Добірка наукової літератури з теми "Launch Vehicle Model"
Оформте джерело за APA, MLA, Chicago, Harvard та іншими стилями
Ознайомтеся зі списками актуальних статей, книг, дисертацій, тез та інших наукових джерел на тему "Launch Vehicle Model".
Біля кожної праці в переліку літератури доступна кнопка «Додати до бібліографії». Скористайтеся нею – і ми автоматично оформимо бібліографічне посилання на обрану працю в потрібному вам стилі цитування: APA, MLA, «Гарвард», «Чикаго», «Ванкувер» тощо.
Також ви можете завантажити повний текст наукової публікації у форматі «.pdf» та прочитати онлайн анотацію до роботи, якщо відповідні параметри наявні в метаданих.
Статті в журналах з теми "Launch Vehicle Model"
You, Ming, Qun Zong, Bailing Tian, and Fanlin Zeng. "Nonsingular terminal sliding mode control for reusable launch vehicle with atmospheric disturbances." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 11 (May 8, 2017): 2019–33. http://dx.doi.org/10.1177/0954410017708211.
Повний текст джерелаGibson, Denton, Waldemar Karwowski, Timothy Kotnour, Luis Rabelo, and David Kern. "The Relationships between Organizational Factors and Systems Engineering Process Performance in Launching Space Vehicles." Applied Sciences 12, no. 22 (November 14, 2022): 11541. http://dx.doi.org/10.3390/app122211541.
Повний текст джерелаHladkyi, Ye H., and V. I. Perlyk. "How Yuzhnoye develops models for flight safety index evaluation for the case of a rocket failure during the flight." Kosmičeskaâ tehnika. Raketnoe vooruženie 2023, no. 1 (May 12, 2023): 14–30. http://dx.doi.org/10.33136/stma2023.01.014.
Повний текст джерелаPu, Pengyu, and Yi Jiang. "Assessing Turbulence Models on the Simulation of Launch Vehicle Base Heating." International Journal of Aerospace Engineering 2019 (August 22, 2019): 1–14. http://dx.doi.org/10.1155/2019/4240980.
Повний текст джерелаda Cás, Pedro L. K., Carlos A. G. Veras, Olexiy Shynkarenko, and Rodrigo Leonardi. "A Brazilian Space Launch System for the Small Satellite Market." Aerospace 6, no. 11 (November 12, 2019): 123. http://dx.doi.org/10.3390/aerospace6110123.
Повний текст джерелаAdelfang, S. I., O. E. Smith, and G. W. Batts. "Ascent wind model for launch vehicle design." Journal of Spacecraft and Rockets 31, no. 3 (May 1994): 502–8. http://dx.doi.org/10.2514/3.26467.
Повний текст джерелаWang, J. T., G. Y. Hang, H. M. Shen, Z. Y. Liu, H. J. Xue, T. Wang, and W. Yu. "Numerical Simulation of Shock Wave Damage to Medium-Range and Long-Range Targets." Journal of Physics: Conference Series 2478, no. 2 (June 1, 2023): 022002. http://dx.doi.org/10.1088/1742-6596/2478/2/022002.
Повний текст джерелаGolubek, A. V., and N. M. Dron'. "Launch Vehicle Rendezvous to Catalogued Orbital Debris while Injecting into Highly-Inclined Orbits." Nauka ta innovacii 16, no. 6 (June 12, 2020): 46–55. http://dx.doi.org/10.15407/scin16.06.046.
Повний текст джерелаGolubek, A. V., and N. M. Dron'. "Launch Vehicle Rendezvous to Catalogued Orbital Debris while Injecting into Highly-Inclined Orbits." Science and innovation 16, no. 6 (November 2020): 46–55. http://dx.doi.org/10.15407/scine16.06.046.
Повний текст джерелаPeng, Bo, Cheng Ma, Guodong Wang, Fengyan Hu, Ke Mei, and Jian Yang. "An aerodynamic surrogate model of launch vehicle based on relevance vector machine." Journal of Physics: Conference Series 2181, no. 1 (January 1, 2022): 012021. http://dx.doi.org/10.1088/1742-6596/2181/1/012021.
