Bibliographies thématiques / Mission design and analysi

Littérature scientifique sur le sujet « Mission design and analysi »

Auteur : Grafiati
Publié le 14 mars 2023

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Articles de revues sur le sujet "Mission design and analysi"

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Negi, Kuldeep, B. S. Kiran et Satyendra Kumar Singh. « Mission Design and Analysis for Mars Orbiter Mission ». Journal of the Astronautical Sciences 67, no 3 (2 décembre 2019) : 932–49. http://dx.doi.org/10.1007/s40295-019-00199-8.

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Musiał, Alicja, Dominik Markowski, Jan Życzkowski et Krzysztof A. Cyran. « Analysis of Methods for CubeSat Mission Design Based on in-orbit Results of KRAKsat Mission ». International Journal of Education and Information Technologies 15 (21 septembre 2021) : 295–302. http://dx.doi.org/10.46300/9109.2021.15.31.

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The success rate of currently performed CubeSat missions shows that despite their popularity, small satellites are still not as reliable as larger platforms. This research was conducted to analyse in-orbit experience from the KRAKsat mission and discuss methods for mission design and engineering that can increase CubeSats reliability and prevent their failures. The main purpose was to define best practices and rules that should be followed during mission development and operations to ensure its success based on the overview of the lessons learned from KRAKsat and problems encountered during its mission. This paper summarizes the experiences obtained and provides methods that can be used while carrying out future robust CubeSat projects. It was written to prove that there are some parts of the small satellite missions that are often neglected in the university-led projects and, by ensuring proper testing and planning before the actual mission, its reliability can increase. The following analysis could be used as a guide during the development of the next CubeSat projects.
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Landgraf, Markus, Florian Renk et Bram de Vogeleer. « Mission design and analysis of European astrophysics missions orbiting libration points ». Acta Astronautica 84 (mars 2013) : 49–55. http://dx.doi.org/10.1016/j.actaastro.2012.10.005.

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Cornara, Stefania, Theresa W. Beech, Miguel Belló-Mora et Guy Janin. « Satellite constellation mission analysis and design ». Acta Astronautica 48, no 5-12 (mars 2001) : 681–91. http://dx.doi.org/10.1016/s0094-5765(01)00016-9.

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Weber, A., S. Fasoulas et K. Wolf. « Conceptual interplanetary space mission design using multi-objective evolutionary optimization and design grammars ». Proceedings of the Institution of Mechanical Engineers, Part G : Journal of Aerospace Engineering 225, no 11 (9 septembre 2011) : 1253–61. http://dx.doi.org/10.1177/0954410011407421.

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Conceptual design optimization (CDO) is a technique proposed for the structured evaluation of different design concepts. Design grammars provide a flexible modular modelling architecture. The model is generated by a compiler based on predefined components and rules. The rules describe the composition of the model; thus, different models can be optimized by the CDO in one run. This allows considering a mission design including the mission analysis and the system design. The combination of a CDO approach with a model based on design grammars is shown for the concept study of a near-Earth asteroid mission. The mission objective is to investigate two asteroids of different kinds. The CDO reveals that a mission concept using two identical spacecrafts flying to one target each is better than a mission concept with one spacecraft flying to two asteroids consecutively.
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Kim, Hongrae, Byung-Il Jeon, Narae Lee, Seong-Dong Choi et Young-Keun Chang. « Development of Mission Analysis and Design Tool for ISR UAV Mission Planning ». Journal of the Korean Society for Aeronautical & ; Space Sciences 42, no 2 (1 février 2014) : 181–90. http://dx.doi.org/10.5139/jksas.2014.42.2.181.

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Shen, Diyang, Yuxian Yue et Xiaohui Wang. « Manned Mars Mission Analysis Using Mission Architecture Matrix Method ». Aerospace 9, no 10 (14 octobre 2022) : 604. http://dx.doi.org/10.3390/aerospace9100604.

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With the development of deep space exploration technology, manned missions to Mars are expected to be realized in the near future. However, the journey to Mars requires more supplies and fuel than near-Earth missions, including moon landings. Using the traditional Apollo-style mission method will result in the spacecraft reaching the LEO mass of 2000 tons, which is not easy to achieve. The use of the modular design method and multiple launches will significantly reduce the mass of a single launch. In addition, the use of nuclear power engines (Nuclear Thermal Propulsion, NTP, and Nuclear Electric Propulsion, NEP) can greatly improve propulsion efficiency, reducing the mass of the propellant. This paper uses the Mission Architecture Matrix (MAM) method to concisely and precisely analyze a series of mission architectures in the case of impulse maneuver transfer and low-thrust transfer. The results show that when only chemical propulsion (specific impulse is 440s) is used, the maximum LEO launch mass in the optimal mission architecture is 325 tons, and the total LEO mass of the system is 1142 tons. With the usage of NTP (specific impulse is 900s) and NEP (the specific impulse is 6000s) technology, the maximum LEO launch mass in the optimal mission architecture is only 85 tons, and the total LEO mass of the system is only about 400 tons. Considering the current rocket technology, the total cost is about USD 1149 million US.
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Jafarsalehi, A., HR Fazeley et M. Mirshams. « Spacecraft mission design optimization under uncertainty ». Proceedings of the Institution of Mechanical Engineers, Part C : Journal of Mechanical Engineering Science 230, no 16 (8 août 2016) : 2872–87. http://dx.doi.org/10.1177/0954406215603416.

