Vectored Propulsion, Supermaneuverability and Robot Aircraft

Gal‐Or, Benjamin

doi:10.1007/978-1-4613-8961-3

Cited by 39 publications

(20 citation statements)

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“…It has been gradually used in recent years to obtain advance supermaneuverability in 4.5 and 5th generation aircraft, such as the F-22 Raptor, the Russian Sukhoi PAK FA (T-50), and the Su-30 [1], Decades of research on mechanical thrust vectoring techniques was initiated in the 1970s to meet the demand for fighter aircraft Contributed by the Turbomachinery Committee of ASME for publication in the Journal of E ngineering for G as T urbines and Power. Manuscript with increasing agility.…”

Section: Introductionmentioning

confidence: 99%

Experimental and Numerical Investigations of a Bypass Dual Throat Nozzle

Guo

2014

Journal of Engineering for Gas Turbines and Power

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The bypass dual throat nozzle (BDTN) is a new kind o f fluidic vec toring nozzle. A bypass is set between the upstream convergent section and upstream minimum area based on the conventional dual throat nozzle (DTN). The BDTN shows a minimum or even no penalty on the nozzle's thrust performance, while it would be able to produce steady and efficient vectoring deflection similar to the conventional DTN. A BDTN model has been designed and sub jected to experimental and computational study. The main results show that: (1) BDTN does not consume any secondary injection from the other part of the engine, while it can produce steady and efficient vectoring deflection. (2) Under the same condition, it can provide the maximum thrust vectoring efficiency o f all the known fluidic thrust vectoring concepts reported in the literature. (3) The thrust vector angle is also greater than that of the conventional DTN that has been reported up to now. Especially, under NPR = 10, the thrust vector angle o f BDTN can reach 21.3 deg. (4) For a wide NPR range from 2 to 10, the BDTN generates the best thrust vectoring performance under NPR =4. Above all, the BDTN is well suited to produce vectored thrust for nozzles.

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Section: Introductionmentioning

confidence: 99%

Experimental and Numerical Investigations of a Bypass Dual Throat Nozzle

Guo

2014

Journal of Engineering for Gas Turbines and Power

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“…With these controls established, Eqs. (2)(3)(4)(5)(6)(7)(8)(9)(10)(11) are applied to calculate the algorithmic prediction performance.…”

Section: Data Theory Comparisonmentioning

confidence: 99%

“…[3][4][5][6]. Assuming that the exit-area deviation from orthogonality with the divergent nozzle centerline is negligible, the effective expansion length is approximated as…”

Section: ) Is Writtenmentioning

confidence: 99%

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Geometric Evaluation of Axisymmetric Thrust-Vectoring Nozzles for Aerodynamic Performance Predictions

Wilson

Adler

Bar‐Yoseph

2002

Journal of Propulsion and Power

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Nomenclature A = area, m 2 A j e =A j t = nozzle area control ratio @ j D E , G CD = ow coef cient at the nozzle throat M = Mach r = radius, m V c = effective nozzle expansion volume, m 3 W = gas ow rate, kg/s x = nozzle expansion length, m x n = length of divergent nozzle aps, m; x G = cos ® @ ± Gy;z D 0 ® = nozzle divergence angle, rad = nozzle convergence angle, rad ± = nozzle jet de ection angle, rad » = one-dimensionalradial elongation of r E t Subscripts c = control constant E = effective e = exit G = geometric i = variable (yaw or pitch) t = throat x = body-axis direction y = yaw direction z = pitch direction 7 = nozzle entrance station number 8 = nozzle throat station number ? = normal to A G t Superscript j = variable (effective or geometric)

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“…Thrust vectoring has established increasing applications in recent decade. Several thrust vector control concepts have been extensively investigated utilizing computational and experimental methods in the past (Páscoa et al, 2013;Saghafi et al, 2007;Gal-Or, 1990). …”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation of Optimization of Injection Angle Effects on Fluidic Thrust Vectoring

Forghany

Taeibi-Rahni

Ghohieh

2017

JAFM

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A computational investigation was conducted to optimize the fluidic injection angle effects on thrust vectoring. Numerical simulation of fluidic injection for shock vector control, with a convergent-divergent nozzle concept was performed, using URANS approach with Spalart-Allmaras turbulence model. The fluidic injection angles from 60º to 120º were investigated at different aerodynamic and geometric conditions. The current investigation demonstrated that secondary injection angle is an essential parameter in fluidic thrust vectoring. Computational results indicated that, optimizing secondary injection angle would have positive impact on thrust vectoring performance. Furthermore, in most cases, decreasing expansion ratio of the nozzle with increasing NPR has negative impact on pitch thrust vector angle and thrust vectoring efficiency. That is, the highest pitch thrust vector angle is obtained by decreasing nozzle expansion ratio with increasing SPR in smaller fluidic injection angles. In addition, the current investigation attempted to initiate a database of optimized injection angles with different essential parameter effects on thrust vectoring, in order to guide the design and development of an efficient propulsion system.

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Vectored Propulsion, Supermaneuverability and Robot Aircraft

Cited by 39 publications

References 0 publications

Experimental and Numerical Investigations of a Bypass Dual Throat Nozzle

Experimental and Numerical Investigations of a Bypass Dual Throat Nozzle

Geometric Evaluation of Axisymmetric Thrust-Vectoring Nozzles for Aerodynamic Performance Predictions

Numerical Investigation of Optimization of Injection Angle Effects on Fluidic Thrust Vectoring

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