Vector deflection control method for binary vector nozzle

Abstract

The invention belongs to the technical field of aircraft engine control, and relates to a vector deflection control method for a binary vector nozzle. The method comprises the following steps: S1, determining a vector deflection angle target value; S2, determining an initial horizontal included angle of two expansion adjusting sheets under the condition that the binary vector nozzle does not deflect, and controlling the two expansion adjusting sheets to deflect according to the vector deflection angle target value; and S3, after the expansion adjusting sheets are adjusted in place, controlling two convergence adjusting sheets to deflect, specifically, the deflection direction of the two convergence adjusting sheets is the same as the deflection direction of the expansion adjusting sheets. According to the vector deflection control method for the binary vector nozzle, pneumatic loads needing to be borne by the expansion section can be shared in the convergence section, the working reliability of the binary vector nozzle is improved, and the service life of the binary vector nozzle is prolonged. The method is simple to implement, easy to modify and high in adaptability.

Description

Technical field [0001] The present application belongs to the technical field of aircraft engine control, and more particularly to a binary appropriate amount of nozzle vector deflection control method. Background technique [0002] The stealth performance is a typical characteristic and technical indicators of the new generation of combat aircraft. As the main component of the engine, the invasive performance of the exhaust system is critical to the engine and even the aircraft, and the binary vector nozzle Structural features can better achieve radar stealth and infrared stealth. The binary vector nozzle is easy to carry out stealth design, and it is easy to integrate the fusement design after the plane, and has been successfully applied to a foreign fighter in foreign countries. [0003] In the existing binary vector nozzle design, the nozzle laryntricular area and the outlet area can be adjusted. Considering the difference in binary vector nozzle and axis-symmetric nozzle, th...

AI Technical Summary

Problems solved by technology

[0005] a) The expansion section of the nozzle needs to bear all the aerodynamic load brought by the thrust vector, which has a great impact on the cooling of the expansion section of the nozzle, and may easily cause ablation of the expansion section of the nozzle;

[0006] b) The characteristic that one side of the convergent section of the vector nozzle can be independently controlled is not fully utilized, and the control potential of the binary vector nozzle is not fully utilized

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