Relevant bibliographies by topics / Thrust Vectoring Control (TVC)

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Thrust Vectoring Control (TVC)'

Author: Grafiati
Published: 4 June 2021
Last updated: 16 February 2022

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Journal articles on the topic "Thrust Vectoring Control (TVC)"

1

Invernizzi, Davide, Marco Lovera, and Luca Zaccarian. "Dynamic Attitude Planning for Trajectory Tracking in Thrust-Vectoring UAVs." IEEE Transactions on Automatic Control 65, no. 1 (January 2020): 453–60. http://dx.doi.org/10.1109/tac.2019.2919660.

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Jiméneze, Abel, and Daniel Icaza. "Thrust Vectoring System Control Concept." IFAC Proceedings Volumes 33, no. 6 (May 2000): 235–44. http://dx.doi.org/10.1016/s1474-6670(17)35476-9.

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Forghany, Farzad, Mohammad Taeibe-Rahni, Abdollah Asadollahi-Ghohieh, and Afshin Banazdeh. "Numerical investigation of injection angle effects on shock vector control performance." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 2 (October 31, 2017): 405–17. http://dx.doi.org/10.1177/0954410017733292.

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The present research paper attempted to utilize a computational investigation for optimizing the fluidic injection angle effects on thrust vectoring. Simulation of a convergent divergent nozzle with shock-vector control method was performed, using URANS approach with Spalart–Allmaras turbulence model. The variable fluidic injection angle is investigated at different aerodynamic and geometric conditions. The current investigation demonstrated that injection angle is an essential parameter in fluidic thrust vectoring. Computational results indicate that optimizing injection angle would improve the thrust vectoring performance. Moreover, dynamic response of starting thrust vectoring would decrease by increasing nozzle pressure ratios and secondary to primary total pressure ratios. Also, shifting the location of fluidic injection towards the nozzle throat would have positive effect on response time. Additionally, the results of response time are more sensitive to primary and secondary total pressure ratios of nozzle and fluidic injection location than the fluidic injection angle. Furthermore, increasing fluidic thrust vectoring performance has negative impact on nozzle thrust at different expansion ratios. In addition, to guide the design and development of an efficient propulsion system, the current study attempted to initiate a database of optimum injection angles with different important parameter effects on thrust vectoring and nozzle thrust decline.
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Kuang, MinChi, and JiHong Zhu. "Hover control of a thrust-vectoring aircraft." Science China Information Sciences 58, no. 7 (June 4, 2015): 1–5. http://dx.doi.org/10.1007/s11432-015-5353-3.

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Invernizzi, Davide, and Marco Lovera. "Trajectory tracking control of thrust-vectoring UAVs." Automatica 95 (September 2018): 180–86. http://dx.doi.org/10.1016/j.automatica.2018.05.024.

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Zivkovic, S., M. Milinovic, N. Gligorijevic, and M. Pavic. "Experimental research and numerical simulations of thrust vector control nozzle flow." Aeronautical Journal 120, no. 1229 (May 25, 2016): 1153–74. http://dx.doi.org/10.1017/aer.2016.48.

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ABSTRACTRocket motor nozzle flow geometry is considered through its influence on the thrust vector control (TVC) performances. Extensive research is conducted using theoretical and software simulations and compared with experimental results. Cold and hot flow test equipments are used. The main objective of the research is to establish the methodology of flow geometry optimisation on the TVC hardware system. Several geometry parameters are examined in detail and their effects on the system performances are presented. The discovered effects are used as guidelines in the TVC system design process. A numerical method is presented for the determination of dynamic response time upper limit for the TVC system based on the gas flow dynamics performances.
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Younes, Khaled, and Jean-Pierre Hickey. "Fluidic Thrust Shock-Vectoring Control: A Sensitivity Analysis." AIAA Journal 58, no. 4 (April 2020): 1887–90. http://dx.doi.org/10.2514/1.j058922.

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Gal-Or, Benjamin Z. "Maximizing thrust-vectoring control power and agility metrics." Journal of Aircraft 29, no. 4 (July 1992): 647–51. http://dx.doi.org/10.2514/3.46214.

