Improved design and performance analysis of counterflow thrust vectoring technology under high subsonic

Abstract

With the development of aviation technology and the scramble for air supremacy is becoming increasingly fierce, people put forward higher requirements on the performance of the fighter. The thrust vector nozzle based on flow control has many advantages compared with the traditional mechanical control method, in the thrust vector technology, the thrust loss is low, it can also be applied in subsonic speed. Thrust vector technology has a wider application background. In this paper, the basic principle of counter current thrust vector technology is explained firstly, then the simplified derivation of the formula and the definition of related parameters are derived by the control body analysis. And fluent software is used to simulate the existing experimental model, the obtained numerical results are compared with the experimental data available in the literature, verification proves that the numerical method is feasible. Then change the Maher number of outflow size of vector analysis to effect change. Finally, for thrust vector effect is not obvious under the Maher problem, the design provides a method for vacuum reverse two secondary channel, and its feasibility by using the method of numerical analysis, the vacuum in the two channel is increased, and the thrust vector angle can reach to 18.1 degrees from 1.7 degrees, an increase of about 10 times.

Keywords

Thrust vector vector angle outflow Maher number suction pressure vacuum degree

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References

Chen

, Numerical Studies Counter flow Thrust Vectoring Nozzle Aerodynamic Parameters, Beijing University of Technology, Beijing, 2013.

Yang

J.-J.

and Wang

M.-S.

, Numerical studies of counterflow thrust vectoring nozzle basic flow characteristics, Acta Aeronautica et Astronautica Sinica04 (2008), 769–775.

Liu

Z.-M.

, Chen

, Shen

and Xu

Y.-L.

, Flight Mach Number Affect the performance of counter flow thrust vector nozzle, Propulsion Technology04 (2014), 442–448.

Liu

Z.-M.

, Xu

Y.-L.

and Shen

, Geometry features of counter flow thrust vector nozzle, Journal of Aerospace Power06 (2014), 1417–1425.

Liu

Z.-M.

, Xu

Y.-L.

and Shen

, Subsonic Condition Shape Parameters on the simulation study of the influence of the reflux vectored nozzle Performance, J Propulsion Technology03 (2014), 305–313.

Y.-L.

, Simulation of the influence of the geometric configurations of counter current vectored Nozzle Performance Research, Beijing University of Technology, Beijing, 2013.

X.-Z.

, Long

T.-Y.

and Su

Y.-X.

, Computational Fluid Mechanics, Chongqing: Chongqing University Press, 2007, pp. 63–177.

P.-F.

, Long

T.-Y.

, Su

Y.-X.

and Proficient

Etc.

, In Cfd Simulation And Case Of Actual Combat——Fluent Gambit Icem Cfd Tecplot. People’s posts and telecommunications publishing house, Beijing (in Chinese), 2007, pp. 21–146.

Strykowski

P.J.

, Krothapalli

and Forliti

D.J.

, Counter flow Thrust Vectoring of supersonic jets, AIAA Journal11(34) (1996).

10.

Yang

J.-J.

, Flow control of thrust vector nozzle aerodynamic characteristics research, Nanjing University of Aeronautics and Astronautics, Nanjing, 2007.

11.

Lim

C.M.

, Kim

H.D.

and Setoguchi

, Studies on thrust vector control using a fluidic counter-flow concept, AIAA2006-5204 (2006).

12.

Karen

A.D.

, Bobby

L.B.

, Jeffrey

, et al., A computational study of a new dual throat fluidic thrust vectoring nozzle concept, AIAA 2005-3502 (2005).

13.

Waithe

K.A.

and Deere

K.A.

, Experimental and computational investigation of multiple injection ports in a convergent-divergent nozzle for fluidic thrust vectoring, AIAA2003-3802 (2003).

14.

Reginald

G.W.

, Fluidic thrust vectoring and throat control exhaust nozzle, AIAA (2002), 3010–4060.

15.

Deere

K.A.

, Summary of fluidic thrust vectoring research conducted at NASA langley research center, AIAA Journal (2003), 2075–2800.

16.

Kowal

H.J.

, Advances in thrust vectoring and the application of low-control technology, Canadian Aeronautics and Space Journal (2002), 3025–4110.

17.

Abeyounis

W.K.

, Static internal performance of an over-expanded, fixed geometry, nonaxisymmetric nozzle with fluidic pitch-thrust-vectoring capability, NASATP-3645 (1997).

18.

Deere

K.A.

, PAB3D simulations of a nozzle with fluidic injection for yaw thrust-vector control, AIAA 98-3254 (1998).

19.

Abeyounis

W.K.

, Static internal performance of an over-expanded, fixed geometry, nonaxisymmetric nozzle with fluidic pitch-thrust-vectoring capability, NASATP-3645 (1997).

20.

Deere

K.A.

, Berrier

B.L.

and Flamm

J.D.

, Computational study of fluidic thrust vectoring using separation control in a nozzle, AIAA 2003 -3803 (2003).

21.

Feedback control for counter flow thrust vectoring with a turbine engine: Experiment design and robust control design and implementation, Delfim Zambujo Das Dores (2005), 1570–3550.

22.

Waithe

K.A.

, An experimental and computational investigation of multiple injection ports in aconvergent-divergent nozzle for fluidic thrust vectoring, (2001), 1870–3740.