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The design of space systems is a complex and multidisciplinary process. In this study, two deterministic and nondeterministic approaches are applied to the system design optimization of a spacecraft which is actually a small satellite in low Earth orbit with remote sensing mission. These approaches were then evaluated and compared. Different disciplines such as mission analysis, payload, electrical power supply, mass model, and launch manifest were properly combined for further use. Furthermore, genetic algorithm and sequential quadratic programming were employed as the system-level and local-level optimizers. The main optimization objective of this study is to minimize the resolution of the satellite imaging payload while there are several constraints. A probabilistic analysis was performed to compare the results of the deterministic and nondeterministic approaches. Analysis of the results showed that the deterministic approaches may lead to an unreliable design (because of leaving little or no room for uncertainties), while using the reliability-based multidisciplinary design optimization architecture, all probabilistic constraints were satisfied.
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Tokadlı, Güliz, et Michael C. Dorneich. « Development of Design Requirements for a Cognitive Assistant in Space Missions Beyond Low Earth Orbit ». Journal of Cognitive Engineering and Decision Making 12, no 2 (12 octobre 2017) : 131–52. http://dx.doi.org/10.1177/1555343417733159.

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This study describes the development of requirements for a cognitive assistant (CA) for use onboard a space vehicle/station. For missions beyond low Earth orbit (LEO), delayed communication will limit mission control’s ability to support the space crew in real time. During off-nominal situations, where no procedures have been developed prior to missions, crews must develop responses in real time and may increasingly rely on automation. A systematic approach was used to model the domain knowledge of the collaborative decision-making process of current space operations, extrapolate to missions beyond LEO, and develop the design requirements for a CA. Document analysis and interviews were conducted to create an abstraction hierarchy and a decision-action diagram of the cognitive functions currently performed by space crew, mission control, and onboard automation. These domain models were extrapolated to missions beyond LEO by identifying the breakpoints where current decision-making processes would break down due to increased communication delay between mission control and the space crew. Design requirements were identified for future CA systems that offer real-time decision-making support to mitigate the negative effect of limited support in off-nominal situations. The approach developed for this research can be generalized to identify the design requirements for future support systems in domains beyond space operations.
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Zenk, Leslie R., et Karen Seashore Louis. « Mission as Metaphor : Reconceptualizing how Leaders Utilize Institutional Mission ». Teachers College Record : The Voice of Scholarship in Education 120, no 9 (septembre 2018) : 1–34. http://dx.doi.org/10.1177/016146811812000907.

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Background/Context Institutional missions serve many purposes within universities, but most studies focus on how mission points to direction, guidelines, or priorities. However, organizational missions have been shown to have other functions such as instructing members about actions or behaviors that are acceptable. This paper therefore examines texts for evidence of how respondents’ ideas about mission go beyond just a statement of direction or priorities. Purpose/Objective/Research Question/Focus of Study To consider the use of metaphor in describing institutional mission, the following research questions were examined: 1. How are metaphors used to describe institutional mission? 2. What function(s) is the discourse around institutional mission being used to serve? Research Design The study is a discourse analysis of written texts and interview transcripts as part of a qualitative, comparative case study of six master's-granting institutions that are campuses within one state's public university system. Data Collection and Analysis Interviews were conducted with 36 university leaders including chief academic officers, deans, department chairs, and faculty members including at least one: (a) member of the institution's body of collegiate deans, (b) department chair and/or collegiate dean directly involved in decision making, and (c) current and/or previous president of the faculty governance body. Qualitative data analysis was conducted using an iterative data analysis method drawing from grounded theory and constant comparative analysis. Following qualitative analysis, a subsequent word count was conducted to determine the extent to which the metaphors were used. Conclusions/Recommendations Results suggest mission is a socially constructed phenomenon with a variety of different functions revealed through metaphor that engage different audiences and are closely tied to institutional context and purpose. Metaphors of mission articulated by respondents include mission as: (a) symbolic unity, (b) boundary object, (c) tool, (d) cage, (e) metamorphosis, (f) cultural artifact, (g) motivator, (h) authoritative text, (i) transaction, and (j) treaty document. Understanding the complexities of institutional mission suggests a need to reconsider it and the ways in which leaders engage with their institutional missions.
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Thèses sur le sujet "Mission design and analysi"

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Shastri, Bhardwaj. « Design and analysis of mission and system requirements for 'NetSat' mission with respect to structural and thermal limitations ». Thesis, Luleå tekniska universitet, Rymdteknik, 2019. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-76336.

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In the scope of this master thesis work, the proposed design for NetSat was analyzed for mission and system requirements with respect to structural and thermal limitations. Different load case scenarios for structural and thermal analysis were considered during the process which have been discussed. Based on results, the design is qualified and expected to satisfy all mission and system requirements with regards to structural and thermal limitations.
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Tanapura, Noravidhya. « Preliminary Mission Analysis and Design for a Small Satellite SWARM ». Thesis, KTH, Rymd- och plasmafysik, 2012. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-104032.

