Journal articles: 'Mission design and analysi'

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

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Musiał, Alicja, Dominik Markowski, Jan Życzkowski, and 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 (September 21, 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, and Bram de Vogeleer. "Mission design and analysis of European astrophysics missions orbiting libration points." Acta Astronautica 84 (March 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, and Guy Janin. "Satellite constellation mission analysis and design." Acta Astronautica 48, no. 5-12 (March 2001): 681–91. http://dx.doi.org/10.1016/s0094-5765(01)00016-9.

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Weber, A., S. Fasoulas, and 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 (September 9, 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, and 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 (February 1, 2014): 181–90. http://dx.doi.org/10.5139/jksas.2014.42.2.181.

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Shen, Diyang, Yuxian Yue, and Xiaohui Wang. "Manned Mars Mission Analysis Using Mission Architecture Matrix Method." Aerospace 9, no. 10 (October 14, 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, and 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 (August 8, 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, and 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 (October 12, 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., and Karen Seashore Louis. "Mission as Metaphor: Reconceptualizing how Leaders Utilize Institutional Mission." Teachers College Record: The Voice of Scholarship in Education 120, no. 9 (September 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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Immer, Marc, and Philipp Georg Juretzko. "Advanced aircraft performance analysis." Aircraft Engineering and Aerospace Technology 90, no. 4 (May 8, 2018): 627–38. http://dx.doi.org/10.1108/aeat-11-2016-0205.

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Purpose The preliminary aircraft design process comprises multiple disciplines. During performance analysis, parameters of the design mission have to be optimized. Mission performance optimization is often challenging, especially for complex mission profiles (e.g. for unmanned aerial vehicles [UAVs]) or hybrid-electric propulsion. Therefore, the purpose of this study is to find a methodology that supports aircraft performance analysis and that is applicable to complex profiles and to novel designs. Design/methodology/approach As its core element, the developed method uses a computationally efficient C++ software “Aircraft Performance Program” (APP), which performs a segment-based mission computation. APP performs a time integration of the equations of motion of a point mass in the vertical plane. APP is called via a command line interface from a flexible scripting language (Python). On top of APP’s internal radius of action optimization, state-of-the-art optimization packages (SciPy) are used. Findings The application of the method to a conventional climb schedule shows that the definition of the top of climb has a significant influence on the resulting optimum. Application of the method to a complex UAV mission optimization, which included maximizing the radius of action, was successful. Low computation time enables to perform large parametric studies. This greatly improves the interpretation of the results. Research limitations/implications The scope of the paper is limited to the methodology that allows for advanced performance analysis at the conceptual and preliminary design stages with an emphasis on novel propulsion concepts. The methodology is developed using existing, validated methods, and therefore, this paper does not contain comprehensive validation. Other disciplines, such as cost analysis, life-cycle assessment or market analysis, are not considered. Practical implications With the proposed method, it is possible to obtain not only the desired optimum mission performance but also off-design performance of the investigated design. A thorough analysis of the mission performance provides insight into the design’s capabilities and shortcomings, ultimately aiding in obtaining a more efficient design. Originality/value Recent developments in the area of hybrid or hybrid-electric propulsion systems have shown the need for performance computation tools aiding the related design process. The presented method is especially valuable when novel design concepts with complex mission profiles are investigated.

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Liu, Sheng Gang, Shao Kai Wang, and Chao Han. "A Distributed Scene Simulation System for Earth Observation Satellite Mission Design and Analysis." Applied Mechanics and Materials 444-445 (October 2013): 1810–14. http://dx.doi.org/10.4028/www.scientific.net/amm.444-445.1810.

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The primary mission objective is gathering information of the Earth by on-board instruments using remote-sensing techniques, and sending the useful information back to the ground. Its mission design and analysis involves identification of critical requirements, determination of mission orbit, analysis of relationship between satellite, the Earth and the Sun. This paper proposed a new scene simulation system based on distributed architecture, which consisted of mission design subsystem, numerical simulation subsystem, scenario display subsystem and model management subsystem. The system can show the updated mission status and performance rapidly and efficiently after user modified the initial mission parameters. Practice has proven that it can help users to make a decision and judgment for the mission design, and improve their work efficiency.

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Page, Jonathan. "Flexibility in Early Stage Design of U.S. Navy Ships: An Analysis of Options." Journal of Ship Production and Design 28, no. 03 (August 1, 2012): 128–33. http://dx.doi.org/10.5957/jspd.2012.28.3.128.

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This paper is a summary of my thesis work at the Massachusetts Institute of Technology (MIT). It explores design options for naval vessels and provides a framework for analyzing their benefit to the Navy. Future demands on Navy warships, such as new or changing missions and capabilities, are unknowns at the time of the ship's design. Therefore, ships often require costly engineering changes throughout their service life. These are expensive both fiscally – because the Navy pays for engineering and installation work – and operationally – because either a warship cannot carry out a desired mission need or is carrying out a mission for which it was not initially designed. One method of addressing uncertainty in capital assets is imbedding flexibilities in their architecture. The paper offers early stage design suggestions on flexibilities for naval platforms to incorporate preplanned repeats of the platform with new or different missions. A conceptual platform created – the SCAMP – includes each of these suggestions in its architecture. Then, the paper summarizes an analysis framework similar to real options to evaluate the value of including these expansion options in early stage design versus traditional design methods and their products. The analysis uses a version of the MIT Cost Model for early stage ship design to determine acquisition and life cycle costs. The model was modified to support this analysis by allowing a simulation of possible mission changes with their severity distributed stochastically over a realistic time horizon. Subsequently, the model calculates these effects on life cycle cost. The most important result is the value of the framework for evaluating these managerial options. This framework can be extended to the subsystem level or to the system-of-systems level. In this application, the model predicts that, on average, a flexible platform should not only cost less to build, but also reduce modernization costs by 9% per ship over its life cycle. Therefore, counter-intuitively, building a lesscapable ship with the flexibility to expand capabilities or switch missions actually provides greater expected utility during its service life.

