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Journal articles on the topic 'Thrust vector'

Author: Grafiati

Published: 4 June 2021

Last updated: 1 February 2022

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1

Kanyshev, Alexey V., Oleg N. Korsun, and Alexander V. Stulovskii. "Methods of Computing Thrust Vector Coordinates for Aircrafts Equipped With Thrust Vector Control." ITM Web of Conferences 10 (2017): 01004. http://dx.doi.org/10.1051/itmconf/20171001004.

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2

Xu, Fei, Yan Xia, Shiyi He, Wenlei Xiao, Xiaoping Ouyang, and Guoqing Liu. "Structural Design and Performance Analysis of α Particle Micro-thruster." MATEC Web of Conferences 288 (2019): 01004. http://dx.doi.org/10.1051/matecconf/201928801004.

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The α particle propelling is a technology under developing by the author’s research group, which uses α decay isotopes emitting high-speed particles to generate thrust. In this paper we mainly designed the thrust magnitude control and vector control structure suitable for this propelling principle and preliminarily analyzed its control performance. The proposed structure mounts the trust film composed of the decay nuclides onto a quasi-spherical frame surface that is conducive to vector synthesis. The traveling wave type ultrasonic motor drives the diaphragm to control the thrust magnitude of each thrust unit independently and efficiently. The vector control of the joint thrust is implemented by taking advantage of the diversity of combination of multiple thrust units. Theoretical calculation and analysis showed that the thruster structure could achieve the thrust magnitude control accuracy of 0.05µN, and the thrust angle control accuracy of 0.5-1.5 degrees.

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3

Bugrova, A. I., G. E. Bugrov, A. M. Bishaev, A. V. Desyatskov, M. V. Kozintseva, A. S. Lipatov, V. K. Kharchevnikov, and P. G. Smirnov. "Experimental investigation of thrust-vector deviation in a plasma thruster." Technical Physics Letters 40, no. 2 (February 2014): 161–63. http://dx.doi.org/10.1134/s1063785014020199.

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4

Orr, Jeb S., and Nathan J. Slegers. "High-Efficiency Thrust Vector Control Allocation." Journal of Guidance, Control, and Dynamics 37, no. 2 (March 2014): 374–82. http://dx.doi.org/10.2514/1.61644.

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5

Lilley, Jay S., and Jerrold H. Arszman. "Scarfed nozzles for thrust-vector adjustment." Journal of Propulsion and Power 7, no. 3 (May 1991): 382–88. http://dx.doi.org/10.2514/3.23338.

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6

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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7

Palmisano, John S., Jason D. Geder, Ravi Ramamurti, William C. Sandberg, and Banahalli Ratna. "Robotic Pectoral Fin Thrust Vectoring Using Weighted Gait Combinations." Applied Bionics and Biomechanics 9, no. 3 (2012): 333–45. http://dx.doi.org/10.1155/2012/802985.

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A method was devised to vector propulsion of a robotic pectoral fin by means of actively controlling fin surface curvature. Separate flapping fin gaits were designed to maximize thrust for each of three different thrust vectors: forward, reverse, and lift. By using weighted combinations of these three pre-determined main gaits, new intermediate hybrid gaits for any desired propulsion vector can be created with smooth transitioning between these gaits. This weighted gait combination (WGC) method is applicable to other difficult-to-model actuators. Both 3D unsteady computational fluid dynamics (CFD) and experimental results are presented.

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8

Wu, Kexin, and Heuy Dong Kim. "Study on Fluidic Thrust Vector Control Based on Dual-Throat Concept." Journal of the Korean Society of Propulsion Engineers 23, no. 1 (February 1, 2019): 24–32. http://dx.doi.org/10.6108/kspe.2019.23.1.024.

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9

Friddell, J. H., and M. E. Franke. "Confined jet thrust vector control nozzle studies." Journal of Propulsion and Power 8, no. 6 (November 1992): 1239–44. http://dx.doi.org/10.2514/3.11468.

