Relevant bibliographies by topics / Hypersonic transportation vehicles

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Academic literature on the topic 'Hypersonic transportation vehicles'

Author: Grafiati
Published: 6 September 2023

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Journal articles on the topic "Hypersonic transportation vehicles"

1

Liu, Hao, Jiansong Zhang, and Jianxiang Xi. "Robust nonlinear controller design for uncertain hypersonic vehicles." CEAS Aeronautical Journal 10, no. 2 (July 20, 2018): 357–66. http://dx.doi.org/10.1007/s13272-018-0320-5.

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Ferretto, Davide, Roberta Fusaro, and Nicole Viola. "Innovative Multiple Matching Charts approach to support the conceptual design of hypersonic vehicles." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 234, no. 12 (April 24, 2020): 1893–912. http://dx.doi.org/10.1177/0954410020920037.

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Several well-established best practices and reliable tools have been developed along the years to support aircraft conceptual and preliminary design. In this context, one of the most widely used tool is the Matching Chart (MC), a graphical representation of the different performance requirements (curves representing the thrust-to-weight ratio (T/W) requirement as function of the wing loading (W/S)) for each mission phase. The exploitation of this tool allows the identification of a feasible design space as well as the definition of a reference vehicle configuration in terms of maximum thrust, maximum take-off weight, and wing surface since the very beginning of the design process. Although the tool was originally developed for conventional aircraft, several extensions and updates of the mathematical models have been proposed over the years to widen its application to innovative configurations. Following this trend, this paper presents a further evolution of the MC model to support the conceptual design of high-speed transportation systems, encompassing supersonic and hypersonic flight vehicles. At this purpose, this paper reports and discusses the updates of the methodology laying behind the generation of the MC for high-speed transportation. Eventually, the results of the validation of the updated methodology and tool are reported, using as case study, the STRATOFLY MR3 vehicle configuration, a Mach 8 antipodal civil transportation system, currently under development within the H2020 STRATOFLY project.
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Bandivadekar, Deep, and Edmondo Minisci. "Modelling and Simulation of Transpiration Cooling Systems for Atmospheric Re-Entry." Aerospace 7, no. 7 (July 1, 2020): 89. http://dx.doi.org/10.3390/aerospace7070089.

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Aerothermodynamic heating is one of the primary challenges faced in progressing towards reliable hypersonic transportation. In the present study, the transpiration cooling method applied to the thermal protection system of re-entry vehicles is investigated. The complexity in analysing the incoming heat flux for re-entry lies not only in the extreme conditions of the flow but also in the fact that the coolant flow through the porous medium needs to be treated appropriately. While the re-entering spacecraft passes through various flow regimes, the peak conditions are faced only near continuum regime. Focusing on these conditions, traditional computational fluid dynamics techniques are used to model transpiration cooling for re-entry vehicles. In the current work, the open source CFD framework OpenFOAM is used to couple two different solvers iteratively and then analyse the thermal response for flow speed conditions typical of re-entry vehicles. Independent computations are performed using the explicit, loosely coupled procedure for high speed argon flow over a 2D axi-symmetrical cylindrical vehicle. The results presented indicate distinct heat flux drop along the surface of the cylindrical vehicle as a function of parameters such as coolant pressure and wall temperature.
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Fusaro, Roberta, and Nicole Viola. "Preliminary reliability and safety assessment methodology for trans-atmospheric transportation systems." Aircraft Engineering and Aerospace Technology 90, no. 4 (May 8, 2018): 639–51. http://dx.doi.org/10.1108/aeat-11-2016-0214.