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Purkhauser, Anna F., Christian Siemes, and Roland Pail. "Consistent quantification of the impact of key mission design parameters on the performance of next-generation gravity missions." Geophysical Journal International 221, no. 2 (February 5, 2020): 1190–210. http://dx.doi.org/10.1093/gji/ggaa070.

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SUMMARY The GRACE and GRACE-FO missions have been observing time variations of the Earth's gravity field for more than 15 yr. For a possible successor mission, the need to continue mass change observations have to be balanced with the ambition for monitoring capabilities with an enhanced spatial and temporal resolution that will enable improved scientific results and will serve operational services and applications. Various study groups performed individual simulations to analyse different aspects of possible NGGMs from a scientific and technical point of view. As these studies are not directly comparable due to different assumptions regarding mission design and instrumentation, the goal of this paper is to systematically analyse and quantify the key mission parameters (number of satellite pairs, orbit altitude, sensors) and the impact of various error sources (AO, OT models, post-processing) in a consistent simulation environment. Our study demonstrates that a single-pair mission with laser interferometry in a low orbit with a drag compensation system would be the only possibility within the single-pair options to increase the performance compared to the GRACE/GRACE-FO. Tailored post-processing is not able to achieve the same performance as a double-pair mission without post-processing. Also, such a mission concept does not solve the problems of temporal aliasing due to observation geometry. In contrast, double-pair concepts have the potential to retrieve the full AOHIS signal and in some cases even double the performance to the comparable single-pair scenario. When combining a double-pair with laser interferometry and an improved accelerometer, the sensor noise is, apart from the ocean tide modelling errors, one of the limiting factors. Therefore, the next big step for observing the gravity field globally with a satellite mission can only be taken by launching a double pair mission. With this quantification of key architecture features of a future satellite gravity mission, the study aims to improve the available information to allow for an informed decision making and give an indication of priority for the different mission concepts.

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WU, AN-MING, XIAOHUI XU, and WEI-TOU NI. "ORBIT DESIGN AND ANALYSIS FOR THE ASTROD MISSION CONCEPT." International Journal of Modern Physics D 09, no. 02 (April 2000): 201–14. http://dx.doi.org/10.1142/s0218271800000165.

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The ASTROD (Astrodynamical Space Test of Relativity using Optical Devices) mission concept is to conduct high-precision measurement of relativistic effects, better determination of the orbits of major asteroids and other solar system parameters, improvement in the measurement of [Formula: see text], measurement of solar angular momentum via Lense–Thirring effect, and the detection of low-frequency gravitational waves and solar oscillations in a single mission. It will be realized by placing a fleet of drag-free spacecraft in solar orbits together with an Earth reference system. Two spacecraft launched into separate solar orbits, as a simple implementation, can reach the opposite side of Sun after traveling about 2.5 years. In this paper, we describe the orbit design process for this simple implementation including the two-body model, initial velocity determination, and optimization consideration. Through fine tuning of the initial velocity, we can have the two spacecraft nearly return to the 2.5 years positions at 7.5 years mission time, which means that the ASTROD mission can have a second good chance to observe Shapiro time delay precisely and to measure the solar Lense–Thirring effect if the mission lasts over 7.5 years. We also calculate the light traveling time and the Shapiro time delay.

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Cassar, Lea, and Jesper Armouti-Hansen. "Optimal Contracting with Endogenous Project Mission." Journal of the European Economic Association 18, no. 5 (October 26, 2019): 2647–76. http://dx.doi.org/10.1093/jeea/jvz055.

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Abstract Empirical evidence suggests that workers care about the mission of their job, in addition to their wage. This paper studies how organizations can choose a mission to attract, incentivize, and screen their workers. We analyze a model in which a principal offers a contract to an agent for the development of a project and can influence the agent’s marginal return of effort through the choice of project mission. The principal’s and the agents’ mission preferences are misaligned and the agents vary in the intensity of their mission drive. Our main results highlight that how far the organization chooses to move from its preferred mission depends on the contractual environment in which it operates. Missions will be more agent-preferred in environments in which effort is noncontractible. In environments in which agents’ drive is unknown, missions will be less agent-preferred and the organization will find it optimal to offer contract menus that may be implemented via scoring auctions when there are competing agents. Our analysis applies to the design and allocation of aid contracts, research funding, and creative jobs.

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Martens, Waldemar, and Eric Joffre. "Trajectory Design for the ESA LISA Mission." Journal of the Astronautical Sciences 68, no. 2 (June 2021): 402–43. http://dx.doi.org/10.1007/s40295-021-00263-2.