Повний текст джерелаДисертації з теми "Launch Vehicle Model"
Plaisted, Clinton. "DESIGN OF AN ADAPTIVE AUTOPILOT FOR AN EXPENDABLE LAUNCH VEHICLE." Master's thesis, University of Central Florida, 2008. http://digital.library.ucf.edu/cdm/ref/collection/ETD/id/2834.
Повний текст джерелаM.S.A.E.
Department of Mechanical, Materials and Aerospace Engineering
Engineering and Computer Science
Aerospace Engineering MSAE
Martin, Andrew Allen 1977. "Model predictive control for ascent load management of a reusable launch vehicle." Thesis, Massachusetts Institute of Technology, 2002. http://hdl.handle.net/1721.1/8126.
Повний текст джерелаIncludes bibliographical references (p. 188-189).
During the boost phase of ascent, winds have a significant impact on a launch vehicle's angle of attack, and can induce large structural loads on the vehicle. Traditional methods for mitigating these loads involve measuring the winds prior to launch and designing trajectories to minimize the vehicle angle of attack (a). The current balloon-based method of collecting wind field information produces wind profiles with significant uncertainty due to the inherent time delays associated with balloon measurement procedures. Managing the mission risk caused by these uncertain wind measurements has always been important to control system designers. This thesis will describe a novel approach to managing structural loads through the combination of a Light Detection and Ranging (LIDAR) wind sensor, and Model Predictive Control (MPC). LIDAR wind sensors can provide near real-time wind measurements, significantly reducing wind uncertainty at launch. MPC takes full advantage of this current wind information through a unique combination of proactive control, constraint integration and tuning flexibility. This thesis describes the development of two types of MPC controllers, as well as a baseline controller representative of current control methods used by industry. A complete description of Model Predictive Control theory and derivation of the necessary control matrices is included. The performance of each MPC controller is compared to that of the baseline controller for a wide range of wind profiles from both the Eastern and Western U.S. Test Ranges. Both MPC controllers are shown to provide reductions of greater than 50% in a, Qa and structural bending moments. In addition, the effects of wind measurement delays and uncertainty on the performance of each controller are investigated.
by Andrew Allen Martin.
S.M.
LePome, Robert C. (Robert Charles) 1977. "Model predictive control for terminal area energy management and approach and landing for a reusable launch vehicle." Thesis, Massachusetts Institute of Technology, 2002. http://hdl.handle.net/1721.1/8125.
Повний текст джерелаIncludes bibliographical references (p. 235-236).
The space industry plans to develop new reusable launch vehicles. The new vehicles will need advanced, new guidance and control systems. Since 1996 Draper Laboratory has been developing the next generation guidance and control for reusable launch vehicles in which guidance and control is integrated into one correlated system. Draper's research of integrated guidance and control originated with a single loop multivariable control scheme using time-invariant linear quadratic regulator theory. The research has since evolved into the use of model predictive control theory. The main focus of this thesis is the theory and design of model predictive control for entry of aerospace vehicles. The goal is to develop design criteria and guidelines explaining how to select the model predictive control parameters: prediction horizon, simulation rates, and weighting matrices. A secondary goal is to tightly couple an onboard trajectory generation algorithm with the model predictive controller to improve tracking performance and robustness. Favorable tracking is achieved through two model predictive control architectures, which are discussed. The first architecture has an inner loop stability augmentation system with model predictive control used as an outer loop. The second architecture replaces the inner and outer loops with a single model predictive controller. The two architectures demonstrate the flexibility of model predictive control to adapt to new vehicles; the model predictive control may be used to augment an existing inner loop or may be used as a stand-alone controller. The design focuses primarily on the architecture without a stability augmentation system.
by Robert C. LePome, II.
S.M.
Brevault, Loïc. "Contributions à l'optimisation multidisciplinaire sous incertitude, application à la conception de lanceurs." Thesis, Saint-Etienne, EMSE, 2015. http://www.theses.fr/2015EMSE0792/document.