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Purpose This paper aims to propose a methodology for a safety and reliability assessment for the conceptual and preliminary design of very complex and disrupting innovative systems like trans-atmospheric vehicles. The proposed methodology differs from existing ones because it does not rely on statistical data at aircraft-level but exploits the statistical population at components-level only. For the sake of clarity, the paper provides some preliminary results of the application of the methodology at system level. The example deals with the safety and reliability assessment of a very complex propulsion system aimed at guaranteeing vertical take-off and landing capabilities of a suborbital vehicle. Design/methodology/approach The proposed methodology is strongly based on a systems engineering approach. It exploits safety and reliability assessment analyses which have already been developed in both aeronautical and space engineering domains, but it combines them in an innovative way to overcome the lack of statistics at aircraft level. The methodology consists of two different steps: a qualitative top-down process, allowing a functional and physical decomposition of the transportation system and a following quantitative bottom-up approach, which provides the estimation of system-level reliability and safety characteristics starting from the statistical estimation of the components’ characteristics. Findings The paper presents a new methodology for the preliminary reliability and safety assessment of innovative transportation systems, such as hypersonic transportation systems. The envisaged methodology will overcome the poorness of statistical data that is usually affecting the conceptual design of breakthrough systems. Research limitations/implications The paper shows the application of the articulated methodology to a limited case study. A complete example of application of the methodology to estimate safety and reliability characteristics at vehicle level will be provided in feature works. Practical implications The methodology has been proposed to be exploited in international research activities in the field of hypersonic transportation systems. Furthermore, a massive application of this approach would allow to create a database for the generation and the update of semi-empirical models focused on high-level estimations of reliability, availability, maintainability and safety (RAMS) characteristics. Moreover, the proposed safety assessment has been conceived to be fully integrated within a typical conceptual design process. Originality/value The existing literature about safety and reliability assessment at the early design stages proposes pure statistical approaches which are usually not applicable to highly innovative products, where the statistical population is not existing, for example, in the case of trans-atmospheric vehicles. This paper describes how to overcome this problem, through the exploitation of statistical data at components-level only through the combination of these data to estimate RAMS characteristics at aircraft-level thanks to functional analysis, concept of operations and typical safety assessment tools, like functional hazard analysis, failure mode and effect analysis, reliability block diagram and fault tree analysis.
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Baek, Jongdae. "Two-Dimensional LiDAR Sensor-Based Three-Dimensional Point Cloud Modeling Method for Identification of Anomalies inside Tube Structures for Future Hypersonic Transportation." Sensors 20, no. 24 (December 17, 2020): 7235. http://dx.doi.org/10.3390/s20247235.

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The hyperloop transportation system has emerged as an innovative next-generation transportation system. In this system, a capsule-type vehicle inside a sealed near-vacuum tube moves at 1000 km/h or more. Not only must this transport tube span over long distances, but it must be clear of potential hazards to vehicles traveling at high speeds inside the tube. Therefore, an automated infrastructure anomaly detection system is essential. This study sought to confirm the applicability of advanced sensing technology such as Light Detection and Ranging (LiDAR) in the automatic anomaly detection of next-generation transportation infrastructure such as hyperloops. To this end, a prototype two-dimensional LiDAR sensor was constructed and used to generate three-dimensional (3D) point cloud models of a tube facility. A technique for detecting abnormal conditions or obstacles in the facility was used, which involved comparing the models and determining the changes. The design and development process of the 3D safety monitoring system using 3D point cloud models and the analytical results of experimental data using this system are presented. The tests on the developed system demonstrated that anomalies such as a 25 mm change in position were accurately detected. Thus, we confirm the applicability of the developed system in next-generation transportation infrastructure.
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Fusaro, Roberta, Nicole Viola, Marco Fioriti, Davide Ferretto, and Sara Cresto Aleina. "Preliminary design of a cabin escape system for a suborbital vehicle aimed at parabolic flights." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 231, no. 12 (August 2, 2017): 2179–91. http://dx.doi.org/10.1177/0954410017723671.