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AbstractThe three Laser Interferometer Space Antenna (LISA) spacecraft are going to be placed in a triangular formation in an Earth-trailing or Earth-leading orbit. They will be launched together on a single rocket and transferred to that science orbit using Solar Electric Propulsion. Since the transfer Δv depends on the chosen science orbit, both transfer and science orbit have been optimised together. For a thrust level of 90 mN, an allocation of 1092 m/s per spacecraft is sufficient for an all-year launch in 2034. For every launch month a dedicated science orbit is designed with a corner angle variation of 60° ± 1.0° and an arm length rate of maximum 10 m/s. Moreover, a detailed navigation analysis of the science orbit insertion and the impact on insertion errors on the constellation stability has been conducted. The analysis shows that Range/Doppler measurements together with a series of correction manoeuvres at the beginning of the science orbit phase can reduce insertion dispersions to a level where corner angle variations remain at about 60° ± 1.1° at 99% C.L. However, the situation can become significantly worse if the self-gravity accelerations acting during the science orbit phase are not sufficiently characterised prior to science orbit insertion.

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Tokadlı, Güliz, and Michael C. Dorneich. "Development of a Functionality Matrix for a Cognitive Assistant on Long Distance Space Missions." Proceedings of the Human Factors and Ergonomics Society Annual Meeting 61, no. 1 (September 2017): 247–51. http://dx.doi.org/10.1177/1541931213601545.

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This paper discusses the development and application of a Functionality Matrix (FM) technique to design requirements for a Cognitive Assistant (CA) to aid future long distance space missions. Future far-Earth space missions pose challenges due to communication delays between Mission Control and space crew. As communication delays increase, Mission Control is less able to support space crew in off-nominal situations. The FM technique was used to extrapolate the joint decision-making functions performed in current near-Earth operations to functions performed in future, far-Earth space operations, allocated between Mission Control, space crew, and potential automation. Data gathered from document analysis and interviews with astronauts were consolidated to generate the domain knowledge models of the collaborative decision-making process for current space operations. Each function in the decision-making process was examined to extrapolate the current collaborative work of Mission Control and space crew to future space operations under long time delays, when the role of Mission Control must change. The domain knowledge models were also used to identify the functions performed to resolve off-nominal situations in current operations that are most affected by long communication delays. The identified functions constituted the input for the FM. The responsibilities of Mission Control, space crew and CA were categorized in the FM as current and/or future space operations. The FM describes the shared responsibilities between space crew and Mission Control with and without CA support in space operations. The FM was used to describe functional design requirements, and will lead to the development of function allocation rules.

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Chupin, Maxime, Thomas Haberkorn, and Emmanuel Trélat. "Low-thrust Lyapunov to Lyapunov and Halo to Halo missions with L2-minimization." ESAIM: Mathematical Modelling and Numerical Analysis 51, no. 3 (April 14, 2017): 965–96. http://dx.doi.org/10.1051/m2an/2016044.

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In this work, we develop a new method to design energy minimum low-thrust missions (L2-minimization). In the Circular Restricted Three Body Problem, the knowledge of invariant manifolds helps us initialize an indirect method solving a transfer mission between periodic Lyapunov orbits. Indeed, using the PMP, the optimal control problem is solved using Newton-like algorithms finding the zero of a shooting function. To compute a Lyapunov to Lyapunov mission, we first compute an admissible trajectory using a heteroclinic orbit between the two periodic orbits. It is then used to initialize a multiple shooting method in order to release the constraint. We finally optimize the terminal points on the periodic orbits. Moreover, we use continuation methods on position and on thrust, in order to gain robustness. A more general Halo to Halo mission, with different energies, is computed in the last section without heteroclinic orbits but using invariant manifolds to initialize shooting methods with a similar approach.

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Kwon, Kybeom, Seunghyun Min, Jongbum Kim, and Kwangwon Lee. "Framework Development for Efficient Mission-Oriented Satellite System-Level Design." Aerospace 10, no. 3 (February 26, 2023): 228. http://dx.doi.org/10.3390/aerospace10030228.

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The space mission analysis and design process defines a space system at the system level to accomplish space mission objectives. Although the traditional process is well established and comprehensive through several years of experience, we propose a novel design process framework in this paper to aid the traditional process focusing on the following areas of improvement: (1) clarification of the direct connection between mission objectives and final system-level baseline design and requirements, (2) development of a comprehensive quantitative judgment criterion to evaluate various design alternatives, (3) derivation of system drivers and critical requirements after obtaining sufficient design knowledge based on the analysis of big data obtained from exploration of entire design space using an integrated design environment, and (4) system optimization even at the system level with a holistic perspective to guarantee that the baseline design meets the mission objectives. Examples of design steps in the proposed framework are characterizing stakeholder needs and engineering characteristics, building an integrated design environment, exploring and analyzing design space, optimizing system-level design, and elaborating mission utility to ensure an efficient mission-oriented design approach. The proposed framework is implemented in an example space mission involving quantum cryptographic communication. Accordingly, we demonstrate that the proposed framework provides an efficient mission-oriented satellite system-level baseline design.