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The thesis is a preliminary mission analysis and design of a small satellite swarm. The concept of the mission is to probe altitudes between 200 km and 6000 km to study the structures and dynamics of the magnetic field aligned currents. The mission lifetime is about 3 months. Aerodynamic drag at low altitudes is used for orbit and formation control. During the perigee passage, the satellite would decelerate due to drag, therefore, reducing its apogee. In addition, the attitude control of the spacecraft during the perigee passage could be used for formation control by changing its cross-sectional area. The simulations indicated that an appropriate insertion orbit should be at the perigee of 168 km and an apogee of 6000km. Moreover, from the orbital decay simulations, it was found that by maintaining a constant ram-facing area of 0.1 m2, it is possible for the satellite to decay in 90 days. The attitude simulations show that for at least one perigee passage at a perigee altitude of 168 km, the satellite is able to maintain its attitude and not tumble throughout the trajectory. In addition, investigation of the leader-follower satellite formation yielded that the relative translation of a circular orbit oscillates in all relative directions whereas in an elliptical orbit it only oscillates in the cross-track direction. Furthermore, the simulation has also shown that the relative translation of a leader-follower formation with a elliptical reference orbit, would spiral out of the radial-cross-track plane.
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Unlusoy, Levent. « Structural Design And Analysis Of The Mission Adaptive Wings Of An Unmanned Aerial Vehicle ». Master's thesis, METU, 2010. http://etd.lib.metu.edu.tr/upload/12611515/index.pdf.

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In this study, the structural design and analysis of a wing having mission-adaptive control surfaces were conducted. The wing structure was designed in order to withstand a maximum aerodynamic loading of 5 g due to maneuver. The structural model of the wing was developed by using MSC/PATRAN package program and that structural model was analyzed by using MSC/NASTRAN package program. The designed wing was then manufactured by Turkish Aerospace Industries Inc. (TUSAS-TAI). The finite element analysis results were verified by conducting ground vibration tests on the manufactured wing. The comparative results were used to tune the finite element model and the results obtained showed that the modeling was very successful.
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Kim, Susan C. (Susan Cecilia). « Mission design and trajectory analysis for inspection of a host spacecraft by a microsatellite ». Thesis, Massachusetts Institute of Technology, 2006. http://hdl.handle.net/1721.1/37566.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2006.
Includes bibliographical references (p. 177-179).
The trajectory analysis and mission design for inspection of a host spacecraft by a microsatellite is motivated by the current developments in designing and building prototypes of a microsatellite inspector vehicle. Two different, mission scenarios are covered in this thesis - a host spacecraft in orbit about Earth and in deep space. Some of the key factors that affect the design of an inspection mission are presented and discussed. For the Earth orbiting case, the range of available trajectories - natural and forced - is analyzed using the solution to the Clohessy-Wiltshire (CW) differential equations. Utilizing the natural dynamics for inspection minimizes fuel costs, while still providing excellent opportunities to inspect and image the surface of the host spacecraft. The accessible natural motions are compiled to form a toolset, which may be employed in planning an inspection mission. A baseline mission concept for a microsatellite inspector is presented in this thesis. The mission is composed of four primary modes: deployment mode, global inspection mode, point inspection mode, and disposal mode. Some figures of merit that may be used to rate the success of the inspection mission are also presented.
(cont.) A simulation of the baseline mission concept for the Earth orbiting scenario is developed from the trajectory toolset. The hardware simulation is based on the current microinspector hardware developments at the Jet Propulsion Laboratory. Through the figures of merit, the quality of the inspection mission is shown to be excellent, when the natural dynamics are utilized for trajectory design. The baseline inspection mission is also extended to the deep space case.
by Susan C. Kim.
S.M.
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Paris, Bethany L. « INSTITUTIONAL LENDING MODELS, MISSION DRIFT, AND MICROFINANCE INSTITUTIONS ». UKnowledge, 2013. http://uknowledge.uky.edu/msppa_etds/9.

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Microfinance is a development tool used to reduce poverty among extremely poor households. Impoverished households can access lines of credit through microfinance institutions (MFIs), in order to create a new business, smooth household consumption, fund medical emergencies, etc. Many authors postulate that MFIs are drifting from a welfarist to an institutionalist approach to lending. Using MIXMarket data on specific MFIs in 118 countries between 1995 and 2011, the average loan balance of these organizations will be regressed against measure of outreach and sustainability of these institutions by charter type through a series of four, fixed effects models. The main research question is: given that a positive, overall shift in average loan balance indicates an institutionalist shift in mission, how does this impact microfinance institutions and the demographics they target on the intensive and extensive margins? These analyses will test the theory that MFIs with larger average loan balances serve households closer to the subsistence poverty level, a manifestation of mission drift toward the institutionalist philosophy of lending. The phenomenon of mission drift directly impacts the outcomes of microfinance institutions and the target demographic of the organization. The results of this study indicate that the mission of these organizations is drifting toward the institutionalist philosophy of lending. With this general result, mission drift can be observed within both the internal and external margins of the microfinance industry, which influences the chosen target market, profit generated, and structure of MFIs, as determined by the mission of the organization.
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Insuyu, Erdogan Tolga. « Aero-structural Design And Analysis Of An Unmanned Aerial Vehicle And Its Mission Adaptive Wing ». Master's thesis, METU, 2010. http://etd.lib.metu.edu.tr/upload/12611657/index.pdf.