Повний текст джерелаLaunch vehicle design is a Multidisciplinary Design Optimization problem whose objective is to find the launch vehicle architecture providing the optimal performance while ensuring the required reliability. In order to obtain an optimal solution, the early design phases are essential for the design process and are characterized by the presence of uncertainty due to the involved physical phenomena and the lack of knowledge on the used models. This thesis is focused on methodologies for multidisciplinary analysis and optimization under uncertainty for launch vehicle design. Three complementary topics are tackled. First, two new formulations have been developed in order to ensure adequate interdisciplinary coupling handling. Then, two new reliability techniques have been proposed in order to take into account the various natures of uncertainty, involving surrogate models and efficient sampling methods. Eventually, a new approach of constraint handling for optimization algorithm ”Covariance Matrix Adaptation - Evolutionary Strategy” has been developed to ensure the feasibility of the optimal solution. All the proposed methods have been compared to existing techniques in literature on analysis and design test cases of launch vehicles. The results illustrate that the proposed approaches allow the improvement of the efficiency of the design process and of the reliability of the found solution
Leung, Martin S. K. "A real-time near-optimal guidance approach for launch vehicles." Diss., Georgia Institute of Technology, 1992. http://hdl.handle.net/1853/12022.
Повний текст джерелаFerreira, Julio Cesar Bolzani de Campos. "Data fusion and multiple models filtering for launch vehicle tracking and impact point prediction: the Alcântara case." Instituto Tecnológico de Aeronáutica, 2004. http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=679.
Повний текст джерелаSouza, Mateus Moreira de. "Sistema de controle de atitude para modelo de VLS fixo com 3 graus de liberdade." Universidade de São Paulo, 2012. http://www.teses.usp.br/teses/disponiveis/18/18148/tde-11102012-111244/.
Повний текст джерелаPole placement control system with filter was implemented to control the attitude of a satellite launch vehicle model. With this purpose, a model and a fixing base with three degrees of freedom was made. Utilizing the system response to step input with PID controller empirically designed to stabilize the system, the model characteristics were identified and the pole placement control system was designed. This system oscillated around the reference with amplitude smaller than 0.5° and peak time around 2.17 seconds. Another PID controller was designed analytically for reference, however the pole placement controller had better response characteristics than the PID controller. Both controllers can stabilize the system even when one engine is shut off.
Karthikeyan, N. "On the Contribution of the Launch Platform towards Acoustic Environment of a Launch Vehicle at Lift-off." Thesis, 2017. http://etd.iisc.ac.in/handle/2005/4313.
Повний текст джерелаTrikha, Manish. "Dynamics And Stability Of A Launch Vehicle." Thesis, 2010. https://etd.iisc.ac.in/handle/2005/1269.
Повний текст джерелаTrikha, Manish. "Dynamics And Stability Of A Launch Vehicle." Thesis, 2010. http://etd.iisc.ernet.in/handle/2005/1269.
Повний текст джерелаКниги з теми "Launch Vehicle Model"
NASA Dryden Flight Research Center., ed. Development of the X-33 aerodynamic uncertainty model. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 1998.
Знайти повний текст джерелаCobleigh, Brent R. Development of the X-33 aerodynamic uncertainty model. Edwards, Calif: Dryden Flight Research Center, 1998.
Знайти повний текст джерелаNASA Dryden Flight Research Center., ed. Development of the X-33 aerodynamic uncertainty model. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 1998.
Знайти повний текст джерелаNASA Dryden Flight Research Center., ed. Development of the X-33 aerodynamic uncertainty model. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 1998.
Знайти повний текст джерелаGeorge C. Marshall Space Flight Center., ed. A strategy for integrating a large finite element model using MSC NASTRAN/PATRAN: X-33 lessons learned. [Huntsville, Ala.]: National Aeronautics and Space Administration, Marshall Space Flight Center, 1999.