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Babnik, Katarina, Kristijan Breznik, Valerij Dermol, and Nada Trunk Širca. "The mission statement: organisational culture perspective." Industrial Management & Data Systems 114, no. 4 (May 6, 2014): 612–27. http://dx.doi.org/10.1108/imds-10-2013-0455.

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Purpose – The purpose of this paper is to contribute to the understanding of mission statement contents and its function in guiding employee's behaviour from the organisational culture (OC) perspective. Design/methodology/approach – The research is based on a mixed method approach. The quantitative content analysis of mission statements was performed on a sample of 222 Slovenian companies. Mission statement's keywords were analysed with exploratory factor analysis. Advanced network analytic approaches such as PathFinder algorithm were utilised to obtain better understanding of interrelatedness of underlying mission components. Three interviews with the top managers were performed as well. Findings – The mission statement content analysis identified five associated organisations’ orientations: concern for stakeholders, orientation towards stability, orientation towards cooperation and innovation, and development and growth. The interviews confirm missions’ role in communicating the espoused or declared OC, although different approaches to achieve employees’ commitment to the organisation's mission can be identified in regard to the size of the organisation. Originality/value – The cultural approach to the analysis of mission statements confirms that the mission statements incorporate basic contents of OC. The methodology applied gives new possibilities in the research of OC perspective of strategic statements.

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Deng, Li, Zhen Yang, Pengyu Du, and You Song. "A cloud platform for space science mission concurrent design." Concurrent Engineering 26, no. 1 (August 11, 2017): 104–16. http://dx.doi.org/10.1177/1063293x17724848.

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Using concurrent design methodology, the duration of space science mission in conceptual design phase can be shortened. This approach requires hardware and software resources to support, such as professional design tools and concurrent design environment. Except for the professional groups, the general researchers such as teachers and students have no chance to access these resources. Nowadays, more and more researchers distributed in different locations join into the space science research. The need for an open concurrent design platform offering design tools and data sharing environment has increased. This article presents a Cloud Platform of Concurrent Design for Space Science Mission. This Cloud Platform of Concurrent Design for Space Science Mission uses the idea of Software as a service, in which five design and analysis tools are offered as services to satisfy the basic requirements for space science mission concurrent design in conceptual design phase. This cloud platform provides the access to space science mission concurrent design for expert and non-expert users using a thin client of web browser. This article presents the platform architecture of the Cloud Platform of Concurrent Design for Space Science Mission and five software offered as services. The services include spacecraft conceptual orbit design, structure design, payload coverage analysis, data transmission analysis, and virtual community. And the basic cloud service (computing and storage) is also briefly introduced. It is described in detail how these services can be leveraged by users to do the concurrent design for one space science mission.

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Radice, Gianmarco, Romain Wuilbercq, and Gioacchino Cafiero. "T-SMAD: a Concurrent Design Tool for Space Mission Analysis and Design." Frontiers in Aerospace Engineering 3, no. 1 (2014): 1. http://dx.doi.org/10.14355/fae.2014.0301.01.

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Buchanan, Weston P., Maxim de Jong, Rachana Agrawal, Janusz J. Petkowski, Archit Arora, Sarag J. Saikia, Sara Seager, and James Longuski. "Aerial Platform Design Options for a Life-Finding Mission at Venus." Aerospace 9, no. 7 (July 7, 2022): 363. http://dx.doi.org/10.3390/aerospace9070363.

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Mounting evidence of chemical disequilibria in the Venusian atmosphere has heightened interest in the search for life within the planet’s cloud decks. Balloon systems are currently considered to be the superior class of aerial platform for extended atmospheric sampling within the clouds, providing the highest ratio of science return to risk. Balloon-based aerial platform designs depend heavily on payload mass and target altitudes. We present options for constant- and variable-altitude balloon systems designed to carry out science operations inside the Venusian cloud decks. The Venus Life Finder (VLF) mission study proposes a series of missions that require extended in situ analysis of Venus cloud material. We provide an overview of a representative mission architecture, as well as gondola designs to accommodate a VLF instrument suite. Current architecture asserts a launch date of 30 July 2026, which would place an orbiter and entry vehicle at Venus as early as November 29 of that same year.

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Palaia, Giuseppe, and Karim Abu Salem. "Mission Performance Analysis of Hybrid-Electric Regional Aircraft." Aerospace 10, no. 3 (March 2, 2023): 246. http://dx.doi.org/10.3390/aerospace10030246.

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This article discusses the mission performance of regional aircraft with hybrid-electric propulsion. The performance analyses are provided by mission simulations tools specifically developed for hybrid-electric aircraft flight dynamics. The hybrid-electric aircraft mission performance is assessed for the design point, identified by top level requirements, and for off-design missions, within the whole operating envelope. This work highlights that the operating features of hybrid-electric aircraft differ from those of aircraft of the same category with conventional thermal propulsion. This assessment is processed by properly analysing the aircraft payload–range diagram, which is a very effective tool to assess the operating performance. The payload–range diagram shape of hybrid-electric aircraft can vary as multiple combinations of the masses of batteries, fuel and payload to be transported on board are possible. The trade-off in the power supply strategies of the two power sources to reduce fuel consumption or to extend the maximum flight distance is described in detail. The results show that the hybrid-electric propulsion integrated on regional aircraft can lead to benefits in terms of environmental performance, through savings in direct fuel consumption, or alternatively in operating terms, through a significant extension of the operating envelope.