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Zhang, Chao, Zi Yang Zhen, Dao Bo Wang, and Xin Yu Meng. "Optimal Control for Thrust Vectoring Unmanned Aerial Vehicle." Key Engineering Materials 439-440 (June 2010): 292–97. http://dx.doi.org/10.4028/www.scientific.net/kem.439-440.292.

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In this paper the application of linear quadratic (LQ) optimal control based techniques to a thrust vectoring unmanned aerial vehicle (TV-UAV) control problem is considered. A general nonlinear dynamic model of the TV-UAV is built, which is different from the common UAV. The longitudinal and lateral linearization models are derived in a benchmark flight state. Two thrust deflections are considered as control variables, associated with the rudder control variables. LQ optimal control method based multivariable control system is designed for the attitude stability control problem. Simulations of a nonlinear model described UAV is carried out, results of which show the superiority of the hybrid control strategy, and also show that the TV-UAV has better properties than the common UAV, in the aspects of anti-disturbance and control efficiency.
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Xue, Fei, Gu Yunsong, Yuchao Wang, and Han Qin. "Research on control effectiveness of fluidic thrust vectoring." Science Progress 104, no. 1 (January 2021): 003685042199813. http://dx.doi.org/10.1177/0036850421998137.

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In view of the control effects of fluidic thrust vector technology for low-speed aircraft at high altitude/low density and low altitude/high density are studied. The S-A model of FLUENT software is used to simulate the flow field inside and outside the nozzle with variable control surface parameters, and the relationship between the area of control surface and the deflection effect of main flow at different altitudes is obtained. It is found that the fluidic thrust vectoring nozzle can effectively control the internal flow in the ground state and the high altitude/low density state. and the mainstream deflection angle can be continuously adjusted. The maximum deflection angle of the flow in the ground state is 21.86°, and the maximum deviation angle of the 20 km high altitude/low density state is 18.80°. The deflecting of the inner flow of the nozzle is beneficial to provide more lateral force and lateral torque for the aircraft. The high altitude/low density state is taken as an example. When the internal flow deflects 18.80°, the lateral force is 0.32 times the main thrust. For aircraft with high altitude and low density, sufficient lateral and lateral torque can make the flying aircraft more flexible, which can make up the shortcomings of the conventional rudder failure and even replace the conventional rudder surface.
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Dissertations / Theses on the topic "Thrust Vectoring Control (TVC)"

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Bernacchia, David. "Design of thrust vectoring attitude control system for lunar lander flying testbed." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2020. http://amslaurea.unibo.it/20504/.

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The proposed work has been developed within the project LEAPFROG (Lunar Entry and Approach Platform For Research On Ground) at the University of Southern California. The project concerns the realization of a lunar lander test bed prototype with the aim of testing GNC algorithms for simulated lunar flight and descent. The main focus is the realization of a newly designed thrust vectoring system (TVC) that exploits the thrust given by a main engine in order to control the attitude of the platform. This new attitude control system is combined with current traditional reaction control system (RCS) based on cold-gas thrusters. After a preliminary hardware design phase, a linear LQR controller, based on a reduced quaternion model, and a non-linear sliding mode controller are designed for the TVC system. Linear Quadratic Regulator offers a simple implementation, an optimal control law. However it can be affected by un-modeled dynamics and the solutions provided are, in general, only locally valid. Sliding mode control (SMC) guarantees robustness against disturbances, unmodeled dynamics and uncertainties about the mass properties of the prototype, offering also a global stability. Cons of this method are the hard implementation and the request of an high-frequency actuation. A MATLAB/Simulink simulation is set up in order to validate and compare the designed controllers and to analyze if the thrust vectoring system leads to the desired results.
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Atesoglu, Ozgur Mustafa. "High Angle Of Attack Maneuvering And Stabilization Control Of Aircraft." Phd thesis, METU, 2007. http://etd.lib.metu.edu.tr/upload/12608575/index.pdf.

