 (CDP4®) är ett samarbetsverktyg för modellbaserad systemteknik (MBSE) som utformats för att bygga komplexa system. Dock finns det begränsningar vad gäller det antalet hanterbara systemalternativ. Det kommande Siemens-verktyget för generativ teknik, Simcenter™ Studio, försöker övervinna denna begränsning genom att möjliggöra automatisk syntes och utvärdering av arkitekturvarianter. Motivationen för Generative Concurrent Design (GCD) -projektet som ett samarbete mellan RHEA, Siemens och OHB är att utveckla en kombinerad prototyp av verktygen CDP4® och Simcenter™. Detta examensarbete presenterar en modellering av rymdkomponenten Copernicus Next Generation (CNG) med användning av generativa funktioner i en typisk fas-0-studie. Den representerar det tredje steget i GCD-valideringsprocessen nedifrån och upp, avsedd att undersöka hur arkitekturen skiljer sig åt mellan "Sub-system", "Systems" och "Systems of Systems (SoS)". Detta arbete ger därför en arkitektonisk strategi som är generaliserbar för andra SoS-användningsfall och bidrar till att bedöma om förlängningar till ECSS-E-TM-10-25 är nödvändiga för att framgångsrikt stödja GCD.
McDonough, Laura. "Receptance Based Control of Aeroelastic Systems for Flutter Suppression." Miami University / OhioLINK, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=miami1355500262.
Повний текст джерелаMcCrink, Matthew H. "Development of Flight-Test Performance Estimation Techniques for Small Unmanned Aerial Systems." The Ohio State University, 2015. http://rave.ohiolink.edu/etdc/view?acc_num=osu1449142886.
Повний текст джерелаBurt, Colin. "Design, Fabrication and Test of an Operationally Responsive Aircraft with NIIRS Evaluated Imager." DigitalCommons@CalPoly, 2013. https://digitalcommons.calpoly.edu/theses/1087.
Повний текст джерелаPatel, Viren Kishor. "SysML Output Interface and System-Level Requirement Analyzer for the Horizon Simulation Framework." DigitalCommons@CalPoly, 2018. https://digitalcommons.calpoly.edu/theses/1834.
Повний текст джерелаChandavarkar, Rohan Vivek. "Eco-inspired Robust Control Design for Linear Time-Invariant systems with Real Parameter Uncertainty." The Ohio State University, 2013. http://rave.ohiolink.edu/etdc/view?acc_num=osu1373467190.
Повний текст джерелаHektor, Oskar. "Review of Present Systems and Costs of Conceptual Designs of UAV:s for Humanitarian Relief Missions." Thesis, KTH, Flygdynamik, 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-240955.
Повний текст джерелаSyftet med den här studien har varit att undersöka möjligheterna för att använda drönare till att leverera humanitär hjälp. Att ge humanitär hjälp innebär att man assisterar stater i att leverera nödvändiga varor och tjänster till områden där den nationella staten behöver assistans för att upprätthålla nödvändiga livsvillkor för befolkningen. Det kan vara att leverera mat och mediciner men även enklare skolmateriel eller liknande. Oftast är orsaken bakom en humanitär insats att det skett någon typ av katastrof, det kan vara både natur och mänskligt skapade katastrofer. Ett exempel på en sådan nylig kris har varit inbördeskriget som rasat i Syrien under större delen av 2010-talet. Ett problem som har dykt upp är att det är svårt att få fram rätt hjälp dit den behövs, speciellt om de civila som har behovet befinner sig i en krigszon. I ett sådant fall är det mycket riskabelt att transportera och leverera humanitär hjälp till de som behöver det. De riskerar att bli skjutna, kidnappade och kapade. Detta skapar både personliga och materiella skador. Frågan blir då om man skulle kunna leverera den hjälpen med drönare, för att minska risken för personskador men också minska effekten för hela hjälpinsatsen om en eller flera av drönare skulle förvinna. Det som komplicerar hela i logistiken är att man måste ta hänsyn till hur personer byter besittning av godsen och hur man verifierar att varje person får just rätt hjälp. Speciellt då värdet av godset i en kris kan bli asymptotiskt högt. För att testa huruvida det är möjligt att använda UAV:er för humanitär hjälp skapades en simuleringsmodell av en drönare. Eftersom det förväntades att ett uppdrag är ungefär 300 km + 300km tur-o-retur övergavs någon typ av helikopterdesign tidigt. Modellen simulerade många uppdrag som bedömdes vara relevanta för en UAV som skulle leverera humanitär hjälp. Utifrån dessa uppdrag bedömdes några av de operativa kostnader som var knutna till uppdragen. Det gäller främst tillverkningskostnader, bränslekostnader samt avgifter som behöver betalas av den som använder luftrummet. Det finns en bok som är flygplanskonstruktörens bibel (Aircraft Design). Den är skriven av Daniel P. Raymer. Han föreslår där en formel för hur man konceptuellt kan bestämma vikten av ett nytt flygplan. De befintliga planen jämfördes sedan med formeln för att undersöka om