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10

Hokenson, Gustave J. "Thrust vector control utilizing asymmetric jet nozzles." Journal of Spacecraft and Rockets 23, no. 6 (November 1986): 655–56. http://dx.doi.org/10.2514/3.25860.

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11

Sakata, Masashi, and Yuichi Maruyama. "Performance Analyses of Fluidic Thrust Vector Control." Proceedings of Conference of Chugoku-Shikoku Branch 2018.56 (2018): 712. http://dx.doi.org/10.1299/jsmecs.2018.56.712.

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12

Nguyen, Tam Willy, Mehdi Hosseinzadeh, and Emanuele Garone. "Thrust vector control of constrained multibody systems." Automatica 129 (July 2021): 109586. http://dx.doi.org/10.1016/j.automatica.2021.109586.

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13

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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14

Wassom, Steven R., Lawrence C. Faupell, and Tim Perley. "Integrated aerofin/thrust vector control for tactical missiles." Journal of Propulsion and Power 7, no. 3 (May 1991): 374–81. http://dx.doi.org/10.2514/3.23337.

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15

Lilley, Jay S. "Reduced-length scarfed-nozzles for thrust vector adjustment." Journal of Propulsion and Power 9, no. 2 (March 1993): 233–39. http://dx.doi.org/10.2514/3.23614.

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16

Francis, Michael S. "Air Vehicle Management with Integrated Thrust-Vector Control." AIAA Journal 56, no. 12 (December 2018): 4741–51. http://dx.doi.org/10.2514/1.j056768.

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17

Wu, Kexin, and Heuy Dong Kim. "Fluidic Thrust Vector Control Using Shock Wave Concept." Journal of the Korean Society of Propulsion Engineers 23, no. 4 (August 1, 2019): 10–20. http://dx.doi.org/10.6108/kspe.2019.23.4.010.

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18

Wu, Kexin, Yingzi Jin, and Heuy Dong Kim. "Hysteretic Behaviors in Counter-Flow Thrust Vector Control." Journal of Aerospace Engineering 32, no. 4 (July 2019): 04019041. http://dx.doi.org/10.1061/(asce)as.1943-5525.0001027.

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19

Xue, Fei, Huaqiang Wang, and Yuchao Wang. "Exploration and study of fluid thrust vector nozzle." Journal of Physics: Conference Series 1300 (August 2019): 012033. http://dx.doi.org/10.1088/1742-6596/1300/1/012033.

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20

TAKAHASHI, Yoichiro, and Yuchi MARUYANA. "Performance Analysis of Fluidic Thrust Vector Control System." Proceedings of Mechanical Engineering Congress, Japan 2020 (2020): J19115. http://dx.doi.org/10.1299/jsmemecj.2020.j19115.

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21

Takahashi, Yoichiro, and Yuichi Maruyama. "Performance Analysis of Fluidic Thrust Vector Control System." Proceedings of Conference of Chugoku-Shikoku Branch 2021.59 (2021): 07b2. http://dx.doi.org/10.1299/jsmecs.2021.59.07b2.

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22

Wu, Kexin, Heuy Dong Kim, and Yingzi Jin. "Fluidic thrust vector control based on counter-flow concept." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 4 (January 14, 2018): 1412–22. http://dx.doi.org/10.1177/0954410017752580.

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Computational studies are conducted on the supersonic nozzle to investigate the possibility of utilizing counter-flow in fluidic thrust vector control. In this work, the design Mach number of the symmetric supersonic nozzle is set to be 2.5. For the validation of methodology, numerical results are compared with experimental data referred from the literature. Two-dimensional numerical simulations are based on well-assessed standard k–ɛ turbulence model with standard wall functions. Second-order accuracy is ensured to reveal more details of flow field. The system thrust ratio, deflection angle, and secondary mass flow ratio were studied for a wide range of nozzle pressure ratios and secondary pressure ratios. The results indicate that deflection angle and secondary mass flow ratio are found to be decreased with increasing nozzle pressure ratio as well as system thrust ratio. The secondary mass flow ratio and deflection angle decrease with the increase of secondary pressure ratio, and system thrust ratio increases with the increasing of secondary pressure ratio. The secondary mass flow rate remains under 2.4% of the primary flow to obtain efficient thrust vector control at high Mach number.