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In this study, the implementation of modern control techniques, that can be used both for the stable recovery of the aircraft from the undesired high angle of attack flight state (stall) and the agile maneuvering of the aircraft in various air combat or defense missions, are performed. In order to accomplish this task, the thrust vectoring control (TVC) actuation is blended with the conventional aerodynamic controls. The controller design is based on the nonlinear dynamic inversion (NDI) control methodologies and the stability and robustness analyses are done by using robust performance (RP) analysis techniques. The control architecture is designed to serve both for the recovery from the undesired stall condition (the stabilization controller) and to perform desired agile maneuvering (the attitude controller). The detailed modeling of the aircraft dynamics, aerodynamics, engines and thrust vectoring paddles, as well as the flight environment of the aircraft and the on-board sensors is performed. Within the control loop the human pilot model is included and the design of a fly-by-wire controller is also investigated. The performance of the designed stabilization and attitude controllers are simulated using the custom built 6 DoF aircraft flight simulation tool. As for the stabilization controller, a forced deep-stall flight condition is generated and the aircraft is recovered to stable and pilot controllable flight regimes from that undesired flight state. The performance of the attitude controller is investigated under various high angle of attack agile maneuvering conditions. Finally, the performances of the proposed controller schemes are discussed and the conclusions are made.
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Olsson, Adam, and David Jacobsson. "How to Keep an Unbalanced Aircraft Balanced : Control Surfaces and Thrust Vectoring." Thesis, KTH, Skolan för teknikvetenskap (SCI), 2019. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-255832.

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To balance and control different aircraft, it is often necessary to use some type of control system, the less stable the craft is without any control system, the more advanced the system is required to be. This project is an experiment which purpose is to attempt to control a very unstable craft using steerable rudders. A design of the craft is modeled in CAD after a rough estimation to determine the required capacity of the components. Then a simulation of the craft is modeled in Matlab’s Simulink environment, which is used to test the control system’s capabilities and determine its optimal settings. Finally a physical model is built to see if the control system is sufficiently designed to stabilize the vessel under real conditions, which when flown did not successfully balance due to insufficient roll capability. Different solutions to this problem and other potential improvements is then discussed.
För att balansera och styra flygande farkoster måste det ofta användas någon typ av styrsystem, desto mindre stabil farkosten är utan något styrsystem desto mer avancerat system krävs. Detta projekt är ett experiment vars syfte är att försöka kontrollera en mycket instabil farkost med hjälp av styrbara roder. En design av farkosten modelleras i CAD efter en enkel överslagsräkning för att bestämma den nödvändiga kapaciteten av komponenterna. Därefter byggs en virtuell model av farkosten i Matlabs Simulink miljö som används till att testa styrsystemets kapabilitet och bestämma dess optimala inställningar. Slutligen byggs en fysisk modell för att se ifall styrsystemet är tillräckligt bra för att stabilisera farkosten under verkliga förhållanden vilket inte lyckas på grund av otillräcklig spin-kontroll. Olika lösningar på detta problem och andra möjliga förbättringar diskuteras.
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Schaefermeyer, M. Ryan. "Aerodynamic Thrust Vectoring For Attitude Control Of A Vertically Thrusting Jet Engine." DigitalCommons@USU, 2011. https://digitalcommons.usu.edu/etd/1237.

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NASA’s long range vision for space exploration includes human and robotic missions to extraterrestrial bodies including the moon, asteroids and the martian surface. All feasible extraterrestrial landing sites in the solar system are smaller and have gravitational fields of lesser strength than Earth’s gravity field. Thus, a need exists for evaluating autonomous and human-piloted landing techniques in these reduced-gravity situations. A small-scale, free-flying, reduced-gravity simulation vehicle was designed by a group of senior mechanical engineering students with the help of faculty and graduate student advisors at Utah State University during the 2009-2010 academic year. The design reproduces many of the capabilities of NASA’s 1960s era lunar landing research vehicle using small, inexpensive modern digital avionics instead of the large, expensive analog technology available at that time. The final vehicle design consists of an outer maneuvering platform and an inner gravity offset platform. The two platforms are connected through a set of concentric gimbals which allow them to move in tandem through lateral, vertical, and yawing motions, while remaining independent of each other in rolling and pitching motions. A small radio-controlled jet engine was used on the inner platform to offset a fraction of Earth’s gravity (5/6th for lunar simulations), allowing the outer platform to act as though it is flying in a reduced-gravity environment. Imperative to the stability of the vehicle and fidelity of the simulation, the jet engine must remain in a vertical orientation to not contribute to lateral motions. To this end, a thrust vectoring mechanism was designed and built that, together with a suite of sensors and a closed loop control algorithm, enables precise orientation control of the jet engine. Detailed designs for the thrust vectoring mechanisms and control avionics are presented. The thrust vectoring mechanism uses thin airfoils, mounted directly behind the nozzle, to deflect the engine’s exhaust plume. Both pitch and yaw control can be generated. The thrust vectoring airfoil sections were sized using the two-dimensional airfoil section compressible-flow CFD code, XFOIL, developed at the Massachusetts Institute of Technology. Because of the high exhaust temperatures of the nozzle plume, viscous calculations derived from XFOIL were considered to be inaccurate. XFOIL was run in inviscid flow mode and viscosity adjustments were calculated using a Utah State University-developed compressible skin friction code. A series of ground tests were conducted to demonstrate the thrust vectoring system’s ability to control the orientation of the jet engine. Detailed test results are presented.
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Muir, Ewan Andrew McPherson. "The application of robust inverse dynamics estimation to the control of a thrust vectoring fighter aircraft." Thesis, Lancaster University, 1996. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.337552.

