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

Author: Grafiati

Published: 4 June 2021

Last updated: 16 February 2022

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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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2

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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3

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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4

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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5

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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6

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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7

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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8

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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9

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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10

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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11

Lee, MyungYeon, and Yeol Lee. "Thrust Vectoring Control of Supersonic Jet Using Proportional Control Valves." Journal of the Korean Society for Aeronautical & Space Sciences 47, no. 1 (January 31, 2019): 1–8. http://dx.doi.org/10.5139/jksas.2019.47.1.1.

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12

Vinayagam, A. K., and N. K. Sinha. "Optimal aircraft take-off with thrust vectoring." Aeronautical Journal 117, no. 1197 (November 2013): 1119–38. http://dx.doi.org/10.1017/s0001924000008733.

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Abstract The short take-off capability is of paramount importance for a fighter airplane to enable its operation from short and damaged runways. This paper analyses the airplane take-off process from the viewpoint of reducing the ground roll/take-off distance with the use of thrust vectoring. The airplane take-off is modelled incorporating the ground reactions on the landing gear and the thrust vector forces and moments. The take-off problem is formulated as an optimal control problem with appropriate constraints. Though many researchers have applied optimal control techniques for designing airplane manoeuvres, its application to the airplane take-off problem is rarely available in the open literature. It is expedient to use such methodology to understand the use of thrust vectoring features of an aircraft to maximise the benefits in shortening the ground roll/take-off distance. An optimal control methodology has been applied in this paper with the objectives stated above to a twin-engine fighter nonlinear aircraft model popularly known as F-18/HARV. Computation of flight path and control schedules using optimal control has been carried out with and without the use of vector nozzles. A reduction of about 6% in take-off distance and about 29% in ground roll distance is obtained with the use of thrust vector for the configuration studied.

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13

Xu, Xia, Lu Xiong, and Yuan Feng. "Torque Vectoring Control for Handling Improvement of 4WD EV." Advanced Materials Research 765-767 (September 2013): 1893–98. http://dx.doi.org/10.4028/www.scientific.net/amr.765-767.1893.

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Exploiting the structural merit that electric motors can be controlled precisely in speed und torque, this paper investigates the use of Torque Vectoring Control (TVC) for improving handling of electric vehicles. The strategy consists of two control levels. The upper level controller layer achieves reference yaw rate tracking, by using the 2-DOF planar bicycle model with a linear tire model to calculate the desired yaw rate. Then with sliding mode control law the desired yaw moment is determined. The lower control level determines control inputs for four driving motors by means of optimum traction distribution. Simulations are carried out by using the co-simulation of vehicle dynamics software CarSim and Simulink to verify the effectiveness of this control system and the effects of parameter variations (friction coefficient and throttle).

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14

Yagle, P. J., D. N. Miller, K. B. Ginn, and J. W. Hamstra. "Demonstration of Fluidic Throat Skewing for Thrust Vectoring in Structurally Fixed Nozzles." Journal of Engineering for Gas Turbines and Power 123, no. 3 (January 1, 2001): 502–7. http://dx.doi.org/10.1115/1.1361109.

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The experimental demonstration of a fluidic, multiaxis thrust vectoring (MATV) scheme is presented for a structurally fixed, afterburning nozzle referred to as the conformal fluidic nozzle (CFN). This concept for jet flow control features symmetric injection around the nozzle throat to provide throttling for jet area control, and asymmetric injection to subsonically skew the sonic plane for jet vectoring. The conceptual development of the CFN was presented in a companion paper (Miller et al. [1]). In that study, critical design variables were shown to be the flap length and expansion area ratio of the nozzle, and the location, angle, and distribution of injected flow. Measures of merit were vectoring capability, gross thrust coefficient, and discharge coefficient. A demonstration of MATV was conducted on a 20 percent scale CFN test article across a range of nozzle pressure ratios (NPR), injector flow rates, and flow distributions. Both yaw and pitch vector angles of greater than 8 deg were obtained at NPR of 5.5. Yaw vector angles greater than 10 deg were achieved at lower NPR. Values of thrust coefficient for the CFN generally exceeded published measurements of shock-based vectoring methods. In terms of vectoring effectiveness (ratio of vector angle to percent injected flow), fluidic throat skewing was found to be comparable to shock-based vectoring methods.