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23

Fani Saberi, Farhad, Mansour Kabganian, Hamed Kouhi, and Morteza Shahravi. "Gimbaled-thruster based nonlinear attitude control of a small spacecraft during thrusting manoeuvre." Aeronautical Journal 121, no. 1241 (June 13, 2017): 983–1004. http://dx.doi.org/10.1017/aer.2017.51.

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ABSTRACTIn this paper, a novel thrusting manoeuvre control scheme is proposed for a small spacecraft which is based only on the gimbaled thrust vector control (TVC) system. The spacecraft structure is composed of a body and a gimbaled thruster where common attitude control systems such as reaction control system (RCS) and spin stabilisation are not employed. A nonlinear two-body model is considered for the characterisation of the gimbaled-nozzle spacecraft where the gimbal actuator provides the only active control input. The spacecraft attitude is affected by a large exogenous disturbance torque which is generated by a thrust vector misalignment from the centre of mass (CM). To achieve some performance goals in the both transient and steady-state modes, a new control scheme is derived based on the combination of two linear and nonlinear controllers. The proposed method ensures the attitude and thrust vector stability during an impulsive orbital manoeuvre while eliminating and rejecting an exogenous disturbance torque. The numerical simulations illustrate the applicability of this method for using in a small spacecraft and its efficiency in sustained operation.

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24

Wang, Bo, Yu Ge An, Man Zhang, and Yuan Zheng. "Numerical Simulation of Thrust Vector Control for a 2D Nozzle." Applied Mechanics and Materials 494-495 (February 2014): 420–23. http://dx.doi.org/10.4028/www.scientific.net/amm.494-495.420.

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In modern campaign, Aircraft maneuverability and agility have been playing an increasingly important role. Plasma thrust vector control can avoid shortcomings of traditional methods, it has a very good prospect.In present work a CFD simulation of a thrust vector control for a 2D nozzle is performed.The results showed that the change of the magnetic field can impress the vector turn of the nozzle flowfield.

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25

Kato, Masayuki, Katsuhiro Hirata, Tomoaki Mototsuji, and Akira Heya. "Edge effect of multi-degree-of-freedom oscillatory actuator driven by vector control." Open Physics 18, no. 1 (July 27, 2020): 346–51. http://dx.doi.org/10.1515/phys-2020-0169.

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AbstractThis article proposes a thrust equation model of two-degree-of-freedom oscillatory actuator considering its edge effect. The proposed thrust equation model clarifies that asymmetric permanent magnet flux linkage and inductance characteristics cause undesirable magnetic thrust and reluctance thrust, respectively.

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26

Wang, Zhaohui, Yinghong Jia, Lei Jin, and Jiajia Duan. "Thrust vector control of upper stage with a gimbaled thruster during orbit transfer." Acta Astronautica 127 (October 2016): 359–66. http://dx.doi.org/10.1016/j.actaastro.2016.06.002.

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27

Qiang, Zhi, and Cai Yuan-li. "Energy-Management Steering Maneuver for Thrust Vector-Controlled Interceptors." Journal of Guidance, Control, and Dynamics 35, no. 6 (November 2012): 1798–804. http://dx.doi.org/10.2514/1.56611.

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28

Gutman, Shaul, and Sergey Rubinsky. "Exoatmospheric Thrust Vector Interception Via Time-to-Go Analysis." Journal of Guidance, Control, and Dynamics 39, no. 1 (January 2016): 86–97. http://dx.doi.org/10.2514/1.g001268.

