Summary of Fluidic Thrust Vectoring Research at NASA Langley Research Center

Deere, Karen A.

doi:10.2514/6.2003-3800

Cited by 111 publications

(71 citation statements)

References 10 publications

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“…Configuration of the test device 추력성능을 7~12% 정도, 또한 운용비용을 37~53% 정도 개선할 수 있음이 보고된 바 있으며 [1], 이차유동의 이용에 따른 노즐의 냉각성능 및 응답속도의 개선을 추가로 기대할 수 있다 [2,3].…”

unclassified

Development of the High-Accuracy Multi-Component Balance for Fluidic Thrust Vectoring Nozzle of UAV

Song¹,

Chang²,

Cho³

et al. 2013

Journal of the Korean Society for Aeronautical & Space Scie

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The thrust vector control technique is essential for high maneuverability of unmanned aerial vehicles. In the present study, a multi-component balance was developed to quantitatively evaluate the thrust-vectoring performance of a supersonic rectangular nozzle based on the Coanda coflowing effect. Precise calibration and detailed data analysis were performed during the development. It was found that the cross-talk errors between load cells in the balance were less than 5%, and that the unwanted errors due to high-pressure supply tubes were almost negligible, which contributed to the high accuracy of the present balance design. Some preliminary test results of the thrust-vectoring performance of the present nozzle design were also obtained and analyzed.

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Development of the High-Accuracy Multi-Component Balance for Fluidic Thrust Vectoring Nozzle of UAV

Song¹,

Chang²,

Cho³

et al. 2013

Journal of the Korean Society for Aeronautical & Space Scie

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“…For instance, actual multi-axis thrust-vectoring technology based on movable nozzles allows unconventional maneuvers such as the "helicopter J-turn backflip" or the acrobatic "hammerhead" safely, even if the aircraft is in stalled conditions for the main part of the maneuver. Thrust vectoring helps vehicles meet takeoff and landing requirements, and it can be a valuable control effector at low dynamic pressures, where traditional aerodynamic controls are less effective [4][5][6][7]. Advantages are also expected for supersonic aircraft, where the use of thrustvectoring nozzles with a canard airframe configuration can allow for lower sonic-boom signatures than possible with conventional configurations [6].…”

mentioning

confidence: 99%

“…The counterflow method uses suction between the trailing edge of the nozzle and an aft collar. The suction creates a reversed flow along the collar, which causes a pressure drop and an increase in velocity near the reversed flow area, thus providing a thrust differential [4]. As a drawback, an additional equipment to provide the suction is required.…”

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confidence: 99%

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Numerical Investigation of the Dynamic Characteristics of a Dual-Throat-Nozzle for Fluidic Thrust-Vectoring

Ferlauto

Marsilio

2017

AIAA Journal

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A computational method tailored for the simulation of fluidic thrust-vectoring systems is employed to investigate the dynamic response of a dual-throat nozzle in open-and closed-loop control. Thrust vectoring in fixed, symmetric nozzles is obtained by secondary flow injections that cause local flow separations, asymmetric pressure distributions, and, as a consequence, the vectoring of primary jet flow. The computational technique is based on a well-assessed mathematical model for the compressible unsteady Reynolds-averaged Navier-Stokes equations. A minimal control system governs the unsteady blowing. Nozzle performances and thrust-vector angles have been computed for a wide range of nozzle pressure ratios and secondary flow injection rates. The numerical results are compared with the experimental data available in the open literature. Several computations of the open-loop dynamics of the nozzle under different forcing have been performed to investigate the system response in terms of thrust-vectoring effectiveness and controllability. These computations have been used to extract autoregressive exogenous models of the nozzle dynamics. The effects of including the actuator dynamics are also discussed. Simple strategies of closed-loop control of the nozzle system by proportional-integrative-derivative regulators are investigated numerically. The closed-loop model predictive control of the system, based on the autoregressive exogenous models, is addressed.

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“…It also provides an enhanced stealth characteristics due to simple tail design [6]. Moreover, Fluidic vectoring techniques offer up to 80% nozzle weight reduction and 50% less maintenance costs in comparison with mechanical control schemes [9]. FTV system depends on the phenomena identified as the Coanda effect.…”

Section: Introductionmentioning

confidence: 99%

Experimental Study of Jet Vectoring by using Counter Flow at Subsonic Speed in Circular Jet

Al-Asady¹,

Faseeh²

2017

IJCA

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An experimental investigation of fluidic jet vectoring using counter-flow method had been carried out in this current work. The experimental investigation included a set of experiments to examine the various effects of geometric variables on the thrust vectoring angle. These included Coanda surface radius R/d = (0.58823, 1.17647, 1.75471), secondary gap height h/d = (0.02941, 0.05882), and secondary mass flow ratio range of (0 ≤ S / p ≤ 0. 07882). In addition, the test rig was built to display the ability of counter-flow method to vector the primary flow in pitch and yaw axes. Load cell readings were obtained using two components overhead balance. The results show proportional increase in vectoring angle value with the increase of the secondary suction rate. Three zones can be observed: a "dead zone" region at low mass flow ratios, followed by a control region where continuous primary jet control is achievable until a saturation region is reached. Small Coanda surface ratio resulted in an extended dead zone. The secondary gap height increase had an inverse effect on the thrust vectoring angle. A Smoke visualization was carried out to augment the experimental work and to demonstrate primary flow vectoring in pitch, and yaw axes. The investigation shows that the experimental gave a good agreement compared with previous studies on jet vectoring angle.

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Summary of Fluidic Thrust Vectoring Research at NASA Langley Research Center

Cited by 111 publications

References 10 publications

Development of the High-Accuracy Multi-Component Balance for Fluidic Thrust Vectoring Nozzle of UAV

Development of the High-Accuracy Multi-Component Balance for Fluidic Thrust Vectoring Nozzle of UAV

Numerical Investigation of the Dynamic Characteristics of a Dual-Throat-Nozzle for Fluidic Thrust-Vectoring

Experimental Study of Jet Vectoring by using Counter Flow at Subsonic Speed in Circular Jet

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