On the Mechanisms Affecting Fluidic Vectoring Using Suction

Gillgrist, R. D.; Forliti, David; Strykowski, Paul J

doi:10.1115/1.2375125

Cited by 11 publications

(5 citation statements)

References 21 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The lateral force caused by the bi-stable asymmetric forebody vortices at a high angle of attack can be estimated by the circumferential pressure distribution [24]. Regarding FTVC technology, previous studies have indicated that the vectoring angle of FTVC is strongly determined by the near-wall pressure on both sides of the jet [25][26][27]; therefore, it is possible to estimate the thrust vectoring properties through the wall pressure distribution. Normally, a dense array of pressure sensors on the nozzle wall is always required to obtain the pressure distribution on the wall, but this solution is impractical for in-flight applications.…”

Section: Introductionmentioning

confidence: 99%

An Optimized Pressure-Based Method for Thrust Vectoring Angle Estimation

Shi,

Gu,

et al. 2023

Aerospace

View full text Add to dashboard Cite

This research developed a pressure-based thrust vectoring angle estimation method for fluidic thrust vectoring nozzles. This method can accurately estimate the real-time in-flight thrust vectoring angle using only wall pressure information on the inner surface of the nozzle. We proposed an algorithm to calculate the thrust vectoring angle from the wall pressure inside the nozzle. Non-dominated sorting genetic algorithm II was applied to find the optimal sensor arrays and reduce the wall pressure sensor quantity. Synchronous force and wall pressure measurement experiments were carried out to verify the accuracy and real-time response of the pressure-based thrust vectoring angle estimation method. The results showed that accurate estimation of the thrust vectoring angle can be achieved with a minimum of three pressure sensors. The pressure-based thrust vectoring angle estimation method proposed in this study has a good prospect for engineering applications; it is capable of accurate real-time in-flight monitoring of the thrust vectoring angle. This method is important and indispensable for the closed-loop feedback control and aircraft attitude control of fluidic thrust vectoring control technology.

show abstract

Section: Introductionmentioning

confidence: 99%

An Optimized Pressure-Based Method for Thrust Vectoring Angle Estimation

Shi,

Gu,

et al. 2023

Aerospace

View full text Add to dashboard Cite

show abstract

“…In 2015, Gillgrist et al [15] used particle image velocimetry and conventional pressure sensors to obtain the results of the transient velocity field. The Reynolds stress field of the near−wall flow under the stable control state for the reverse flow vectoring nozzle model demonstrated that the lateral pressure gradient generated by the negative suction pressure and the reverse flow shear layer, under the combined action of the induced negative pressure on the wall, is the cause of the jet vector deflection.…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigation on Jet Vector Deflection Jumping Phenomenon of Coanda Effect Nozzle

Chi

2022

Applied Sciences

View full text Add to dashboard Cite

The Coanda effect nozzle is a fluid thrust vectoring technology that uses the Coanda effect to control jet vector deflection. The jumping phenomenon often occurs in the process of controlling jet vector deflection. This phenomenon leads to the nonlinearity of thrust vector control. It destroys the control performance of the aircraft and brings potential dangers to the safety of the aircraft. The jumping phenomenon occurs in an unsteady flow field different from the traditional flow phenomenon. The flow structure in an unsteady flow field changes with time, so it is not easy to control by the traditional active flow control method. This paper explains the reasons for the jumping phenomenon from two aspects: flow field stability and flow structure. Secondly, the unsteady flow field with the jumping phenomenon is studied and analyzed by a flow visualization experiment and dynamic force measurement. Furthermore, the dynamic modal decomposition (DMD) method is used to extract the characteristic frequencies of the critical vortices causing jets to jump in unsteady flow fields. Finally, a pulsed jet with the same characteristic frequency is used to control the varying vortices in the unsteady flow field. The experimental results show that the active flow control method, which extracts the characteristic frequency of the critical flow field structure by DMD, effectively suppresses the jumping phenomenon in the unsteady flow field. It also linearizes the process of jet nonlinear vector deflection.

show abstract

“…Fluidic thrust vectoring control technology will soon become a new direction of thrust vector technology development. 11,12 According to the generation principle of thrust vector, the realization forms of fluid thrust vector control technology can be roughly divided into five basic types: shock vector fluid thrust vector control, Throat Skewing fluid thrust vector control, counter-flow fluid thrust vector control, Co-flow fluid thrust vector control and Coanda effect fluid thrust vector control. 7,8,[12][13][14][15] The shock vector control is to introduce a secondary jet into one side of the nozzle expansion section, and generate oblique shock when the high-speed main stream flows through it, so as to change the direction of the main stream to obtain the required vector angle.…”

Section: Introductionmentioning

confidence: 99%

“…Fluidic thrust vectoring control technology will soon become a new direction of thrust vector technology development. 11 , 12 …”

Section: Introductionmentioning

confidence: 99%

Research on control effectiveness of fluidic thrust vectoring

Xue

Wang

et al. 2021

Science Progress

View full text Add to dashboard Cite

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.

show abstract

On the Mechanisms Affecting Fluidic Vectoring Using Suction

Cited by 11 publications

References 21 publications

An Optimized Pressure-Based Method for Thrust Vectoring Angle Estimation

An Optimized Pressure-Based Method for Thrust Vectoring Angle Estimation

Experimental Investigation on Jet Vector Deflection Jumping Phenomenon of Coanda Effect Nozzle

Research on control effectiveness of fluidic thrust vectoring

Contact Info

Product

Resources

About