Знайти повний текст джерелаUnited States. National Aeronautics and Space Administration., ed. A transient model of the RL10A-3-3A rocket engine. [Washington, DC]: National Aeronautics and Space Administration, 1995.
Знайти повний текст джерелаCenter, Langley Research, ed. Aerothermodynamic calculations on X-34 at Mach 6 wind tunnel conditions. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1999.
Знайти повний текст джерелаWood, William A. Aerothermodynamic calculations on X-34 at Mach 6 wind tunnel conditions. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1999.
Знайти повний текст джерелаAmerican Institute of Aeronautics and Astronautics. Recommended practice: Space launch integration. Reston, VA: American Institute of Aeronautics and Astronautics, 2001.
Знайти повний текст джерелаJ, Vess Robert, North Carolina State University. Dept. of Mechanical and Aerospace Engineering., and Langley Research Center, eds. Design and fabrication of the NASA HL-20 full scale research model. Raleigh, NC: North Carolina State University, Mechnical and Aerospace Engineering, Mars Mission Research Center, 1991.
Знайти повний текст джерелаЧастини книг з теми "Launch Vehicle Model"
Jia, Jian, Weifeng Chen, and Zixuan Wang. "Aerodynamic Parameter Estimation for Launch Vehicles." In Autonomous Trajectory Planning and Guidance Control for Launch Vehicles, 201–13. Singapore: Springer Nature Singapore, 2023. http://dx.doi.org/10.1007/978-981-99-0613-0_7.
Повний текст джерелаLi, Xuefeng, Fan Xu, and Guoqiang Xu. "Model of Launch Vehicle Dynamics and Redundant Strapdown IMUs." In Redundant Inertial Measurement Unit Reconfiguration and Trajectory Replanning of Launch Vehicle, 5–34. Singapore: Springer Nature Singapore, 2022. http://dx.doi.org/10.1007/978-981-19-4637-0_2.
Повний текст джерелаMercer, J. F., G. S. Aglietti, M. Remedia, and A. M. Kiley. "Study of Correlation Criteria for Spacecraft-Launch Vehicle Coupled Loads Analysis." In Model Validation and Uncertainty Quantification, Volume 3, 337–47. Cham: Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-29754-5_33.
Повний текст джерелаAtkinson, Joseph P., Rory N. Thomas, and Roy C. Burton. "A Dynamic Model Tailored to Flexible Launch Vehicle Umbilical Analysis." In Topics in Modal Analysis II, Volume 6, 565–79. New York, NY: Springer New York, 2012. http://dx.doi.org/10.1007/978-1-4614-2419-2_57.
Повний текст джерелаKrishnan, Ranjani, and V. R. Lalithambika. "Modeling and Verification of Launch Vehicle Onboard Software Using SPIN Model Checker." In Transactions on Computational Science and Computational Intelligence, 131–39. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-49500-8_12.
Повний текст джерелаSchumann, Jan-Erik, Markus Fertig, Volker Hannemann, Thino Eggers, and Klaus Hannemann. "Numerical Investigation of Space Launch Vehicle Base Flows with Hot Plumes." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 179–91. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_11.
Повний текст джерелаYan, Xiaodong, and Cong Zhou. "Ascent Predictive Guidance for Thrust Drop Fault of Launch Vehicles Using Improved GS-MPSP." In Autonomous Trajectory Planning and Guidance Control for Launch Vehicles, 75–98. Singapore: Springer Nature Singapore, 2023. http://dx.doi.org/10.1007/978-981-99-0613-0_3.
Повний текст джерелаWan, Zhen, Rustam Ismatov, and Haiyan Xu. "Efficiency of Competitiveness Evaluation of Medium-Lift Launch Vehicle (MLV) Using Integrated DEA-TOPSIS Model." In Lecture Notes in Business Information Processing, 36–52. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-91768-5_3.
Повний текст джерелаBuehrle, Ralph D., Justin D. Templeton, Mercedes C. Reaves, Lucas G. Horta, James L. Gaspar, Paul A. Bartolotta, Russell A. Parks, and Daniel R. Lazor. "Ares I-X Launch Vehicle Modal Test Overview." In Structural Dynamics, Volume 3, 999–1009. New York, NY: Springer New York, 2011. http://dx.doi.org/10.1007/978-1-4419-9834-7_88.