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This thesis investigates the effects of camber change on the mission adaptive wing of a structurally designed unmanned aerial vehicle (UAV). The commercial computational fluid dynamics (CFD) software ANSYS/FLUENT is employed for the aerodynamic analyses. Several cambered airfoils are compared in terms of their aerodynamic coefficients and the effects of the camber change formed in specific sections of the wing on the spanwise pressure distribution are investigated. The mission adaptive wing is modeled structurally to observe the effect of spanwise pressure distribution on the wing structure. For the structural design and analysis of the UAV under this study, commercial software MSC/PATRAN and MSC/NASTRAN are used. The structural static and dynamic analyses of the unmanned aerial vehicle are also performed under specified flight conditions. The results of these analyses show that the designed structure is safe within the flight envelope. Having completed aero-structural design and analysis, the designed unmanned aerial vehicle is manufactured by TUSAS Aerospace Industries (TAI).
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Zimmer, Aline [Verfasser]. « Mission Analysis and Conceptual Spacecraft Design for Human Exploration of Near-Earth Asteroids / Aline Zimmer ». München : Verlag Dr. Hut, 2012. http://d-nb.info/1029400342/34.

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Cucciarrè, Francesca. « Numerical and experimental methods for design and test of units and devices on BepiColombo Mission ». Doctoral thesis, Università degli studi di Padova, 2013. http://hdl.handle.net/11577/3423379.

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In this thesis work several numerical and experimental methods for design and test of units and devices onboard BepiColombo Mission are studied, implemented and described. BepiColombo Mission is the result of the joined efforts of European Space Agency and Japanese Space Agency: in 2015 two different orbiters (ESA Mercury Planetary Orbiter, MPO, which will support remote sensing and radio-science instrumentation, and JAXA Mercury Magnetospheric Orbiter, MMO) will be launched in the direction of Mercury to study the surface composition and morphology, the geology and the magnetosphere of the planet closest to the Sun. Italy plays an important role in the mission since it is involved in the design and development of the Spectrometer and Imagers for Mpo Bepicolombo Integrated Observatory SYStem (SIMBIO-SYS): this integrated package of instruments includes an imaging system with stereo (STC) and high spatial resolution (HRIC) capabilities along with a hyperspectral imager (VIHI) in the visible and near infrared range. Due to the proximity to the Sun, MPO will face an extremely harsh environment from a thermal point of view, therefore the orbiter, and in particular instrumentation exposed to the thermal fluxes, shall be equipped with sophisticated thermal control devices, such as baffling systems for heat rejection. Starting from the deep knowledge of the thermal scenario in which units and baffles will operate, thanks to the results obtained from detailed thermal and mathematical models, different innovative test-beds have been conceived and designed in order to simulate the environmental thermal fluxes in laboratory. At first, the Structural Thermal Models of SIMBIO-SYS baffles have been tested, subjecting the devices to the environmental infrared fluxes provided by infrared lamps and cold sources in vacuum conditions and assuring different temperature levels on the thermal interfaces of the units; after the test campaign, the thermal mathematical models of the baffles themselves have been validated thanks to the correlation with the experimental results, providing some useful information on the design of the Flight Models of the baffles. Afterwards an original set-up to test the Qualification Model of the Stavroudis baffle of HRIC unit has been designed: during tests, scheduled in January and February 2013, also solar fluxes will be simulated, thanks to CISAS solar simulator, with the aim to qualify the instrument reproducing in vacuum the maximum and minimum operative and non operative temperatures and the most critical heat fluxes (solar and infrared) in sequence. In parallel to this activity, from the need to calibrate and qualify the units in space-like environment simulating the operative conditions, two thermal vacuum chambers have been designed: calibration will be performed for HRIC and STC-VIHI units separately, with and without baffles. The activity started from the comprehension of the instruments calibration requirements and proceeded with the conceptual design of the units, the detailed thermal, structural and electrical design and concluded with the procurement, the assembling and the test activity, which has been performed in order to verify the initial requirements. Thanks to these activities, a series of methods, procedures and techniques, both numerical and experimental, have been developed and validated, with the aim to provide an original and useful contribution to the design and test of SIMBIO-SYS suite onboard BepiColombo mission
L’anno 2015 vedrà l’inizio della missione BepiColombo, promossa dall’Agenzia Spaziale Europea (ESA) in collaborazione con l’Agenzia Spaziale Giapponese (JAXA): la missione scientifica permetterà di approfondire la conoscenza di Mercurio, il pianeta più interno del Sistema Solare, studiandone la superficie, la composizione interna e il campo magnetico, consentendo inoltre di investigare sulle cause che hanno portato alla nascita dei pianeti e sulla loro evoluzione nel tempo. Il segmento di volo è costituito da 2 satelliti distinti: il Mercury Planet Orbiter (MPO), sotto la diretta responsabilità dell’ESA, che supporta la strumentazione per remote sensing e radioscienza, e il Mercury Magnetospheric Orbiter (MMO), che supporta la strumentazione per lo studio del campo magnetico e che è assegnato al controllo della JAXA. L’Italia riveste un ruolo fondamentale nell’ambito della missione dal momento che l’Agenzia Spaziale Italiana è coinvolta nella progettazione e nello sviluppo della suite SIMBIO-SYS (Spectrometer and Imagers for Mpo Bepicolombo Integrated Observatory SYStem), un pacchetto integrato di strumenti costituito da un sistema per imaging stereo (STC), da un sistema per imaging ad alta risoluzione (HRIC) e da uno spettrometro nel campo delle lunghezze d’onda del visibile e dell’infrarosso (VIHI). A causa della vicinanza del pianeta al Sole, MPO opererà in un ambiente ostile ed estremo dal punto di vista termico, di conseguenza il satellite e la strumentazione saranno dotati di sofisticati sistemi per il controllo termico attivo e passivo (ad esempio sistemi di baffling per la reiezione dei flussi). Partendo dalla comprensione e dalla conoscenza dello scenario termico in cui la strumentazione si troverà ad operare, grazie ai risultati dei modelli matematici previsionali, sono stati ideati e progettati diversi setup sperimentali innovativi al fine di simulare in laboratorio i flussi termici ambientali. Inizialmente è stata condotta una campagna di test sui modelli termo-strutturali (STM) dei baffles di SIMBIO-SYS, sottoponendo i dispositivi al flusso infrarosso planetario, simulato da lampade infrarosse e sorgenti fredde in condizioni di vuoto e assicurando diversi livelli di temperature alle interfacce termiche delle unità. In seguito alla campagna di test, i modelli matematici e termici dei baffles sono stati validati, mediante la procedura di correlazione con i risultati sperimentali; grazie alla validazione, è stato quindi possibile raffinare i modelli termici del modello da volo dei baffles. In secondo luogo è stato ideato e progettato un set-up per testare il Qualification Model del baffle Stavroudis di HRIC: durante i test, in programma per gennaio e febbraio 2013, saranno simulati anche i flussi solari, grazie all’innovativo simulatore solare progettato al CISAS, allo scopo di qualificare lo strumento riproducendo in vuoto le minime e massime temperature operative e non operative e i flussi termici (solare e infrarosso) più critici. All’attività precedentemente descritta è stato affiancato il design di due camere termovuoto che verranno utilizzate in fase di calibrazione e qualifica dei modelli da volo di STC, VIHI e HRIC, con e senza baffles. A partire dall’analisi delle prestazioni degli strumenti e da una serie di requisiti meccanici, termici, elettrici, di vuoto, di cleanliness e contamination, è stato effettuato uno studio di fattibilità, a cui sono seguiti il design preliminare delle camere, una serie di analisi strutturali e termiche di dettaglio (per simulare in camera da vuoto le interfacce meccaniche e termiche degli strumenti), la progettazione elettrica, il procurement dei componenti e l’attività di test sui sistemi progettati, al fine di verificare i requisiti iniziali imposti. Grazie a queste attività, sono stati sviluppati e validati una serie di metodi, procedure e tecniche, sia dal punto di vista numerico che sperimentale, al fine di fornire un contributo utile ed originale alla progettazione e alla verifica della strumentazione della suite SIMBIO-SYS a bordo della missione BepiColombo
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Wertz, Julie (Julie Ann) 1978. « Expected productivity-based risk analysis in conceptual design : with application to the Terrestrial Planet Finder Interferometer mission ». Thesis, Massachusetts Institute of Technology, 2005. http://hdl.handle.net/1721.1/35590.