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Heiligers, Jeannette, Matteo Ceriotti, Colin R. McInnes, and James D. Biggs. "Mission analysis and systems design of a near-term and far-term pole-sitter mission." Acta Astronautica 94, no. 1 (January 2014): 455–69. http://dx.doi.org/10.1016/j.actaastro.2012.12.015.

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Chouraqui, S., and M. Benyettou . "Orbital Motion Modelling for Spacecraft Mission Analysis and Design." Journal of Applied Sciences 5, no. 8 (July 15, 2005): 1438–44. http://dx.doi.org/10.3923/jas.2005.1438.1444.

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Yang, Chen, Baoyin He-xi, and Li Jun-feng. "Trajectory Analysis and Design for A Jupiter Exploration Mission." Chinese Astronomy and Astrophysics 37, no. 1 (January 2013): 77–89. http://dx.doi.org/10.1016/j.chinastron.2013.01.008.

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Benedetti, Gianluca, Nicoletta Bloise, Davide Boi, Francesco Caruso, Andrea Civita, Sabrina Corpino, Erik Garofalo, et al. "Interplanetary CubeSats for asteroid exploration: Mission analysis and design." Acta Astronautica 154 (January 2019): 238–55. http://dx.doi.org/10.1016/j.actaastro.2018.05.011.

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He, Yongming, Yuan Wang, Yingwu Chen, and Lining Xing. "Auto Mission Planning System Design for Imaging Satellites and Its Applications in Environmental Field." Polish Maritime Research 23, s1 (October 1, 2016): 59–70. http://dx.doi.org/10.1515/pomr-2016-0047.

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Abstract Satellite hardware has reached a level of development that enables imaging satellites to realize applications in the area of meteorology and environmental monitoring. As the requirements in terms of feasibility and the actual profit achieved by satellite applications increase, we need to comprehensively consider the actual status, constraints, unpredictable information, and complicated requirements. The management of this complex information and the allocation of satellite resources to realize image acquisition have become essential for enhancing the efficiency of satellite instrumentation. In view of this, we designed a satellite auto mission planning system, which includes two sub-systems: the imaging satellite itself and the ground base, and these systems would then collaborate to process complicated missions: the satellite mainly focuses on mission planning and functions according to actual parameters, whereas the ground base provides auxiliary information, management, and control. Based on the requirements analysis, we have devised the application scenarios, main module, and key techniques. Comparison of the simulation results of the system, confirmed the feasibility and optimization efficiency of the system framework, which also stimulates new thinking for the method of monitoring environment and design of mission planning systems.

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Kwiek, Agnieszka. "Conceptual design of an aircraft for Mars mission." Aircraft Engineering and Aerospace Technology 91, no. 6 (June 10, 2019): 886–92. http://dx.doi.org/10.1108/aeat-08-2018-0231.

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Purpose The purpose of this paper is to present the results of a conceptual design of Martian aircraft. This study focuses on the aerodynamic and longitudinal dynamic stability analysis. The main research questions are as follows: Does a tailless aircraft configuration can be used for Martian aircraft? How to the short period characteristic can be improved by side plates modification? Design/methodology/approach Because of a conceptual design stage of this Martian aircraft, aerodynamic characterises were computed by the Panukl package by using the potential flow model. The longitudinal dynamic stability was computed by MATLAB code, and the derivatives computed by the SDSA software were used as the input data. Different aircraft configurations have been studied, including different wing’s aerofoils and configurations of the side plate. Findings This paper presents results of aerodynamic characteristics computations and longitudinal dynamic stability analysis. This paper shows that tailless aircraft configuration has potential to be used as Martian aircraft. Moreover, the study of the impact of side plates’ configurations on the longitudinal dynamic stability is presented. This investigation reveals that the most effective method to improve the short period damping ratio is to change the height of the bottom plate. Practical implications The presented result might be useful in case of further design of the aircrafts for the Mars mission and designing the aircrafts in a tailless configuration. Social implications It is considered by the human expedition that Mars is the most probable planet to explore. This paper presents the conceptual study of aircraft which can be used to take the high-resolution pictures of the surface of Mars, which can be crucial to find the right place to establish a potential Martian base. Originality/value Most of aircrafts proposed for the Mars mission are designed in a configuration with a classic tail; this paper shows a preliminary calculation of the tailless Martian aircraft. Moreover, this paper shows the results of a dynamic stability analysis, where similar papers about aircrafts for the Mars mission do not show such outcomes, especially in the case of the tailless configuration. Moreover, this paper presents the results of the dynamic stability analysis of tailless aircraft with different configurations of the side plates.

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Mahdi, Mohammed Chessab. "Orbit Design and Simulation for Kufasat Nanosatellite." Artificial Satellites 50, no. 4 (December 1, 2015): 157–68. http://dx.doi.org/10.1515/arsa-2015-0013.