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Robertson, Welsh Bradley. "On the influence of nozzle geometries on supersonic curved wall jets." Thesis, University of Manchester, 2017. https://www.research.manchester.ac.uk/portal/en/theses/on-the-influence-of-nozzle-geometries-on-supersonic-curved-wall-jets(bc8817e4-c812-44bc-8dfb-f5d0fdf62a72).html.

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Circulation control involves tangentially blowing air around a rounded trailing edge in order to augment the lift of a wing. The advantages of this technique over conventional mechanical controls are reduced maintenance and lower observability. Despite the technology first being proposed in the 1960s and well-studied since, circulation control is not in widespread use today. This is largely due to the high mass flow requirements. Increasing the jet velocity increases both the efficiency (in terms of mass flow) and effectiveness. However, as the jet velocity exceeds the speed of sound, shock structures form which cause the jet to separate. Recent developments in the field of fluidic thrust vectoring (FTV) have shown that an asymmetrical convergent-divergent nozzle capable of producing an irrotational vortex (IV) has the potential to prevent separation through eliminating stream-wise pressure gradients. In this study, the feasibility of preventing separation at arbitrarily high jet velocities through the use of asymmetrical nozzle geometries designed to maintain irrotational (and stream-wise pressure gradient free) flow is explored. Furthermore, the usefulness of an adaptive nozzle geometry for the purpose of extending circulation control device efficiency and effectiveness is defined. Through a series of experiments, the flow physics of supersonic curved wall jets is characterised across a range of nozzle geometries. IV and equivalent area ratio symmetrical convergent-divergent nozzles are compared across three slot height to radius ratios (H/R): H/R = 0.1, H/R = 0.15, H/R = 0.2. The conclusion of this study is that at low H/R (0.1 and 0.15), there is no significant difference in behaviour between IV and symmetrical nozzles, whilst at high H/R (0.2), the IV nozzles begin separating whilst correctly expanded due to the propagation of pressure upstream from the edge of the reaction surface via the boundary layer. Consequently, it is shown that symmetrical nozzles of equivalent mass flow at high H/R have a higher separation NPR compared to IV nozzles. Specifically, the elimination of favourable, in addition to adverse stream-wise pressure gradients contradicts the expected behaviour of IV nozzles. The separation NPR for nozzles tested in this study, in addition to past studies is subsequently plotted against the throat height to radius ratios (A*/R). This shows that in fact, no previous experiments have shown a higher separation NPR for IV nozzles compared to symmetrical nozzles of equivalent mass flow. The overall outcome is that neither fixed geometry IV, nor adaptive nozzles are justified to maintain attachment, or to improve efficiency. This is because fixed nozzle geometries designed for higher separation NPR do not show any performance deficit when operating at lower NPRs. However, the throat height could be varied to maximise effectiveness (at the expense of mass flow). The contributions to new knowledge made by this study are as follows: the development of a new method of combining shadowgraph and schlieren images to simplify and enhance visualisation of supersonic flows; the use of pressure sensitive paint (PSP) to study the structure of the supersonic curved wall jet before and after separation; the identification of a clear mechanism for the separation of supersonic curved wall jets, valid over a broad range of nozzle geometries (including a clarification of previously unexplained behaviour witnessed in prior studies); the explanation that reattachment hysteresis occurs due to the upstream movement of the point of local separation at full separation (specifically, this explains why certain geometries such as backward-facing steps prevent reattachment hysteresis).
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Saucez, Manuel. "Résolution des qualités de vol de l'aile volante Airbus." Thesis, Toulouse, ISAE, 2013. http://www.theses.fr/2013ESAE0026/document.