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15

Islam, Md Shafiqul, Md Arafat Hasan, and A. B. M. Toufique Hasan. "Numerical Analysis of Bypass Mass Injection on Thrust Vectoring of Supersonic Nozzle." MATEC Web of Conferences 179 (2018): 03014. http://dx.doi.org/10.1051/matecconf/201817903014.

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High speed aerospace applications require rapid control of thrust (i.e. thrust vectoring) in order to achieve better manoeuvrability. Among the existing technologies, shock vector control is one of the efficient ways to achieve thrust vectoring. In the present study, bypass mass injection (passive control) was used to generate shock vectoring in a planar supersonic Converging-Diverging (CD) nozzle. Two diffenrent bypass lines were used to inject mass in the diverging section varying their dimension in the span wise direction (10 mm ×10 mm2 square channel and 2.68 mm×38 mm2 rectangular channel) in such a way that, the mass flow ratio in both the case remain the same (4.9%) in order to compare the effect of bypass channel dimension in the resulting thrust vector angle and thrust performance. Reynolds-averaged Navier-Stokes (RANS) equations with k-omega SST turbulence model have been implemented through numerical computations to capture the three-dimensional steady characterstics of the flow field. Results showed a significant change in the shock structure with the fromation of recirculation zone near the bypass injection port in both the case with a variation of shock structure and thrust performance for different geometry bypass lines. It was found that, thrust vector angle increases as injection length increases in the span wise direction.

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16

Lee, MyungYeon, MyungJun Song, DaBin Kim, and Yeol Lee. "Bidirectional Thrust Vectoring Control of a Rectangular Sonic Jet." AIAA Journal 56, no. 6 (June 2018): 2494–98. http://dx.doi.org/10.2514/1.j056598.

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17

MIWA, Masafumi, Yuki SHIGEMATSU, and Takashi YAMASHITA. "Control of Ducted Fan Flying Object Using Thrust Vectoring." Journal of System Design and Dynamics 6, no. 3 (2012): 322–34. http://dx.doi.org/10.1299/jsdd.6.322.

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18

Liu, Tao, Yuli Hu, Hui Xu, and Mohamed El Ghami. "Investigation of an Underwater Vectored Thruster Based on 3RPS Parallel Manipulator." Mathematical Problems in Engineering 2020 (September 29, 2020): 1–18. http://dx.doi.org/10.1155/2020/9287241.

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Autonomous underwater vehicles (AUVs) are important and useful tool platforms in exploring and utilizing ocean resource. However, the effect of control surfaces would decrease even invalid complete in this condition, and it is very hard for conventional AUVs to perform detailed missions at a low forward speed. Therefore, solving this problem of AUVs becomes particularly important to increase the application scope of AUVs. In this paper, we present a design scheme for the vectored thruster AUV based on 3RPS parallel manipulator, which is a kind of parallel manipulator and has advantages of compact structure and reliable performance. To study the performance and characteristics of the proposed thrust-vectoring mechanism, a series of works about corresponding kinematic and dynamic analysis have been performed through the theoretical analysis and numerical simulation. In the part of kinematics, the inverse, forward kinematics, and workspace analysis of the thrust-vectoring mechanism is presented, and the numerical simulations are accomplished to prove the feasibility and effectiveness of this design in AUVs. In order to further verify feasibility of the thrust-vectoring mechanism, based on the considerations of various affecting factors, a dynamic model of the designed thrust-vectoring mechanism is established according to theoretical analysis, and the driving forces of the linear actuator are presented through a series of numerical simulations. In addition, a control scheme based on PID algorithm is proposed for the designed vectored thruster with considering various affecting factors and the application environment. Meanwhile, the control scheme is also established and verified in MATLAB Simscape Mutibody. A series of numerical simulations of the thrust-vectoring mechanism prove the feasibility of the vectored thruster. According to equipping the designed vectored thruster, the AUVs can overcome the limit of weakening the control ability at zero or low forward speeds, and this improvement also expands the application of it, which has been scaled greatly.