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Abstract Orbit design for KufaSat Nano-satellites is presented. Polar orbit is selected for the KufaSat mission. The orbit was designed with an Inclination which enables the satellite to see every part of the earth. KufaSat has a payload for imaging purposes which require a large amount of power, so the orbit is determined to be sun synchronous in order to provide the power through solar panels. The KufaSat mission is designed for the low earth orbit. The six initial Keplerian Elements of KufaSat are calculated. The orbit design of KufaSat according to the calculated Keplerian elements has been simulated and analyzed by using MATLAB first and then by using General Mission Analysis Tool.

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List, Meike, Stefanie Bremer, Benny Rievers, and Hanns Selig. "Modelling of Solar Radiation Pressure Effects: Parameter Analysis for the MICROSCOPE Mission." International Journal of Aerospace Engineering 2015 (2015): 1–14. http://dx.doi.org/10.1155/2015/928206.

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Modern scientific space missions pose high requirements on the accuracy of the prediction and the analysis of satellite motion. On the one hand, accurate orbit propagation models are needed for the design and the preparation of a mission. On the other hand, these models are needed for the mission data analysis itself, thus allowing for the identification of unexpected disturbances, couplings, and noises which may affect the scientific signals. We present a numerical approach for Solar Radiation Pressure modelling, which is one of the main contributors for nongravitational disturbances for Earth orbiting satellites. The here introduced modelling approach allows for the inclusion of detailed spacecraft geometries, optical surface properties, and the variation of these optical surface properties (material degradation) during the mission lifetime. By using the geometry definition, surface property definitions, and mission definition of the French MICROSCOPE mission we highlight the benefit of an accurate Solar Radiation Pressure modelling versus conventional methods such as the Cannonball model or a Wing-Box approach. Our analysis shows that the implementation of a detailed satellite geometry and the consideration of changing surface properties allow for the detection of systematics which are not detectable by conventional models.

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Chudoba, B., and W. Heinze. "Evolution of generic flight vehicle design synthesis." Aeronautical Journal 114, no. 1159 (September 2010): 549–67. http://dx.doi.org/10.1017/s0001924000004036.

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AbstractWhen defining a new product like an aircraft, space access vehicle or space mission, the Advanced Projects Group evaluates the available design space and compares it with the design space required to accomplish the specified mission. As with any product development process, the general life-cycle characteristics are established first during the conceptual design (CD) phase, clearly before a design proposal can be released to the follow-on design phases such as preliminary design (PD), detail design (DD), flight test (FT), and finally operation and disposal. As a rule of thumb, it can be assumed that around 80% of the flight vehicle configuration and mission tandem are determined during the CD phase alone, which is the key phase where the initial brainstorming has to take place. Clearly, it is the responsibility of the CD team to simulate the entire life-cycle of the project from ‘cradle to grave’ where the focus is on correctness rather accuracy in order to identify the design space and offer an overall proof of design convergence. Currently, the important primary aerospace vehicle and mission design decisions at CD level are still made using extremely simple analysis and heuristics. A reason for this scenario is the difficulty in synthesising the range of individual design disciplines for both, classical and novel aerospace vehicle conceptual designs, in more than anad hocfashion. Although the CD segment is seen as the most important step in the product development phase due to its pre-defining function, it is the least well understood part of the entire product evolution process due to its level of abstraction. This paper presents the roadmap towards the next generation of aerospace life-cycle synthesis systems, a software and management process capable to immediately calculate cost and time implications while simultaneously linking design, manufacturing, testing, and operation. A historical review of how design has been accomplished until today is presented. The design approaches are categorised and the characteristics of today’s state-of-the-art design synthesis systems are discussed. A specification for the new class of intelligent generic design synthesis systems is presented capable of satisfying the demands imposed by the new breed of high-performance aircraft, space access vehicles, space missions, and others. Finally, the development status of the next generation aerospace vehicle design synthesis (AVDS-PrADO) simulation-based acquisition environment is presented.

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Van Bossuyt, Douglas L., Paul Beery, Bryan M. O’Halloran, Alejandro Hernandez, and Eugene Paulo. "The Naval Postgraduate School’s Department of Systems Engineering Approach to Mission Engineering Education through Capstone Projects." Systems 7, no. 3 (August 4, 2019): 38. http://dx.doi.org/10.3390/systems7030038.

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This article presents an educational approach to applied capstone research projects using a mission engineering focus. It reviews recent advances in mission engineering within the Department of Defense and integrates that work into an approach for research within the Systems Engineering Department at the Naval Postgraduate School. A generalized sequence of System Definition, System Modeling, and System Analysis is presented as an executable sequence of activities to support analysis of operational missions within a student research project at Naval Postgraduate School (NPS). That approach is detailed and demonstrated through analysis of the integration of a long-range strike capability on a MH-60S helicopter. The article serves as a demonstration of an approach for producing operationally applicable results from student projects in the context of mission engineering. Specifically, it demonstrates that students can execute a systems engineering project that conducts system-level design with direct consideration of mission impacts at the system of systems level. Discussion of the benefits and limitations of this approach are discussed and suggestions for integrating mission engineering into capstone courses are provided.

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Hwang, Hoyon, Jaeyoung Cha, and Jon Ahn. "Solar UAV design framework for a HALE flight." Aircraft Engineering and Aerospace Technology 91, no. 7 (July 8, 2019): 927–37. http://dx.doi.org/10.1108/aeat-03-2017-0093.