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Thesis (Ph. D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, February 2006.
Page 238 blank.
Includes bibliographical references (p. 233-238).
During the design process, risk is mentioned often, but, due to the lack of a quantitative parameter that engineers can understand and trade, infrequently impacts major design decisions. The definition of risk includes two elements - probability and impact. As a result of heritage techniques used in the nuclear industry, risk assessment in the aerospace industry is usually purely reliability based, and is calculated as the probability of a failure occurring before the end of the design lifetime. While this definition of risk makes sense if all failures result in the same impact, for many non safety-critical systems, the impact of failures may vary, including variance by when a failure occurs. While current risk assessment techniques answer the question "What is the probability of failure?", the true question that needs to be answered for many missions is "How much return can be expected?" Depending on the question answered, the relative ranking of risk items may be different - leading to different risk mitigation investment decisions. Consequently, to complete an accurate risk assessment, it is important to combine system performance and reliability, and model the probabilistic nature of the expected value of the total system productivity.
(cont.) This expected value is defined as the expected productivity. While the expected productivity is easy to calculate for simple systems, it is more complex if a system has a path-dependant productivity function, as is the case with many aerospace systems. In these systems, the productivity in each state depends on the previous states of the system. An approach, called Expected Productivity Risk Analysis (EPRA), has been developed to model the systems described above in an efficient manner by finding the expected path, and then find the expected productivity given that path. EPRA has been tested against conventional Monte Carlo simulations with excellent results that consistently fall within the 95% confidence interval of the Monte Carlo results, while completing the simulation up to 275 times faster. The EPRA approach has been applied to two case-studies, to demonstrate the importance of using expected productivity in a trade study for a real mission, the Terrestrial Planet Finder Interferometer.
by Julie A. Wertz.
Ph.D.
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Gagliano, Joseph R. « Orbital Constellation Design and Analysis Using Spherical Trigonometry and Genetic Algorithms : A Mission Level Design Tool for Single Point Coverage on Any Planet ». DigitalCommons@CalPoly, 2018. https://digitalcommons.calpoly.edu/theses/1877.