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L'objectif de cette étude est de résoudre les qualités de vol d'une aile volante long courrier, au stade de la conception avion. Le concept d'aile volante promet un gain important en terme de performances et de niveau de finesse par rapport aux configurations classiques. Ce gain est obtenu par l'intégration des quatre fonctions principales de l'avion (portance, contrôle, propulsion, transport) dans un seul corps. Ces choix de configuration entraînent des challenges à relever, dont l'obtention de qualités de vol respectant la certification. La configuration initiale étudiée présente de fortes instabilités longitudinales et latérales, une faible autorité en roulis, et des difficultés à effectuer la manœuvre de rotation au décollage. Dans cette étude sont proposées des solutions, combinant des surfaces de contrôle innovantes et des degrés de libertés originaux, qui tirent profit des avantages de la configuration. Les qualités de vols sont résolues dans un processus de résolution avec aussi peu de boucles que possible, et l'impact sur les performances est minimisé. En sortie de ce processus se trouve l'architecture de surface de contrôle optimisée, qui minimise l'impact des qualités de vol sur le coût de la mission
The aim of this study is to solve the handling qualities problems of a long range blended wing body, at the conceptual design phase. That concept, also named flying wing in this report, is an aircraft which integrates the four aircraft functions (lift, control, propulsion, passengers transportation) in one single body. That configuration presents a benefit in cruise lift-over-drag ratio, as well as in noise emissions, due to the shielding effect provided by the inner wing to mask the engine noise.That configuration choice leads also to challenges. One of them is the handling qualities. The baseline studied flying wing presents initially longitudinal and lateral instabilities, as well as lack of roll manoeuvrability and difficulty to do the rotation at takeoff. In this report are proposed solutions, combining innovative control surfaces and original drivers, which are adapted to the configuration advantages. The handling qualitiesare solved in a resolution process with as few loops as possible, and the impact on the performances is minimized. The output of that process is the best control surfaces architecture and airfoils design which minimizes the impact of the handling qualities resolution on the cost of the mission
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Dulke, Michael F., David Salinas, and Matthew D. Kelleher. "Heat transfer modeling of jet vane Thrust Vector Control (TVC)--Systems." Thesis, 1987. http://hdl.handle.net/10945/22822.

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Dores, Delfim Zambujo das Collins Emmanuel G. Alvi Farruk S. "Feedback control for counterflow thrust vectoring with a turbine engine experiment design and robust control design and implementation /." Diss., 2005. http://etd.lib.fsu.edu/theses/available/etd-04082005-130006.

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Thesis (Ph. D.)--Florida State University, 2005.
Advisors: Dr. Emmanuel G. Collins Jr., and Dr. Farruk S. Alvi, FAMU-FSU College of Engineering, Dept. of Mechanical Engineering. Title and description from dissertation home page (viewed June 15, 2005). Document formatted into pages; contains xvii, 185 pages. Includes bibliographical references.
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Books on the topic "Thrust Vectoring Control (TVC)"

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Nunn, R. H. TVC jet vane thermal modeling using parametric system identification. Monterey, Calif: Naval Postgraduate School, 1988.

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Asbury, Scott C. Effects of internal yaw-vectoring devices on the static performance of a pitch-vectoring nonaxisymmetric convergent-divergent nozzle. Hampton, Va: Langley Research Center, 1993.

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Lallman, Frederick J. Preliminary design study of a lateral-directional control system using thrust vectoring. [s.l.]: National Aeronautics and Space Administration Scientific and Technical Information Branch, 1985.

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Mason, Mary L. A static investigation of the thrust vectoring system of the F/A-18 high-alpha research vehicle. Hampton, Va: Langley Research Center, 1992.

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Nelms, R. M. Design of power electronics for TVC & EMA systems: Final report. [Washington, DC: National Aeronautics and Space Administration, 1994.