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Purpose The purpose of this paper is to present the development of an optimal design framework for high altitude long endurance solar unmanned aerial vehicle. The proposed solar aircraft design framework provides a simple method to design solar aircraft for users of all levels of experience. Design/methodology/approach This design framework consists of algorithms and user interfaces for the design of experiments, optimization and mission analysis that includes aerodynamics, performance, solar energy, weight and flight distances. Findings The proposed sizing method produces the optimal solar aircraft that yields the minimum weight and satisfies the constraints such as the power balance, the night time energy balance and the lift coefficient limit. Research limitations/implications The design conditions for the sizing process are given in terms of mission altitudes, flight dates, flight latitudes/longitudes and design factors for the aircraft configuration. Practical implications The framework environment is light and easily accessible as it is implemented using open programs without the use of any expensive commercial tools or in-house programs. In addition, this study presents a sizing method for solar aircraft as traditional sizing methods fail to reflect their unique features. Social implications Solar aircraft can be used in place of a satellite and introduce many advantages. The solar aircraft is much cheaper than the conventional satellite, which costs approximately $200-300m. It operates at a closer altitude to the ground and allows for a better visual inspection. It also provides greater flexibility of missions and covers a wider range of applications. Originality/value This study presents the implementation of a function that yields optimized flight performance under the given mission conditions, such as climb, cruise and descent for a solar aircraft.

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Genta, Giancarlo, and P. Federica Maffione. "IRMA: a Graphical Tool for Interplanetary Mission Design." MATEC Web of Conferences 210 (2018): 02049. http://dx.doi.org/10.1051/matecconf/201821002049.

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Designing an interplanetary mission is a complex task and requires the choice of the launch opportunity and of the exact launch and arrival dates. Depending on these choices, the trajectory must be defined and, in case of continuous thrust, also the thrust profile needs to be optimized.. Traditionally, these choices are made using some plots which allow to find a good compromise between the travel duration and the cost of the mission, which is often expressed in terms of initial mass in Earth orbit (IMLEO). IRMA (InterPlanetary Mission Analysis) code, based on the MATLAB®environment, is here described. It allows to deal with both impulsive propulsion (using the patched conics approach) and low continuous thrust (Solar or Nuclear electric or propellantless, like solar sails). A specific solver, based on indirect optimization techniques, has been developed specifically for this program, but IRMA can be used also as an interface for standard solvers, based on direct methods, like the FALCON.m code.

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Lintern, Gavan, Diane Miller, and Keith Baker. "Work Centered Design of a Usaf Mission Planning System." Proceedings of the Human Factors and Ergonomics Society Annual Meeting 46, no. 3 (September 2002): 531–35. http://dx.doi.org/10.1177/154193120204600366.

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In large-scale socio-technical systems such as military command and control, operators must work with complex and dynamic information from many diverse sources. For this project, we used the Cognitive Work Analysis and Ecological Interface Design frameworks to design a virtual workspace for the USAF work domain of Special Assignment Airlift Mission planning. Based on information made available through the analysis, we developed a workspace prototype in which multiple View-Ports house distinct functional requirements and in which options are made available to link various View-Port functionalities in the mission planning process. In this paper we illustrate how we bridged the gap between analysis and design by developing a link from the analytic products of our Cognitive Work Analysis to the design of the ecological workspace.

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Wadas, Linda R. "Mission statements in academic libraries: a discourse analysis." Library Management 38, no. 2/3 (March 14, 2017): 108–16. http://dx.doi.org/10.1108/lm-07-2016-0054.

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Purpose The purpose of this paper is to determine how academic library mission statements are related to their parent institution mission statements. Design/methodology/approach Using a random sample of the US colleges and universities, library and their respective college or university mission statements were compared using discourse analysis. Findings This study shows a very weak link between college or university mission statements and library mission statements in the majority of cases. Originality/value This paper opens a discussion of the value and purpose of library mission statements with the context of parent institution mission statements.

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Abbas, Naqvi Najam, Han Xiao, Li Yan Jun, and Muhammad Raza. "An Architecture Analysis of ADCS for CubeSat: A Recipe for ADCS Design of ICUBE." Applied Mechanics and Materials 110-116 (October 2011): 5397–404. http://dx.doi.org/10.4028/www.scientific.net/amm.110-116.5397.

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This research article presents the architecture analysis and design of Attitude determination and control subsystem (ADCS) of the Pico-Satellites especially the CubeSat, developed and launched into the Low Earth orbit (LEO). ADCS is not a stringent requirement for all the CubeSat missions but several missions were specifically designed to test and validate the ADCS. This paper contributes in evaluating the previous ADCS of CubeSat and presents an optimal ADCS design and a recipe for any CubeSat mission and specifically for the upcoming ICUBE of the Institute of Space Technology (IST), Pakistan. The proposed ADCS for ICUBE includes GPS receiver as position sensor while magnetometer as attitude sensor and magnetic coils as the active actuators. The determination will be done by Kalman filter and LQR will be used as a controller.

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Buckshaw, Donald L., Gregory S. Parnell, Willard L. Unkenholz, Donald L. Parks, James M. Wallner, and O. Sami Saydjari. "Mission Oriented Risk and Design Analysis of Critical Information Systems." Military Operations Research 10, no. 2 (March 1, 2005): 19–38. http://dx.doi.org/10.5711/morj.10.2.19.