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19

Gan, Yi He, Lu Xiong, Yuan Feng, and Felix Martinez. "A Torque Vectoring Control System for Maneuverability Improvement of 4WD EV." Applied Mechanics and Materials 347-350 (August 2013): 899–903. http://dx.doi.org/10.4028/www.scientific.net/amm.347-350.899.

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This paper studies the improvement of the handling performance of 4WD EV driven by in-wheel motors under regular driving conditions. Fundamentally the structure of torque vectoring control (TVC) system for handling control consists of two control layers. The upper layer is a model following controller which makes the vehicle follow the desired yaw rate limited by the side slip angle and lateral acceleration. The torque distribution constitutes the lower layer. Several simulations based on veDYNA/Simulink are conducted to verify the effectiveness of the control system. It is clarified that the control system exhibits satisfactory performance in both open and closed loop maneuvers and the agility of the electric vehicle is improved.

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20

Wu, Kexin, Guang Zhang, Tae Ho Kim, and Heuy Dong Kim. "Numerical parametric study on three-dimensional rectangular counter-flow thrust vectoring control." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 234, no. 16 (May 22, 2020): 2221–47. http://dx.doi.org/10.1177/0954410020925602.

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Recently, fluidic thrust vectoring control is popular for micro space launcher propulsion systems due to its several advantages, such as fast dynamic responsiveness, better control effectiveness, and no moving mechanical equipment. Counter-flow thrust vectoring control is an especially effective technique by utilizing less suction flow to control the mainstream deflection flexibly. In the current work, theoretical and numerical analyses are performed together to elaborate on the performance of the three-dimensional rectangular counter-flow thrust vectoring control system. A new propulsion nozzle of Mach 2.5 is devised by method of characteristics. To testify the feasibility and accuracy of the present research methodology, numerical results were validated against experimental data from the open literature. The computational result using the standard k-epsilon turbulence model reveals a good match with experimentally measured static pressure values along the centerline of the upper suction collar. The influence of several key parameters on vectoring performance is investigated herein, including the mainstream temperature, collar radius, horizontal collar length, and gap height. Critical parameters have been quantitatively analyzed, such as static pressure distribution along the centerline of the upper suction collar, pitching angle, suction mass flow ratio, and thrust coefficient. Furthermore, the flow-field features are qualitatively expounded based on the static pressure contour, streamline, iso-turbulent kinetic energy contour, and iso-Mach number contour. Some important conclusions are offered for further studies. The mainstream temperature mainly affects different dynamic characteristics of the mixing shear layer, including the convective Mach number of the shear layer, density ratio, and flow velocity ratio. The collar radius influences the pressure gradient near the suction collar surface significantly. The pitching angle increases rapidly with the increasing collar radius. As the horizontal collar length increases, the systematic deflection angle initially increases then decreases. The highest pitching angle is obtained for L/ H = 3.53. With regard to the gap height, a larger gap height can achieve a higher pitching angle.

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21

Cornelius, Kenneth C., and Gerald A. Lucius. "Thrust vectoring control from convergent nozzles with translating side wall." Journal of Propulsion and Power 11, no. 3 (May 1995): 427–32. http://dx.doi.org/10.2514/3.23861.

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22

Zhao, Yanan, Emmanuel G. Collins, Farrukh Alvi, and Delfim Dores. "Design and Implementation of Feedback Control for Counterflow Thrust Vectoring." Journal of Propulsion and Power 21, no. 5 (September 2005): 815–21. http://dx.doi.org/10.2514/1.12882.

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23

SHIGEMATSU, Yuki, Takashi YAMASHITA, Yasuyuki ISHIHARA, and Masafumi MIWA. "911 Control of ducted fan flying object using thrust vectoring." Proceedings of Conference of Chugoku-Shikoku Branch 2012.50 (2012): 91101–2. http://dx.doi.org/10.1299/jsmecs.2012.50.91101.