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Recent interest surrounding large scale satellite constellations has increased analysis efforts to create the most efficient designs. Multiple studies have successfully optimized constellation patterns using equations of motion propagation methods and genetic algorithms to arrive at optimal solutions. However, these approaches are computationally expensive for large scale constellations, making them impractical for quick iterative design analysis. Therefore, a minimalist algorithm and efficient computational method could be used to improve solution times. This thesis will provide a tool for single target constellation optimization using spherical trigonometry propagation, and an evolutionary genetic algorithm based on a multi-objective optimization function. Each constellation will be evaluated on a normalized fitness scale to determine optimization. The performance objective functions are based on average coverage time, average revisits, and a minimized number of satellites. To adhere to a wider audience, this design tool was written using traditional Matlab, and does not require any additional toolboxes. To create an efficient design tool, spherical trigonometry propagation will be utilized to evaluate constellations for both coverage time and revisits over a single target. This approach was chosen to avoid solving complex ordinary differential equations for each satellite over a long period of time. By converting the satellite and planetary target into vectors of latitude and longitude in a common celestial sphere (i.e. ECI), the angle can be calculated between each set of vectors in three-dimensional space. A comparison of angle against a maximum view angle, , controlled by the elevation angle of the target and the satellite’s altitude, will determine coverage time and number of revisits during a single orbital period. Traditional constellations are defined by an altitude (a), inclination (I), and Walker Delta Pattern notation: T/P/F. Where T represents the number of satellites, P is the number of orbital planes, and F indirectly defines the number of adjacent planes with satellite offsets. Assuming circular orbits, these five parameters outline any possible constellation design. The optimization algorithm will use these parameters as evolutionary traits to iterate through the solutions space. This process will pass down the best traits from one generation to the next, slowly evolving and converging the population towards an optimal solution. Utilizing tournament style selection, multi-parent recombination, and mutation techniques, each generation of children will improve on the last by evaluating the three performance objectives listed. The evolutionary algorithm will iterate through 100 generations (G) with a population (n) of 100. The results of this study explore optimal constellation designs for seven targets evenly spaced from 0° to 90° latitude on Earth, Mars and Jupiter. Each test case reports the top ten constellations found based on optimal fitness. Scatterplots of the constellation design solution space and the multi-objective fitness function breakdown are provided to showcase convergence of the evolutionary genetic algorithm. The results highlight the ratio between constellation altitude and planetary radius as the most influential aspects for achieving optimal constellations due to the increased field of view ratio achievable on smaller planetary bodies. The multi-objective fitness function however, influences constellation design the most because it is the main optimization driver. All future constellation optimization problems should critically determine the best multi-objective fitness function needed for a specific study or mission.
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Livres sur le sujet "Mission design and analysi"

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Larson, Wiley J., et James R. Wertz, dir. Space Mission Analysis and Design. Dordrecht : Springer Netherlands, 1992. http://dx.doi.org/10.1007/978-94-011-2692-2.

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Wertz, James R., et Wiley J. Larson, dir. Space Mission Analysis and Design. Dordrecht : Springer Netherlands, 1991. http://dx.doi.org/10.1007/978-94-011-3794-2.

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(Firm), Knovel, dir. Space mission analysis and design. 3e éd. El Segundo, Calif : Microcosm, 1999.

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R, Wertz James, et Larson Wiley J, dir. Space mission analysis and design. Dordrecht : Kluwer, 1991.

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Richard, Wertz James, et Larson Wiley J, dir. Space mission analysis and design. Dordrecht : Kluwer Academic, 1991.

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J, Larson Wiley, et Wertz James Richard, dir. Space mission analysis and design. 2e éd. Torrance, Calif : Microcosm, 1992.

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J, Larson Wiley, et Wertz James R, dir. Space mission analysis and design workbook. Torrance, Calif : Microcosm Press, 1993.

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United States. Environmental Protection Agency. Office of Administration and Resources Management., dir. System design and development guidance : Mission needs analysis. [Washington, D.C.?] : U.S. Environmental Protection Agency, Administration and Resources Management, 1989.

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Design and Analysis of Accelerated Tests for Mission Critical Reliability. London : Taylor and Francis, 2004.

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Design and analysis of accelerated tests for mission critical reliability. Boca Raton· FL : Chapman & Hall/CRC·, 2003.

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Chapitres de livres sur le sujet "Mission design and analysi"

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Negron, David, et Arthur Chomas. « Mission Operations ». Dans Space Mission Analysis and Design, 491–516. Dordrecht : Springer Netherlands, 1991. http://dx.doi.org/10.1007/978-94-011-3794-2_14.

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Reinert, Richard P., et James R. Wertz. « Mission Characterization ». Dans Space Mission Analysis and Design, 19–34. Dordrecht : Springer Netherlands, 1991. http://dx.doi.org/10.1007/978-94-011-3794-2_2.

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Wertz, James R. « Mission Evaluation ». Dans Space Mission Analysis and Design, 35–56. Dordrecht : Springer Netherlands, 1991. http://dx.doi.org/10.1007/978-94-011-3794-2_3.

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Negron, David, et Arthur Chomas. « Mission Operations ». Dans Space Mission Analysis and Design, 553–77. Dordrecht : Springer Netherlands, 1992. http://dx.doi.org/10.1007/978-94-011-2692-2_14.

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Reinert, Richard P., et James R. Wertz. « Mission Characterization ». Dans Space Mission Analysis and Design, 19–46. Dordrecht : Springer Netherlands, 1992. http://dx.doi.org/10.1007/978-94-011-2692-2_2.

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Wertz, James R. « Mission Evaluation ». Dans Space Mission Analysis and Design, 47–68. Dordrecht : Springer Netherlands, 1992. http://dx.doi.org/10.1007/978-94-011-2692-2_3.

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Wertz, James R. « Space Mission Geometry ». Dans Space Mission Analysis and Design, 79–112. Dordrecht : Springer Netherlands, 1991. http://dx.doi.org/10.1007/978-94-011-3794-2_5.

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Wertz, James R. « Space Mission Geometry ». Dans Space Mission Analysis and Design, 93–127. Dordrecht : Springer Netherlands, 1992. http://dx.doi.org/10.1007/978-94-011-2692-2_5.