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29

KIMURA, Ichiro, Kazuya OSAMURA, and Toshi TAKAMORI. "A Thrust Vector Control Jet Nozzle for Submersible Vehicles." Transactions of the Society of Instrument and Control Engineers 24, no. 6 (1988): 603–7. http://dx.doi.org/10.9746/sicetr1965.24.603.

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30

Sahinkaya, Yilmaz E., and Sherry A. Cordova. "An Intelligent Controller Architecture for Missile Thrust Vector Control." IFAC Proceedings Volumes 27, no. 13 (September 1994): 333–38. http://dx.doi.org/10.1016/s1474-6670(17)45822-8.

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31

Navarro-Tapia, Diego, Andrés Marcos, and Samir Bennani. "Envelope Extension via Adaptive Augmented Thrust Vector Control System." Journal of Guidance, Control, and Dynamics 44, no. 5 (May 2021): 1044–52. http://dx.doi.org/10.2514/1.g005436.

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32

Busurin, V. I., and P. V. Mulin. "Optimization of the trimming tilting angle of the electric tiltrotor propeller group." Civil Aviation High Technologies 24, no. 4 (August 27, 2021): 50–60. http://dx.doi.org/10.26467/2079-0619-2021-24-4-50-60.

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The paper examined the possibility of improving the energy efficient performance of an electric tiltrotor with a lift-propulsion propeller group for a steady flight mode by reducing the energy consumption of the propeller group per unit of time or per unit of the path traveled by the electric tiltrotor. This is achieved by selecting the optimal tilting angles of the electric tiltrotor total thrust vector. In the proposed approach, the trimming tilting angle of the propeller group is variable, depending on the aerodynamic characteristics of the electric tiltrotor, its propeller group. Since the propeller group is equipped with the drives for tilting them, this approach is easily implemented by the conventional facilities of the electric tiltrotor. The tilting of the total thrust vector, on the one hand, leads to an increase in the effective value of the aerodynamic lift coefficient and, on the other hand, it is accompanied by a decrease in the projection of the total thrust vector on the flight speed vector, a change in the drag and power required to create the thrust of the propeller group. This circumstance makes it necessary to solve the optimization problem in order to increase the maximum endurance and long-range capabilities in the cruise mode of the electric tiltrotor flight. The paper presents a method for calculating the optimal tilting angles of the total thrust vector based on the equations of steady motion of the electric tiltrotor in the cruise flight mode, the expression for the total power required for the rotation of the propellers of the propeller group. The analytical dependences for the optimal tilting angles of the total thrust vector are obtained depending on the ratio of the wing area to the total propeller-disk area of the propeller group and the aerodynamic quality of the electric tiltrotor.

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33

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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34

Tokareva, Olena Leonidivna, Natalia Serhiivna Priadko, and Ternova Vitaliivna Ternova. "An operation algorithm for the combined thrust vector control system of a rocket engine." System technologies 4, no. 123 (October 12, 2019): 58–66. http://dx.doi.org/10.34185/1562-9945-4-123-2019-06.