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24

CHATANI, Naoki, Shinji UEMURA, and Masafumi MIWA. "817 Translating control of ducted fan helicopter using thrust vectoring." Proceedings of Conference of Chugoku-Shikoku Branch 2016.54 (2016): _817–1_—_817–2_. http://dx.doi.org/10.1299/jsmecs.2016.54._817-1_.

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25

SHIGEMATSU, Yuki, Takashi YAMASHITA, and Masafumi MIWA. "A311 Control of ducted fan flying object using thrust vectoring." Proceedings of the Symposium on the Motion and Vibration Control 2011.12 (2011): 487–90. http://dx.doi.org/10.1299/jsmemovic.2011.12.487.

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26

Muir, E., and A. Bradshaw. "Control Law Design for a Thrust Vectoring Fighter Aircraft Using Robust Inverse Dynamics Estimation (RIDE)." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 210, no. 4 (October 1996): 333–43. http://dx.doi.org/10.1243/pime_proc_1996_210_378_02.

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Control laws have been designed for a high performance fighter aircraft using robust inverse dynamics estimation (RIDE) with the aim of providing good control at high angles of attack. This necessitates the use of thrust vectoring in flight conditions where aerodynamic control surfaces become ineffective. It is shown that the RIDE controller is able to transfer smoothly from using the aerodynamic surfaces to thrust vectoring during post-stall manoeuvring. The RIDE controller is structured so as to estimate the inverse dynamics of the aircraft and gives the designer freedom to assign the dynamics of the controlled states. Simulation results demonstrate that RIDE provides a simple method for the design of control laws which give specified response characteristics across the flight envelope and are robust to plant variations.

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27

Alvi, F. S., P. J. Strykowski, A. Krothapalli, and D. J. Forliti. "Vectoring Thrust in Multiaxes Using Confined Shear Layers." Journal of Fluids Engineering 122, no. 1 (December 7, 1999): 3–13. http://dx.doi.org/10.1115/1.483220.

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A fluidic scheme is described which exploits a confined countercurrent shear layer to achieve multiaxis thrust vector response of supersonic jets in the absence of moving parts. Proportional and continuous control of jet deflection is demonstrated at Mach numbers up to 2, for pitch vectoring in rectangular nozzles and multiaxis vectoring in axisymmetric nozzles. Secondary mass flow rates less than approximately 2% of the primary flow are used to achieve thrust vector angles exceeding 15 degrees. Jet slew rates up to 180 degrees per second are shown, and the fluidic scheme is examined in both static and wind-on configurations. Thrust performance is studied for external coflow velocities between Mach 0.3 and 0.7. [S0098-2202(00)02601-8]

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28

Li, Li, Dong Ping Wang, and Tsutomu Saito. "Effect of Control Parameters of Secondary Jet on Fluidic Thrust Vectoring." Advanced Materials Research 998-999 (July 2014): 613–16. http://dx.doi.org/10.4028/www.scientific.net/amr.998-999.613.

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The flow field was simulated in a 2D convergent-divergent nozzle, for fluidic thrust vectoring with N-S method. Based on the specific design, the effects of control parameters of secondary jet injection is investigated, and a method is proposed to calculate the initial state of secondary jet, which is different from original hypothesis of stagnation. The results showed that the two methods have closed results and the stagnation hypothesis is suitable for the calculation of the initial state of secondary jet.

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29

Toivanen, Petri K., and Pekka Janhunen. "Spin Plane Control and Thrust Vectoring of Electric Solar Wind Sail." Journal of Propulsion and Power 29, no. 1 (January 2013): 178–85. http://dx.doi.org/10.2514/1.b34330.

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30

Miwa, Masafumi, and Shinya Maruhashi. "Attitude control of Pusher Configuration VTOL aircraft with thrust vectoring nozzle." Proceedings of JSME annual Conference on Robotics and Mechatronics (Robomec) 2016 (2016): 1P1–17b6. http://dx.doi.org/10.1299/jsmermd.2016.1p1-17b6.