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Wirin, William B., et Darren S. McKnight. « Limits on Mission Design ». Dans Space Mission Analysis and Design, 683–710. Dordrecht : Springer Netherlands, 1991. http://dx.doi.org/10.1007/978-94-011-3794-2_21.

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Wirin, William B., et Darren S. McKnight. « Limits on Mission Design ». Dans Space Mission Analysis and Design, 741–66. Dordrecht : Springer Netherlands, 1992. http://dx.doi.org/10.1007/978-94-011-2692-2_21.

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Actes de conférences sur le sujet "Mission design and analysi"

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Park, Jae-Pil, Sang-young Park, Kwangwon Lee, Hyungjik J. Oh, Kyung Yun Choi, Young Bum Song, Jin-Chul Yim et al. « Mission Analysis and CubeSat Design for CANYVAL-X mission ». Dans SpaceOps 2016 Conference. Reston, Virginia : American Institute of Aeronautics and Astronautics, 2016. http://dx.doi.org/10.2514/6.2016-2493.

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Kahle, Ralph, Gerhard Hahn, Ekkehard Kuehrt et Stefanos Fasoulas. « Athos Deflection Mission Analysis and Design ». Dans 2004 Planetary Defense Conference : Protecting Earth from Asteroids. Reston, Virigina : American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-1460.

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Wowczuk, Zenovy S., Jeffery R. X. Auld et James E. Smith. « A Cost and Time Effective Alternative for an Aerial Reconnaissance and Surveillance Platform ». Dans ASME 8th Biennial Conference on Engineering Systems Design and Analysis. ASMEDC, 2006. http://dx.doi.org/10.1115/esda2006-95600.

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An expanded need for information obtainable from aerial sensor platforms is driving research and development towards both the use of Unmanned Aerial Vehicles (UAV’s) and the extensive physical redesign of existing airframes to accommodate alternative capabilities. This trend in aerial platform development requires significant time and funding and has yet to transpire into low single-system cost that can be rapidly set to use. An alternative concept of utilizing existing and unmodified airframes as sensor platforms, through the use of peripheral systems, presents an attractive solution to this problem. A particular sensor platform system (Oculus) has been designed for use upon a C-130 aircraft and, as a blueprint concept, shows considerable design flexibility for use upon additional existing military and commercial airframes. This roll-on roll-off sensor platform is a stand alone system that requires no modification to the C-130 airframe and has the capacity to incorporate multi-mission sensor capabilities which can be used for a wide variety of missions. These missions are (but not limited to) Environmental Impact Assessment, Counter Drug, Counter Terrorism, Homeland Security, Resource Surveys, Environmental Surveys, and Search and Rescue. This system (patent pending) has been developed to support a broad spectrum of the latest in remote sensor technology for missions requiring highly proficient reconnaissance capabilities. It was also designed under the criterion of mission flexibility, stability, field of view, storability, modular attachment space and provisions for expansion and upgrade. This sensor platform system provides a superior cost-effective upgrade capability to existing airframes.
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WHEELOCK, R. « The role of mission effectiveness analysis during preliminary design ». Dans Aerospace Design Conference. Reston, Virigina : American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-1260.

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Shriyam, Shaurya, et Satyandra K. Gupta. « Task Assignment and Scheduling for Mobile Robot Teams ». Dans ASME 2018 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/detc2018-86007.

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Most complex missions comprise of spatially separated tasks which have to be finished using teams of mobile robots. The main challenges for planning such missions are forming effective coalitions among available robots and assigning them to tasks in such a way that the expected mission completion time is minimized. Our model allows task execution by a fraction of the assigned team even when the rest of the team has not yet arrived at the task location. We also allow tasks to be interrupted and robots of assigned teams to be rescheduled from an unfinished task to another task. We describe five different heuristic algorithms to compute schedules for all robots assigned to the mission. We compare them and analyze the computational performance of the best performing strategy. We also show how to handle uncertainty that may arise during traveling or task execution and then study the effect of varying uncertainty on the minimization of mission completion time.
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FAWCETT, C., et J. MARTIN. « Review of future strategic aeronautical systems mission analysis ». Dans Aircraft Systems, Design and Technology Meeting. Reston, Virigina : American Institute of Aeronautics and Astronautics, 1986. http://dx.doi.org/10.2514/6.1986-2643.

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Danhel, Martin, Hana Kubatova et Radek Dobia. « Predictive Analysis of Mission Critical Systems Dependability ». Dans 2013 Euromicro Conference on Digital System Design (DSD). IEEE, 2013. http://dx.doi.org/10.1109/dsd.2013.66.

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Hutcheson, Ryan S., Daniel A. McAdams, Robert B. Stone et Irem Y. Tumer. « A Function-Based Methodology for Analyzing Critical Events ». Dans ASME 2006 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2006. http://dx.doi.org/10.1115/detc2006-99535.

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The objective of this research was to develop a function-based method for analyzing the critical sequences of events that must occur for complex space missions to be successful. The resulting methodology, the Function-based Analysis of Critical Events, or FACE, uses functional and event models to identify the changes in functionality of a system as it transitions between critical mission events. Two examples are presented that detail the application of FACE to prior mission failures including the loss of the Columbia orbiter and the failure of the Mars Polar Lander probe. The result of the research is a methodology that allows designers to not only reduce the occurrence of such failures but also analyze the specific functional causes of the failures when they do occur.
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Fisher, Zachary C., David Locascio, K. Daniel Cooksey, Dimitri N. Mavris et Eric Spero. « ADAPt Design : A Methodology for Enabling Modular Design for Mission Specific SUAS ». Dans ASME 2016 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/detc2016-60122.