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The paper deals with the conceptual design and sizing of a cabin escape system to be applied to a trans-atmospheric transportation system. At first, the role of suborbital vehicles towards the development of a hypersonic transportation system is presented. From this analysis, it has been clear that one of the key points in enhancing the public consensus is to demonstrate a higher level of safety and reliability with respect to the current space vehicles. Since the time of the Space Shuttle enterprise, the development of a proper escape system has been considered crucial to diminish the risk of loss of lives per mission, moving from space-like reliability characteristics to values closer to the aeronautical case. In particular, this paper presents the conceptual design of an escape system for a single stage vehicle aimed at parabolic flights. The proposed design methodology starts with the identification of the major requirements that will lead the design and sizing activities. Then, special attention is devoted to the identification of the required capabilities of a Cabin Escape System and to the selection of the proper subsystems able to guarantee these functionalities. Indeed, considering the high-level of complexity of such a system, during the design process, specific attention should be paid to the impact of on-board systems integration on the overall transportation system architecture and layout. At this purpose, a proper utilization of CAD models can ease the integration process allowing fast verification of mass and volume budgets as well as integrated simulation techniques could be useful. Furthermore, the possibility of exploiting this system during the different phases of the mission should be properly evaluated and, eventually, a preliminary impact risk analysis is reported.
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Xu, Fei, Guangle Gao, and Longqiang Ni. "A New Adaptive Federated Cubature Kalman Filter Based on Chi-Square Test for SINS/GNSS/SRS/CNS Integration." Mathematical Problems in Engineering 2022 (March 24, 2022): 1–14. http://dx.doi.org/10.1155/2022/7588265.

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As an emerging means of transportation for the intelligent transportation system (ITS) in aviation and aerospace, hypersonic cruise vehicles (HCVs) have received numerous research interests during the past several decades. However, the navigation and positioning strictly limit the progress and application of HCVs due to their special characteristics on dynamics and environments. To improve the stability of navigation in HCVs, a chi-square test-based adaptive federated cubature Kalman filter (CAFCKF) is proposed in this paper. In the proposed approach, the chi-square test is adopted for the estimation of the measurement noise statistics firstly. Subsequently, a new adaptive information fusion factor is designed for the federated filter to adjust the contribution of each subsystem. Finally, the information sharing factor, which is used for the amendment of the state covariance of each subsystem, is refined based on the judging index of the chi-square test accordingly. Simulation results show that the proposed CAFCKF can be used to improve the accuracy and stability of the navigation system.
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Chudoba, B., G. Coleman, X. Huang, and P. A. Czysz. "Conceptual design assessment of a suborbital tourist space access vehicle." Aeronautical Journal 112, no. 1135 (September 2008): 523–35. http://dx.doi.org/10.1017/s0001924000002487.

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Abstract Space transportation remains in the pioneering stages. What might this century bring if we had a ‘railroad to space’ that embodied the characteristics of the transcontinental undertaking? The X-33 and Venture Star projects were one attempt to achieve the characteristics of that transcontinental railroad. There are others, here and in other countries, but perhaps we need to begin with a smaller first step, a small, commercial reusable rocket with ballistic ascent to space altitude with a hypersonic glider return? Our challenge in space today is to develop vehicles that are in continuous use, maintained and operated on a fixed schedule despite weather or environmental hazards, which move payloads not only into space but back again. The X PRIZE was a $10 million prize awarded to Scaled Composites as the first privately financed spaceship that launched the equivalent of three persons to an altitude of at least 100 kilometers on two consecutive flights within two weeks. What about an analogous vehicle that flies two or three times a week, every week for a number of years? A major difference is that this challenge is to be accomplished without government support or government developed vehicles. The aerospace vehicle design (AVD) Laboratory team at the University of Texas at Arlington is developing a generic space access vehicle (SAV) design synthesis environment with focus on the conceptual design phase. The AVD Lab has applied elements of this toolbox to the study of a tourist aerospace vehicle under a grant from Rocketplane Limited, Inc. The development of a low-cost tourist vehicle based on the adaptation of a Learjet 25/35/45 series aircraft is the focus of this paper.
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Kumar, SS Satheesh, M. Sudhakara Rao, I. Balasundar, Amit Kumar Singh, T. Raghu, and G. Madhusudhan Reddy. "Compressive behaviour of a nickel superalloy Superni 263 honeycomb sandwich panel." Journal of Sandwich Structures & Materials 22, no. 5 (July 10, 2018): 1426–49. http://dx.doi.org/10.1177/1099636218786438.