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The new combined rocket engine (RE) control system consists of combining various control systems - mechanical thrust vector control system (MTVCS) and gas-dynamic one (GDTVCS) within one bifunctional system that performs the functions of controlling and stabilizing the rocket stage flight. Previously it was shown that the MTVCS speed has limit, since with its speed increase the sensitivity to high-frequency random disturbances rises, which increases random errors. In addition, the system performance rise leads to an increase in the mass and dimensions of the steering drive of the engine swing. As part of the combined system, GDTVCS supplies any given speed requirements, and MTVCS provides maximum control efforts with minimum drive power and maximum element simplicity of the thrust vector control system as a whole. However, there is a problem of rational function distribution between subsystems and coordination of their functioning. For automatic control of the RE thrust vector, the input data are angle deviations in a certain plane, which characterize the direction violations of the installation.The purpose of the work is to study the input signal characteristics of the thrust vector system of steering engines applied to the combined RE control system and the design of an optimal algorithm for its operation.There were analyzed possible determining methods for the trend existence of the input signal on the characteristic RE operation intervals and method was proposed for selected trend using. This made it possible to develop an algorithm for the functioning of the combined (mechanical and gas-dynamic) thrust vector control system of the rocket engine. The created algorithm provides the processing of the TVCS input signal with the selection of the deterministic (static) component (trend) and high-frequency signal oscillations (deviations from the trend). The trend type of the deviation angle perturbation of the RE thrust vector is also taken into account. The typical dependence of the output control actions for the steering RE on the input signals at different operation time intervals is investigated.The developed algorithm allows optimal separating (in terms of energy consumption for creating control efforts) the subsystem functions of the combined RE thrust vector control system, to improve the quality and reliability of the flight control system of the rocket stage.

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35

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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36

Wu, Kexin, and HeuyDong Kim. "A fluidic thrust vector control using the bypass flow in a dual throat nozzle." Journal of Mechanical Science and Technology 35, no. 8 (July 22, 2021): 3435–43. http://dx.doi.org/10.1007/s12206-021-0716-8.

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37

Fitzpatrick, David, Giuseppe Cimadoro, and Daniel Cleather. "The Magical Horizontal Force Muscle? A Preliminary Study Examining the “Force-Vector” Theory." Sports 7, no. 2 (January 22, 2019): 30. http://dx.doi.org/10.3390/sports7020030.

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The force-vector theory contends that horizontal exercises are more specific to horizontal sports skills. In this context, the focus is on horizontal force production relative to the global coordinate frame. However, according to the principle of dynamic correspondence, the direction of force relative to the athlete is more important, and thus the basis for the force-vector theory is flawed. The purpose of this study was therefore to test the force-vector theory. According to the force-vector theory, hip thrust is a horizontally loaded exercise, and so hip thrust training would be expected to create greater improvements in horizontal jump performance than vertical jump performance. Eleven collegiate female athletes aged 18–24 years completed a 14-week hip thrust training programme. Pre and post testing was used to measure the following: vertical squat jump, vertical countermovement jump, horizontal squat jump, horizontal countermovement jump and hip thrust 3 repetition maximum (3RM). Subjects improved their 3 repetition maximum hip thrust performance by 33.0% (d = 1.399, p < 0.001, η2 = 0.784) and their vertical and horizontal jump performance (improvements ranged from 5.4–7.7%; d = 0.371–0.477, p = 0.004, η2 = 0.585). However, there were no differences in the magnitude of the improvement between horizontal and vertical jumping (p = 0.561, η2 = 0.035). The results of this study are contrary to the predictions of the force-vector theory. Furthermore, this paper concludes with an analysis of the force-vector theory, presenting the mechanical inconsistencies in the theory. Coaches should use the well established principle of dynamic correspondence in order to assess the mechanical similarity of exercises to sports skills.

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38

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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39

Sun, Liang, Guowei Zhao, Hai Huang, and Ming Chen. "Optimal Control Scheme of the Tethered System for Orbital Transfer under a Constant Thrust." International Journal of Aerospace Engineering 2018 (2018): 1–12. http://dx.doi.org/10.1155/2018/1572726.

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The tethered system with a long tether has its unique advantages in space environment exploration. With the development of requirement, the orbital transfer of the tethered system under a constant thrust and its related optimal control become significant and challenging. Three different optimal control schemes of the tethered system are proposed, including the tension control, the thrust vector control, and the mixed control. In the tension control, in order to ensure the smoothness of pendular motion of the tethered system, different cost functions are adopted and compared. In the thrust vector control, the constraint of thrust direction angle is fully considered. In the mixed control, equivalent conditions to other control schemes are investigated. The advantages and disadvantages of three optimal control schemes are compared and analyzed, which provides a reference for research on the optimal control problem of the tethered system under a constant thrust.