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Recent advances in small unmanned aircraft systems (SUAS) have greatly broadened the scope of their potential applications. However, traditional design processes applied to SUAS produce a single design for a single set of requirements. Off-design mission performance is often greatly degraded due to the vehicle’s small scale. This paper considers a different approach to SUAS design aimed at addressing this issue. In this approach, a hybrid modular and scalable product family is coupled with linked engineering analyses in order to automatically formulate a design given a set of mission requirements. This allows multiple SUAS designs to be rapidly synthesized from multiple sets of design requirements using a common set of components. Designs are then rapidly generated and manufactured “on-demand” using automated manufacturing techniques in order to address unforeseen mission needs. The design approach, named “Aggregate Derivative Approach to Product Design” (ADAPt Design), consists of four actions: (1) requirements analysis, (2) architecture selection, (3) interface design, and (4) concept refinement and design. The outcomes of the method are a family of designs which are highly compatible with design automation, and a toolset that automatically translates changes in requirements to changes in detailed 3-D models. Results of the application of this approach are presented via the design of several SUAS. The capability of the design paradigm is assessed through a comparison of design requirements to the measured performance of the designed vehicle, and conclusions are drawn about the approach’s applicability and scalability.
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Azarsina, Farhood, et Hassan Sayyaadi. « Design of a Fuzzy Controller for an Underwater Vehicle Aiming at a Stationary Target ». Dans ASME 8th Biennial Conference on Engineering Systems Design and Analysis. ASMEDC, 2006. http://dx.doi.org/10.1115/esda2006-95033.

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In this paper, on the basis of a robust algorithm for the analysis of the 6 DOF motion of an underwater vehicle in calm water, after presenting the dynamics model and simulating motion, the model is put in the closed loop control to perform a controlled mission. The mission is defined as to navigate the submarine toward a desired point in the vertical plane. In performing the mission, the least time and of course the least position error with respect to the target point is aimed. The designed controller based on fuzzy logic and thus adapted to the human patterns for navigation, with a simple structure, performs the mission accurately. The intelligent structure of the fuzzy controller, results in a spectacular capability in target finding; such that by the increase of mission duration, the submarine, which never completely stops in this modeling, reaches the target point multiple times. Several simulations of the controlled motion, changing the coordinates of target point, proved the controller effectiveness.
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Rapports d'organisations sur le sujet "Mission design and analysi"

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Fevig, Ronald Adrey, et Jeremy Straub. Formalizing Mission Analysis and Design Techniques for High Altitude Ballooning. Ames (Iowa) : Iowa State University. Library. Digital Press, janvier 2012. http://dx.doi.org/10.31274/ahac.8323.

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Chrien, Thomas G., et Ronald B. Lockwood. Design and Analysis Approach for a Rapid Response Hyperspectral Imaging Mission. Fort Belvoir, VA : Defense Technical Information Center, septembre 2005. http://dx.doi.org/10.21236/ada438875.

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Schock, Alfred, Meera Mukunda et G. Summers. Analysis, Optimization, and Assessment of Radioisotope Thermophotovoltaic System Design for an Illustrative Space Mission. Office of Scientific and Technical Information (OSTI), juin 1994. http://dx.doi.org/10.2172/1034425.

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Schock, Alfred, Meera Mukunda, Chuen T. Or, Vasanth Kumar et G. Summers. Design, Analysis, and Optimization of a Radioisotope Thermophotovoltaic (RTPV) Generator, and its Applicability to an Illustrative Space Mission. Office of Scientific and Technical Information (OSTI), octobre 1994. http://dx.doi.org/10.2172/1033365.

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Schock, Alfred, Heros Noravian, Chuen Or et Kumar Sankarankandath. Design and Analysis of RTGs for CRAF and Cassini Missions. Office of Scientific and Technical Information (OSTI), janvier 1991. http://dx.doi.org/10.2172/1047824.

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Schock, Alfred, Heros Noravian et Sankarankandath. Design and Analysis of RTGs for CRAF and Cassini Missions. Office of Scientific and Technical Information (OSTI), novembre 1990. http://dx.doi.org/10.2172/1047829.

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Schock, Alfred. Design and Analysis of RTGs for Solar and Martian Exploration Missions. Office of Scientific and Technical Information (OSTI), mai 1990. http://dx.doi.org/10.2172/1033389.

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Schock, Alfred, Chuen T. Or et Heros Noravian. Design, Analysis, and Spacecraft Integration of RTGs for CRAF and Cassini Missions. Office of Scientific and Technical Information (OSTI), avril 1991. http://dx.doi.org/10.2172/1047830.

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Schock, Alfred, Chuen T. Or et Heros Noravian. Design, Analysis, and Spacecraft Integration of RTGs for CRAF and Cassini Missions. Office of Scientific and Technical Information (OSTI), avril 1991. http://dx.doi.org/10.2172/1033413.

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Schock, Alfred, Chuen T. Or et Heros Noravian. Design, Analysis, and Spacecraft Integration of RTGs for CRAF and Cassini Missions. Office of Scientific and Technical Information (OSTI), juillet 1991. http://dx.doi.org/10.2172/1033414.

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