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31

Kowal, H. J. "ADVANCES IN THRUST VECTORING AND THE APPLICATION OF FLOW-CONTROL TECHNOLOGY." Canadian Aeronautics and Space Journal 48, no. 2 (June 2002): 145–51. http://dx.doi.org/10.5589/q02-020.

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32

Shigematsu, Yuuki, Hidefumi Ojima, Takashi Yamashita, and Masafumi Miwa. "310 Control of ducted fan flying obj ect using thrust vectoring." Proceedings of Conference of Chugoku-Shikoku Branch 2011.49 (2011): 87–88. http://dx.doi.org/10.1299/jsmecs.2011.49.87.

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33

Shin, Choon Sik, Heuy Dong Kim, Toshiaki Setoguchi, and Shigeru Matsuo. "A computational study of thrust vectoring control using dual throat nozzle." Journal of Thermal Science 19, no. 6 (December 2010): 486–90. http://dx.doi.org/10.1007/s11630-010-0413-x.

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34

Buffington, James M., Andrew G. Sparks, and Siva S. Banda. "Robust longitudinal axis flight control for an aircraft with thrust vectoring." Automatica 30, no. 10 (October 1994): 1527–40. http://dx.doi.org/10.1016/0005-1098(94)90093-0.

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35

Imamura, Akitaka, Masafumi Miwa, and Junichi Hino. "Flight Characteristics of Quad Rotor Helicopter with Thrust Vectoring Equipment." Journal of Robotics and Mechatronics 28, no. 3 (June 17, 2016): 334–42. http://dx.doi.org/10.20965/jrm.2016.p0334.

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[abstFig src='/00280003/09.jpg' width=""300"" text='Thrust vectoring mechanisms for WRH' ] A quad rotor helicopter (QRH) is a radio controlled (RC) aircraft that tilts its attitude to generate a horizontal force component to move in a certain direction. Using autonomous control, the attitude control system tilts the airframe against disturbances, such as wind. Thus, the attitude of a flying QRH is always slanted. In this study, three types of deflecting thruster were compared to maintain the position and horizontal attitude of the QRH. The extra thrusters are tilted to generate a thrust against disturbances without causing the airframe to incline. It is suitable for precise measurements for which the airframe posture should remain horizontal.

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36

Whalley, R., and M. Ebrahimi. "Missile captive firing, modelling and control." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 212, no. 1 (January 1, 1998): 31–43. http://dx.doi.org/10.1243/0954410981532117.

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The pitch plane manoeuvring characteristics of a solid propellant missile under captive firing conditions are considered. Analysis techniques are used to establish the dynamic model of the suspended, lumped parameter representation of the vehicle, which is regulated directionally by thrust vectoring. Three-term feedback control is employed to confine the response of the system to both demanded input changes and external load disturbances from airstream turbulence and defensive projectile debris strikes. Simulated manoeuvring characteristics are computed for demonstration purposes.

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37

Biggs, James D., and Gaetano Livornese. "Control of a Thrust-Vectoring CubeSat Using a Single Variable-Speed Control Moment Gyroscope." Journal of Guidance, Control, and Dynamics 43, no. 10 (October 2020): 1865–80. http://dx.doi.org/10.2514/1.g005181.

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38

Atesoglu, Özgür, and M. Kemal Özgören. "Control and Robustness Analysis for a High-Infinity Maneuverable Thrust-Vectoring Aircraft." Journal of Guidance, Control, and Dynamics 32, no. 5 (September 2009): 1483–96. http://dx.doi.org/10.2514/1.42989.

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39

MARUBASHI, Shinya, and Masafumi MIWA. "803 Attitude control of inverted pendulum type airframe by thrust vectoring nozzle." Proceedings of Conference of Chugoku-Shikoku Branch 2015.53 (2015): _803–1_—_803–2_. http://dx.doi.org/10.1299/jsmecs.2015.53._803-1_.