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40

Rizvi, Farheen, and Raquel M. Weitl. "Characterizing Limit Cycles in the Cassini Thrust Vector Control System." Journal of Guidance, Control, and Dynamics 36, no. 5 (September 2013): 1490–500. http://dx.doi.org/10.2514/1.57295.

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41

Schoyer, H. F. R. "Thrust Vector Control for (Clustered Modules) Plug Nozzles: Some Considerations." Journal of Propulsion and Power 16, no. 2 (March 2000): 196–201. http://dx.doi.org/10.2514/2.5583.

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42

Schinstock, Dale E., Douglas A. Scott, and Tim A. Haskew. "Transient Force Reduction in Electromechanical Actuators for Thrust-Vector Control." Journal of Propulsion and Power 17, no. 1 (January 2001): 65–72. http://dx.doi.org/10.2514/2.5708.

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43

Liu, Junjie, Zengqiang Chen, Mingwei Sun, and Qinglin Sun. "Practical Coupling Rejection Control for Herbst Maneuver with Thrust Vector." Journal of Aircraft 56, no. 4 (July 2019): 1726–34. http://dx.doi.org/10.2514/1.c035338.

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44

Sung, Hong-Gye, and Jun-Young Heo. "Fluidic Thrust Vector Control of Supersonic Jet Using Coflow Injection." Journal of Propulsion and Power 28, no. 4 (July 2012): 858–61. http://dx.doi.org/10.2514/1.b34266.

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45

Wekerle, Timo, Euler Gonçalves Barbosa, César Moura Batagini, Luís E. V. Loures da Costa, and Luís Gonzaga Trabasso. "Closed-loop actuator identification for Brazilian Thrust Vector Control development." IFAC-PapersOnLine 49, no. 17 (2016): 468–73. http://dx.doi.org/10.1016/j.ifacol.2016.09.080.

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SHAKOUCHI, Toshihiko, Tsubasa TANOUE, Koichi TSUJIMOTO, and Toshitake ANDO. "Thrust Vector Control of Transonic and Supersonic Under-Expanded Jets." Proceedings of Mechanical Engineering Congress, Japan 2018 (2018): S0510303. http://dx.doi.org/10.1299/jsmemecj.2018.s0510303.

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Wie, Bong. "Thrust vector control design for a liquid upper stage spacecraft." Journal of Guidance, Control, and Dynamics 8, no. 5 (September 1985): 566–72. http://dx.doi.org/10.2514/3.20023.

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Porzio, A. J., and M. E. Franke. "Experimental study of a confined jet thrust vector control nozzle." Journal of Propulsion and Power 5, no. 5 (September 1989): 596–601. http://dx.doi.org/10.2514/3.23195.

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Lowe, James D. "Comment on "Thrust Vector Control of a V/STOL Airship"." Journal of Aircraft 22, no. 4 (April 1985): 348. http://dx.doi.org/10.2514/3.56751.

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Chandra Murthy, M. S. R., and Debasis Chakraborty. "Numerical Characterisation of Jet-Vane based Thrust Vector Control Systems." Defence Science Journal 65, no. 4 (July 20, 2015): 261. http://dx.doi.org/10.14429/dsj.65.7960.

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Abstract:

<p>Computational fluid dynamics methodology was used in characterising jet vane based thrust vector control systems of tactical missiles. Three-dimensional Reynolds Averaged Navier-Stokes equations were solved along with two-equation turbulence model for different operating conditions. Nonlinear regression analysis was applied to the detailed CFD database to evolve a mathematical model for the thrust vector control system. The developed model was validated with series of ground based 6-Component static tests. The proven methodology is applied toa new configuration.</p><p><strong>Defence Science Journal, Vol. 65, No. 4, July 2015, pp. 261-264, DOI: http://dx.doi.org/10.14429/dsj.65.7960</strong></p>

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