Повний текст джерелаShuo, Wang, Huang Cong, and Wang Guanghui. "Model Free Adaptive Attitude Control Method for Launch Vehicles." In Lecture Notes in Electrical Engineering, 3587–93. Singapore: Springer Nature Singapore, 2023. http://dx.doi.org/10.1007/978-981-19-6613-2_348.
Повний текст джерелаТези доповідей конференцій з теми "Launch Vehicle Model"
Chen, Jiaye, Rongjun Mu, Xin Zhang, and Yanpeng Deng. "Reusable launch vehicle model uncertainties impact analysis." In Young Scientists Forum 2017, edited by Songlin Zhuang, Junhao Chu, and Jian-Wei Pan. SPIE, 2018. http://dx.doi.org/10.1117/12.2317531.
Повний текст джерелаADELFANG, S., O. SMITH, and G. BATTS. "A wind model for launch vehicle design." In 31st Aerospace Sciences Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-752.
Повний текст джерелаSinclair, Andrew, and George Flowers. "Low-Order Aeroelastic Model of Launch-Vehicle Dynamics." In AIAA Guidance, Navigation, and Control Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-7725.
Повний текст джерелаQu, Min, John Sohn, Peter Gage, John Bradford, and Brett Starr. "Generalized Vehicle Performance Closure Model for Two-Stage-to-Orbit Launch Vehicles." In 42nd AIAA Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-1221.
Повний текст джерелаChung, Y. T., and James Peebles. "Hybrid Interface Modal Model Formulation for Launch Vehicle Coupled Loads Analysis." In 45th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics & Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-1796.
Повний текст джерелаOrr, Jeb. "A Coupled Aeroelastic Model for Launch Vehicle Stability Analysis." In AIAA Atmospheric Flight Mechanics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-7642.
Повний текст джерелаGage, Peter, and Jeremy Vander Kam. "A Data Model for Evaluating Reusable Launch Vehicle Concepts." In 41st Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.2003-1330.
Повний текст джерелаDuque, Edson Luciano, Marco Antonio Barreto, and Agenor de Toledo Fleury. "Math Model to Simulate Clutch Energy During Vehicle Launch." In SAE Brasil 2009 Congress and Exhibit. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2009. http://dx.doi.org/10.4271/2009-36-0401.
Повний текст джерелаLiu, Jingbang, Xian Yu, Shangtai Jin, and Zhongsheng Hou. "Model Free Adaptive Attitude Control for a Launch Vehicle." In 2019 Chinese Control Conference (CCC). IEEE, 2019. http://dx.doi.org/10.23919/chicc.2019.8865199.
Повний текст джерелаBoglis, Ioana-Carmen, and Adrian M. Stoica. "Model Reference Adaptive Control Design for the VEGA Launch Vehicle." In 2019 E-Health and Bioengineering Conference (EHB). IEEE, 2019. http://dx.doi.org/10.1109/ehb47216.2019.8970009.
Повний текст джерелаЗвіти організацій з теми "Launch Vehicle Model"
Martindale, Michael. A Discrete-Event Simulation Model for Evaluating Air Force Reusable Military Launch Vehicle Post-Landing Operations. Fort Belvoir, VA: Defense Technical Information Center, June 2006. http://dx.doi.org/10.21236/ada457121.
Повний текст джерелаMohammadian, Abolfazl, Ehsan Rahimi, Mohammadjavad Javadinasr, Ali Shamshiripour, Amir Davatgari, Afshin Allahyari, and Talon Brown. Analyzing the Impacts of a Successful Diffusion of Shared E-Scooters and Other Micromobility Devices and Efficient Management Strategies for Successful Operations in Illinois. Illinois Center for Transportation, May 2022. http://dx.doi.org/10.36501/0197-9191/22-006.
Повний текст джерела