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40

WANG, QingYun, Tian LIU, GuoZheng QIN, and HaoLiang WANG. "Tracking control for a hypersonic air-breathing vehicle with thrust vectoring nozzles." SCIENTIA SINICA Physica, Mechanica & Astronomica 43, no. 4 (April 1, 2013): 415–23. http://dx.doi.org/10.1360/132012-724.

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41

Papachristos, Christos, Kostas Alexis, and Anthony Tzes. "Dual–Authority Thrust–Vectoring of a Tri–TiltRotor employing Model Predictive Control." Journal of Intelligent & Robotic Systems 81, no. 3-4 (May 12, 2015): 471–504. http://dx.doi.org/10.1007/s10846-015-0231-1.

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42

Shneider, Mikhail N., and Sergey O. Macheret. "Hypersonic Aerodynamic Control and Thrust Vectoring by Nonequilibrium Cold-Air Magnetohydrodynamic Devices." Journal of Propulsion and Power 22, no. 3 (May 2006): 490–97. http://dx.doi.org/10.2514/1.16960.

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43

LIM, DAVID W., and LARRY G. REDEKOPP. "Aerodynamic flow-vectoring of a planar jet in a co-flowing stream." Journal of Fluid Mechanics 450 (January 9, 2002): 343–75. http://dx.doi.org/10.1017/s0022112001006462.

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The vectoring of an incompressible, two-dimensional jet in a co-flowing stream is investigated by means of direct numerical simulation. The control input used to stimulate jet vectoring is accomplished through distributed suction from blunt-faced lips at the exit of the jet. The thrust vector methodology is based on suppression of global instabilities in the wake-shear layers formed between the co-flow and the jet. Once a critical suction volume flux needed to suppress these global instabilities is exceeded, local flow control can be realized through varying the distribution of suction across the base of the jet lips. It is found that the critical suction flux scales primarily with the ambient co-flow, not with the jet speed, and that lift-to-thrust ratios exceeding 15% can be realized. The effects of jet Reynolds number, jet-to- ambient velocity ratio, boundary-layer thickness, and geometric parameters on various performance characteristics are examined. It is also shown that the asymmetric flow control approach used for vectoring the jet can also be implemented in a symmetric configuration to enhance jet spreading. Significant increases in jet spreading can be realized when the symmetrically applied suction flux is sufficient to stimulate the sinuous mode of instability of the jet such that energetic apping motion ensues.

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Nieto-Wire, Clara, and Kenneth Sobel. "Flight Control Design for a Tailless Aircraft Using Eigenstructure Assignment." International Journal of Aerospace Engineering 2011 (2011): 1–13. http://dx.doi.org/10.1155/2011/549131.

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We apply eigenstructure assignment to the design of a flight control system for a wind tunnel model of a tailless aircraft. The aircraft, known as the innovative control effectors (ICEs) aircraft, has unconventional control surfaces plus pitch and yaw thrust vectoring. We linearize the aircraft in straight and level flight at an altitude of 15,000 feet and Mach number 0.4. Then, we separately design flight control systems for the longitudinal and lateral dynamics. We use a control allocation scheme with weights so that the lateral pseudoinputs are yaw and roll moment, and the longitudinal pseudoinput is pitching moment. In contrast to previous eigenstructure assignment designs for the ICE aircraft, we consider the phugoid mode, thrust vectoring, and stability margins. We show how to simultaneously stabilize the phugoid mode, satisfy MIL-F-8785C mode specifications, and satisfy MIL-F-9490D phase and gain margin specifications. We also use a cstar command system that is preferable to earlier pitch-rate command systems. Finally, we present simulation results of the combined longitudinal/lateral flight control system using a full 6DOF nonlinear simulation with approximately 20,000 values for the aerodynamic coefficients. Our simulation includes limiters on actuator deflections, deflection rates, and control system integrators.