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Metallic thermal protection systems comprising of sandwich panels consisting of hexagonal honeycomb sandwich structures are envisaged to be used in advanced transportation systems like hypersonic vehicles and reusable launch vehicles. The assessment of compressive mechanical behaviour is necessary to understand the response of sandwich structures to aerothermal loads. The fabrication methodology for realizing Ni based superalloy Superni 263 hexagonal honeycomb sandwich panels is established. This work is aimed at understanding the effect of sandwich panel geometry parameters like hexagonal cell size and core thickness on the out-of-plane flatwise compressive behaviour at room temperature. The ultimate compressive strength decreases with increasing core height irrespective of the cell sizes investigated. The dependence of specific compressive strength on the cell size is established by a power law relationship. The compressed sandwich panels subjected to understand the deformation behaviour indicated the dominance of cell wall bending and occasional fracture, however in the case of sandwich panels with higher core thickness cell wall buckling coupled with shearing at the face sheet vicinity is noticed.
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DOGRA, Bharat Ankur, Mehakveer SINGH, Tejinder Kumar JINDAL, and Subhash CHANDER. "Technological advancements in Pulse Detonation Engine Technology in the recent past: A Characterized Report." INCAS BULLETIN 11, no. 4 (December 8, 2019): 81–92. http://dx.doi.org/10.13111/2066-8201.2019.11.4.8.

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Pulse Detonation Engine (PDE), is an emerging and promising propulsive technology all over the world in the past few decades. A pulse detonation engine (PDE) is a type of propulsion system that uses detonation waves to combust the fuel and oxidizer mixture. Theoretically, a PDE can be operate from subsonic to hypersonic flight speeds. Pulsed detonation engines offer many advantages over conventional air-breathing engines and are regarded as potential replacements for air-breathing and rocket propulsion systems, for platforms ranging from subsonic unmanned vehicles, long-range transportation, high-speed vehicles, space launchers to space vehicles. This article highlights the operating cycle of PDE, starting with the fuel-oxidizer mixture, combustion and Deflagration to detonation transition (DDT) followed by purging. PDE combustion process, a unique process, leads to consistent and repeatable detonation waves. This pulsed detonation combustion process causes rapid burning of the fuel-oxidizer mixture, which cannot be seen in any other combustion process as it is a thousand times faster than any other mode of combustion. PDE not only holds the capability of running effectively up to Mach 5 but it also changes the technicalities in space propulsion. The present paper is the extension of the previous study which is also a well characterized status report of PDE in different areas. The present study deals with the categorization of the design approach, computations & simulations, flow visualization, DDT & Thrust enhancement, PDRE’s, experimental detonation engines with some of the experience and research undertaken in Punjab Engineering College under the complete supervision and guidance of Prof. Tejinder Kumar Jindal followed by applications of PDE technology.
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Books on the topic "Hypersonic transportation vehicles"

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Viviani, Antonio, and Giuseppe Pezzella. Hypersonic Vehicles: Applications, Recent Advances, and Perspectives. IntechOpen, 2022.

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Zhao, Min. Prediction and Validation Technologies of Aerodynamic Force and Heat for Hypersonic Vehicle Design. Springer Singapore Pte. Limited, 2021.

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Zhao, Min. Prediction and Validation Technologies of Aerodynamic Force and Heat for Hypersonic Vehicle Design. Springer, 2022.

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Conference papers on the topic "Hypersonic transportation vehicles"

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Kremer, Frans G. J. "Balance of Moments for Hypersonic Vehicles." In ASME 1992 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1992. http://dx.doi.org/10.1115/92-gt-251.