dessa också stämde på drönare. Eftersom drönare inte har piloter ombord innebär det att vissa apparater inte behöver finnas på det flygplanet, vilket kan tänkas ändra hur mycket en UAV estimeras väga jämfört med ett vanligt plan. Studien kommer fram till att det som Raymer har föreslagit verkar för det mesta vara rättvisande även när man designar UAV:er. Avslutningsvis identifieras tre olika drönare som med mer eller mindre modifiering skulle kunna användas för humanitära insatser. Dock är, som nämnt tidigare, de flesta UAV:er utvecklade för olika typer av informationssamling. Då flera av dessa apparater inte är lika nödvändiga i en humanitär-logistisk situation är det sannolikt att inköpspriset skulle vara billigare än annars. Slutsatserna är att det nu är tekniskt möjligt att använda drönare för humanitär hjälp, ekonomiskt är det möjligt om än dyrt men juridiskt är det i dagsläget inte möjligt. Juridiken och reglementet för hur avgiftssystemet och luftrummet fungerar behöver utvecklas för att på ett hållbart och säkert sätt integrera autonoma farkoster med befintlig luftfart. Beroende på hur regleringarna av luftrummet förändras, ändras även de ekonomiska förutsättningarna för att använda drönare för att utföra logistiska uppdrag.
Fabbri, Riccardo. "Conceptualization, design & simulation of a small asteroid probe." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2019.
Знайти повний текст джерелаAshley, Eric. "A System Architecture for Phased Development of Remote sUAS Operation." DigitalCommons@CalPoly, 2020. https://digitalcommons.calpoly.edu/theses/2138.
Повний текст джерелаCheney, Liam Jon. "Development of Safety Standards for CubeSat Propulsion Systems." DigitalCommons@CalPoly, 2014. https://digitalcommons.calpoly.edu/theses/1180.
Повний текст джерелаFern, Lisa C. "A Cognitive Systems Engineering Approach to Developing Human Machine Interface Requirements for New Technologies." The Ohio State University, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=osu1461248106.
Повний текст джерелаD'Anniballe, Alessandro. "Development of a sizing tool for preliminary mission analysis and design of propulsion systems for orbit control of small satellites in LEO -VLEO." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2017. http://amslaurea.unibo.it/14719/.
Повний текст джерелаAshworth, Geoffrey (Geoffrey John). "Architectural disruption in aerospace." Thesis, Massachusetts Institute of Technology, 2009. http://hdl.handle.net/1721.1/55202.
Повний текст джерелаCataloged from PDF version of thesis.
Includes bibliographical references (p. 70-71).
Distinctive technology and customer / supplier relationships are currently the primary sources of competitive advantage in the Aerospace industry. Modular Open System Architecture (MOSA) requirements represent a significant disruption to this mode of competition. The United States Department of Defense intends to accelerate the rate of aerospace innovation and inject additional competitiveness into the procurement process through the modularization of its products and effective intellectual property management. This combination of architectural disruption and new customer capabilities has the potential to reduce the industry's opportunity to capture value from innovative technologies or a position as first supplier. Historical examples such as Polaroid and IBM demonstrate the organizational paralysis that often results from disruptions in product architecture. The competitive formula becomes ingrained in the processes, resources, and culture of mature companies and is no longer explicit knowledge, which limits the company's ability to develop the capabilities required to compete in its new environment. Competing in a MOSA environment will require the development of new organizational capabilities such as rapid experimentation, fighting standards wars, and protecting system-level knowledge. Defining the disruptive threat and the foundations of current core competencies will enable firms to develop the organizational capabilities essential for this shift in competitive context.
(cont.) The author will present several historical examples of architectural disruption, a framework for evaluating the disruptive change, and an identification of organizational anchors that may hinder a particular competitor's ability to respond to MOSA. The goal of the thesis is to start a dialogue within an identified incumbent with in hopes of beginning the organizational transformation required to effectively compete in this new era.
by Geoffrey Ashworth.
S.M.
Chalker, Jack Randolph. "Design and Manipulation of a Power-Generating System with High-Temperature Fuel Cells for Hypersonic Applications." Wright State University / OhioLINK, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=wright1567169603256774.
Повний текст джерела