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Gu, D.-W., K. Natesan, and I. Postlethwaite. "Modelling and robust control of fluidic thrust vectoring and circulation control for unmanned air vehicles." Proceedings of the Institution of Mechanical Engineers, Part I: Journal of Systems and Control Engineering 222, no. 5 (August 2008): 333–45. http://dx.doi.org/10.1243/09596518jsce485.

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Wu, Kexin, and Heuy Dong Kim. "Numerical study on the shock vector control in a rectangular supersonic nozzle." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 13 (March 8, 2019): 4943–65. http://dx.doi.org/10.1177/0954410019834133.

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In recent decades, the fluidic thrust vector control technique is one of the core strategies to redirect various aerospace vehicles, such as modern launch rockets, supersonic aircraft, and guided missiles. The fundamental theory of the shock vector control is that the gas is injected into the supersonic part of a conventional convergent–divergent nozzle from the transverse to cause interactions between the shock waves and boundary layers. Then, the deflection of the primary jet can be easily realized by the induced oblique shock waves. It was evident that the shock vector control is a very simple, low weight, low cost, and quick vectoring response technique to gain high thrust vectoring performance. In the present work, computational fluid dynamics studies were performed at different control parameters in a three-dimensional rectangular supersonic nozzle with the slot injector. For the validation of the numerical methodology, computational results were compared with experimental data referred to the NASA Langley Research Center. The static pressure distributions along the upper and lower nozzle surfaces in the symmetry plane were matched with the test data excellently. Numerical simulations were based on the well-assessed shear stress transport k–ω turbulence model. Second-order accuracy was selected to reveal more details of the flow-field as much as possible. Lots of factors were investigated, such as the momentum flux ratio, length-to-width ratio, injection location, and injection angle. The performance variations for different affecting factors were illustrated and some constructive conclusions were obtained to provide the reference for further investigations in fluidic thrust vector control field.

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Silva, João Paulo, Christophe De Wagter, and Guido de Croon. "Quadrotor Thrust Vectoring Control with Time and Jerk Optimal Trajectory Planning in Constant Wind Fields." Unmanned Systems 06, no. 01 (January 2018): 15–37. http://dx.doi.org/10.1142/s2301385018500024.

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This paper proposes a trajectory planning and control strategy to optimally visit a given set of waypoints in the presence of wind. First, aerodynamic properties of quadrotors which affect trajectory planning and tracking performance are investigated. Blade flapping, induced and parasitic drag are derived and an extended method to identify all coefficients from flight test data is developed. Then, a three-step approach is suggested to optimize the trajectory. These steps reduce the size of the optimization problem and thereby increase computational efficiency while still guaranteeing near optimal results. The trajectories are optimized for minimal aerodynamic drag and minimal jerk. The derived smooth trajectory generation is compared with traditional trajectory planning consisting of discrete point to point tracking followed by low-pass filtering. The new trajectories yield a clear reduction in maximal needed thrust and in Euler angle aggressiveness. A thrust vectoring controller is designed, which exploits the a priori trajectory information and identified aerodynamic properties. Its performance is compared to a standard PID controller and results show a reduction in tracking delay and an increase in thrust and attitude angle margins, which overall enable faster flight.

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Tsubakino, Daisuke, and Shunsuke Saito. "Nonlinear control of a pusher-configured small tail-sitter UAV with thrust vectoring." Proceedings of Conference of Tokai Branch 2020.69 (2020): 412. http://dx.doi.org/10.1299/jsmetokai.2020.69.412.

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MARUBASHI, Shinya, and Masafumi MIWA. "815 Attitude control of Tail-sitter type VTOL aircraft with thrust vectoring nozzle." Proceedings of Conference of Chugoku-Shikoku Branch 2016.54 (2016): _815–1_—_815–2_. http://dx.doi.org/10.1299/jsmecs.2016.54._815-1_.

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Wu, Linfeng, Huanyu Li, Yingjie Li, and Chunwen Li. "Position Tracking Control of Tailsitter VTOL UAV With Bounded Thrust-Vectoring Propulsion System." IEEE Access 7 (2019): 137054–64. http://dx.doi.org/10.1109/access.2019.2942526.

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