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Ramjet engines propelling hypersonic flight vehicles will be highly integrated into the vehicle, resulting in strong interactions between the vehicle and the engine. An assessment of these interactions in relation to the flight mission is made by simple but adequate modeling of the flight vehicle aerodynamics and the engine performance. Especially moments associated with the propulsion system are of interest. This paper deals with the pitch moments introduced by the ramjet related forces, which are evaluated by one-dimensional engine performance and by modeling of the inlet and nozzle flow. Furthermore, it discusses the balance of moments for the first stage of a two stage transportation system for an ascent trajectory.
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Fujii, Kenji, Toshiya Nakamura, Hiroshi Kawato, and Shigeya Watanabe. "Concepts and Studies of Flight Experiment Vehicles for Reusable Space Transportation System." In 12th AIAA International Space Planes and Hypersonic Systems and Technologies. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.2003-6984.

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Callens, Natacha, Marie-Christine Bernelin, Philippe Coué, Marine Regnier, and Mathieu Beylard. "The Student Aerospace Challenge: a european multidisciplinary contest and tertiary educational programme." In Symposium on Space Educational Activities (SSAE). Universitat Politècnica de Catalunya, 2022. http://dx.doi.org/10.5821/conference-9788419184405.054.

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Inspired by the first successful tests of a private manned spaceplane in 2004, the Student Aerospace Challenge was created in 2006 by the European Astronaut Club and its partners - Dassault Aviation, the European Space Agency, the International Astronautical Federation, Safran and Thales at the time - to allow European university students to explore some aspects of manned suborbital vehicles. Until 2020, the Challenge focused on a local reusable vehicle reaching Mach 3.5 and an altitude of 100 km. Since the 15th edition, to better respond to the evolution of the sector, a second vehicle is proposed: a hypersonic vehicle dedicated to point-to-point transportation taking, for example, less than two hours to travel from Barcelona to Tokyo. Each year, the Steering Committee defines several work packages corresponding to a large variety of study domains realistically related to this type of innovative vehicles like aerodynamic and flight control, structure, reusable propulsion, airworthiness, promotion, market analysis, legal frame & medicine. The introduction of a second vehicle having a quite different mission led the Committee to introduce dedicated topics. In addition, for the current edition, a new work package was proposed to cover potential applications of suborbital flights other than carrying passengers. In function of their background and interest, European University students have the opportunity to work, during several months, on a topic related to one of the work packages and to explore new solutions. Proposed projects should be technically realistic, economically viable and environmentally friendly. Reports and posters issued by student teams are evaluated by the Steering Committee some weeks before the “Suborbital Day”, a dedicated event organised like a mini-symposium, usually on-site where students present orally their projects and meet representatives of the different partners. The best-quoted projects are rewarded with prizes, among them, the ESA Grand Prize offering the winner team the unique opportunity to present their project in an appropriate European space-related event. To date, 216 teams and 998 University students coming from all over Europe already took part in the Student Aerospace Challenge, a motivating and ambitious multidisciplinary educational programme. Their participation allowed them to complement their knowledge, learn new skills and enlarge their network in the space sector
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Mayrhofer, M., and G. Sachs. "Mission safety concept for a two-stage space transportation vehicle." In 10th AIAA/NAL-NASDA-ISAS International Space Planes and Hypersonic Systems and Technologies Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-1789.

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Bottacini, Massimiliano, Luciano Basile, and Flavio Bandini. "Crew Compartments Design and Development for Human Space Transportation and Exploration Vehicles." In AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.2005-3367.

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Wu, Nan, and Jia Yu. "Robust Controller Design of Hypersonic Vehicle in Uncertainty Models." In 3rd International Conference on Electromechanical Control Technology and Transportation. SCITEPRESS - Science and Technology Publications, 2018. http://dx.doi.org/10.5220/0006969302880293.

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Zeng, Jianghui, and Yongming Gao. "Positioning and Tracking Performance Analysis of Hypersonic Vehicle Based on Cubature Kalman Filter." In Proceedings of the 2018 International Conference on Transportation & Logistics, Information & Communication, Smart City (TLICSC 2018). Paris, France: Atlantis Press, 2018. http://dx.doi.org/10.2991/tlicsc-18.2018.7.

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