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The Mechanism Study of Thrust Vectoring Using Synthetic Jet Actuator

Author: WangDeQuan
Tutor: XiaZhiXun
School: National University of Defense Science and Technology
Course: Aeronautical and Astronautical Science and Technology
Keywords: Synthetic jet technology Synthetic jet actuators Thrust vector control Numerical Simulation Vector
CLC: V433
Type: Master's thesis
Year: 2004
Downloads: 153
Quote: 3
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Abstract


In this paper, theoretical analysis, the combined method of numerical simulation and experimental study of synthetic jet flow mechanism and thrust vector control. One of the innovations of this paper is to band inclination synthetic jet actuators with the adjacent actuators used in low-speed the mainstream thrust vector control, compared to conventional actuators the adjacent actuators with inclination incentive to get good thrust vector control effect. This paper research specifically reflected in the following aspects: (1) one of the main tasks of this paper is to compare the different actuator simplified model, two-dimensional numerical analysis of the the synthesis flow field of synthetic jet with the mainstream in order to explore the synthetic jet with the mainstream The mechanism of interaction. By analysis of the following conclusions: 1 in the \pull to the side of the actuator, the speed is also slowly decline; the mainstream channels medial pressure difference arises primarily in the upper and lower wall between the actuator mainstream outlet. The ② push mode synthetic jet penetration, respectively, with the the film vibration velocity amplitude mainstream speed ratio is proportional to the number with 斯托罗哈尔 inversely proportional. ③ \and best value is influenced by other parameters can be regularly changed. (2) formed by the interaction of different retardation, different amplitudes, different frequencies of the two adjacent actuator with mainstream synthetic flow field numerical analysis and to study the mechanism. The study found that mainstream by the adjacent actuator influence phase difference there is an optimal value, the actuator phase advance close to mainstream; frequency than amplitude than the impact on the mainstream is very complex, as the frequency ratio increases mainstream maximum deflection angle of a non-linear change. (3) made a numerical analysis of the synthetic jet with inclination incentive mainstream. Actuator angle there is an optimal value, and the inclination of the best values ??of the structural parameters and excitation parameters impact. Case without increasing the exciter input power, with the inclination of the actuator can be greatly increased mainstream deflection angle, a good effect of the thrust vector control. (4) Based on the design of the synthetic jet actuators and testing system, in the stationary atmospheric environment principle experiment, the outlet shape of the actuator, the excitation voltage waveform, the state of compression of the vibrating membrane assembly, the quantity of the vibrating membrane, and the different excitation Dimensions and other factors on the impact of the synthetic jet and the analysis of the experimental results with theoretical analysis and numerical simulation results coincide.

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CLC: > Aviation, aerospace > Aerospace ( Astronauts ) > Propulsion system ( engine, propeller ) > Engine control systems and devices
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