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Capone, Francis J. Multiaxis control power from thrust vectoring for a supersonic fighter aircraft model at Mach 0.20 to 2.47. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Office, 1987.

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Imlay, Scott T. Implicit time-marching solution of the Navier-Stokes equations for thrust reversing and thrust vectoring nozzle flows. Hampton, Va: Langley Research Center, 1986.

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Wing, David J. Static investigation of a multiaxis thrust-vectoring nozzle with variable internal contouring ability. Washington, D.C: National Aeronautics and Space Administration, 1997.

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Foley, Robert J. Static thrust-vectoring performance of nonaxisymmetric convergent-divergent nozzles with post-exit yaw vanes. Hampton, Va: Langley Research Center, 1991.

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Asbury, Scott C. Multiaxis thrust-vectoring characteristics of a model representative of the F-18 High-Alpha Research Vehicle at angles of attack from 0 deg to 70 deg. Hampton, Va: Langley Research Center, 1995.

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Book chapters on the topic "Thrust Vectoring Control (TVC)"

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Adams, Richard J., James M. Buffington, Andrew G. Sparks, and Siva S. Banda. "Thrust Vectoring F-18 Design." In Advances in Industrial Control, 101–60. London: Springer London, 1994. http://dx.doi.org/10.1007/978-1-4471-2111-4_5.

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Miwa, Masafumi, Yuki Shigematsu, and Takashi Yamashita. "Control of Ducted Fan Flying Object Using Thrust Vectoring." In Intelligent Systems, Control and Automation: Science and Engineering, 97–107. Tokyo: Springer Japan, 2013. http://dx.doi.org/10.1007/978-4-431-54276-6_7.

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Conference papers on the topic "Thrust Vectoring Control (TVC)"

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Snow, Barton H. "Thrust Vectoring Control Concepts and Issues." In Aerospace Technology Conference and Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1990. http://dx.doi.org/10.4271/901848.

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Collins, E. G., Y. Zhao, F. Alvi, M. I. Alidu, and P. J. Strykowski. "Feedback control for counterflow thrust vectoring." In Proceedings of the 2004 American Control Conference. IEEE, 2004. http://dx.doi.org/10.23919/acc.2004.1384479.

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Garrison, Michael, Scott Steffan, Steve Tollefson, and Mark Reinecke. "Thrust Vector Control (TVC) System Architecture Trade Study Overview." In 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2007. http://dx.doi.org/10.2514/6.2007-5848.

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CORNELIUS, KENNETH, and GERALD LUCIUS. "Thrust vectoring control from underexpanded asymmetric nozzles." In 3rd Shear Flow Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-3261.

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Mason, Mark, and William Crowther. "Fluidic Thrust Vectoring for Low Observable Air Vehicles." In 2nd AIAA Flow Control Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-2210.

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CHAWLA, KALPANA, and W. VAN DALSEM. "Numerical simulation of STOL operations using thrust-vectoring." In Guidance, Navigation and Control Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-4254.

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Williams, Reginald, and Baily Vittal. "Fluidic Thrust Vectoring and Throat Control Exhaust Nozzle." In 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2002. http://dx.doi.org/10.2514/6.2002-4060.

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Jiang, B. W., C. H. Kuo, K. J. Peng, K. C. Peng, S. H. Hsiung, and C. M. Kuo. "Thrust Vectoring Control for Infrastructure Inspection Multirotor Vehicle." In 2019 IEEE 6th International Conference on Industrial Engineering and Applications (ICIEA). IEEE, 2019. http://dx.doi.org/10.1109/iea.2019.8714892.

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WHITE, JOHN. "Attitude control of a spinning rocket via thrust vectoring." In Navigation and Control Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-2617.

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Yong, Kenan, Hui Ye, Mou Chen, and Qingxian Wu. "Transformation model of thrust-vectoring using RBF neural network." In 2014 33rd Chinese Control Conference (CCC). IEEE, 2014. http://dx.doi.org/10.1109/chicc.2014.6895788.

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Reports on the topic "Thrust Vectoring Control (TVC)"

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Collins Jr, Emmanuel G. Feedback Control Design for Counterflow Thrust Vectoring. Fort Belvoir, VA: Defense Technical Information Center, September 2005. http://dx.doi.org/10.21236/ada438337.

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