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Rand, Omri, and Vladimir Khromov. "Mission Oriented Multi-Prop UAV Analysis Using Statistical Design Trends." Aerospace 8, no. 11 (October 28, 2021): 321. http://dx.doi.org/10.3390/aerospace8110321.

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This paper presents a methodology for the sizing and preliminary analysis of Multi-Prop UAVs. The methodology is founded on design trends that emerge from a vast and unique database that has been collected for such vehicles. The database includes geometry parameters, components’ weight, the power required, and flight performance estimation. For a given mission, the analysis enables optimization of a specific design of a Multi-Prop configuration for either minimal weight or minimal dimensions. As opposed to low-order and relatively simple analyses that are typically used in early design stages, the results presented in this paper include design trends and correlations within existing flying configurations and, therefore, contain many design constraints that typically emerge only during advanced stages of the design process.

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Yu, D.-R., X.-W. Lv, W. Bao, and Z.-L. Yao. "Preliminary design analysis of a hopper vehicle for Mars mission." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 224, no. 3 (December 2, 2009): 283–91. http://dx.doi.org/10.1243/09544100jaero615.

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Ding, Yu. "Design and Analysis of Accelerated Tests for Mission-Critical Reliability." Technometrics 47, no. 2 (May 2005): 240. http://dx.doi.org/10.1198/tech.2005.s268.

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Padgett, David A., and Andre P. Mazzoleni. "Nullcline Analysis as an Analytical Tethered Satellite Mission Design Tool." Journal of Guidance, Control, and Dynamics 30, no. 3 (May 2007): 741–52. http://dx.doi.org/10.2514/1.20946.

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OGAWA, Naoko, Mutsuko Y. MORIMOTO, Yuichi TSUDA, Tetsuya YAMADA, Kazuhisa FUJITA, Tomohiro YAMAGUCHI, Yasuhiro KAWAKATSU, Takashi KUBOTA, and Jun'ichiro KAWAGUCHI. "Preliminary Mission Analysis and Orbit Design for Next Mars Exploration." TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 8, ists27 (2010): Tk_7—Tk_12. http://dx.doi.org/10.2322/tastj.8.tk_7.

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Wedde, Horst F., and Jon A. Lind. "Performance-Driven Design and Analysis for Distributed Mission-Critical Systems." IFAC Proceedings Volumes 28, no. 25 (November 1995): 151–62. http://dx.doi.org/10.1016/s1474-6670(17)44838-5.

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Castronuovo, Marco M. "Active space debris removal—A preliminary mission analysis and design." Acta Astronautica 69, no. 9-10 (November 2011): 848–59. http://dx.doi.org/10.1016/j.actaastro.2011.04.017.

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Sung, Dong-gyu, Eun-hak Koh, Ju-chan Kim, Yong-hyeon Nam, Jeong-ho Lee, Jae-seung Lee, Chan-bin Lee, Yeong-bae Jeon, Cheol-kyun Choi, and Jae woo Lee. "Flying-wing Type Compound Drone Design and Mission Accuracy Analysis." Journal of the Korean Society for Aviation and Aeronautics 26, no. 4 (December 2018): 122–28. http://dx.doi.org/10.12985/ksaa.2018.26.4.122.

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Alegre, Inés, Jasmina Berbegal-Mirabent, and Adrian Guerrero. "Mission statements: what university research parks tell us about timing." Journal of Business Strategy 40, no. 5 (September 3, 2019): 46–53. http://dx.doi.org/10.1108/jbs-11-2018-0191.

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Purpose Mission statements are a key element of any organization. Ideally, the mission statement should be written at the initial stages of an organization’s life to be a useful tool to guide future organization’s decisions and strategy. However, at the early stages of an organization’s life, the organization might still be under development with the objective and stakeholders not yet well-defined, and therefore, stating the mission so early on, might neglect some important elements. In this paper, the authors explore the difference in mission statement quality between missions that have been created at the birth stage of an organization versus missions that are just explicitly formulated once the organization is already well-established and an underlying implicit mission already exists. The authors use as an empirical setting university research parks. Design/methodology/approach The authors evaluate mission statement quality using content analysis. The authors then test the differences on mission statement quality between two groups of research parks, those that have followed a creation strategy versus those that have followed a formulation strategy, using mean of differences test. Findings The authors find that a formulation strategy produces more complete mission statements than the creation strategy. Research parks that have followed a formulation strategy include in their mission statements more references to relevant stakeholders, such as investors, than parks following a creation strategy with respect to their mission statement. Research limitations/implications The research setting is Spanish Science Parks. This research setting is appropriate to answer the research question, as two Park creation strategies, planned and unplanned, allow the researchers to clearly differentiate between two mission conception strategies. However, the sample size is rather small. Practical implications Research has shown that a well-defined mission helps organizations focus and strategy formulation. The authors’ research offers some guidance on how to achieve a high-quality mission statement which will, in turn, help organizations have a better definition of their purpose. Originality/value Research until now has assumed that the mission statement should be formulated at the initial stages of the organization’s life. The authors’ research shows that defining the mission statement later in the process creates higher-quality mission statements that better reflect the organizations purpose and relevant stakeholders.

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Journal articles on the topic 'Mission design and analysi'

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