Throat excursion type pneumatic vector nozzle with asymmetric rear body profiles

Abstract

The invention discloses a throat excursion type pneumatic vector nozzle with asymmetric rear body profiles. The throat excursion type pneumatic vector nozzle comprises a nozzle body, and the rear bodyprofiles of the nozzle body are arranged to be of asymmetrical structures. Under general conditions, the upper and lower rear body profiles of the outside of an outlet of the nozzle are asymmetrical,main flow flowing out of the outlet of the nozzle acts with an asymmetric nozzle rear body to generate a low pressure zone, the main flow is promoted to further be close to the wall surface of the nozzle rear body, and the nozzle vector angle is increased. Meanwhile, the wall face of the wall surface of the asymmetric nozzle rear body and the main flow of the nozzle generate interaction with different strengths and different ranges, and the nozzle pitch vector angles are not equal. Through the design of the asymmetric nozzle rear body profiles, the vector angle of the throat offset pneumaticvector nozzle is further increased, the pitch vector angles are not equal, the infrared stealth performance of the nozzle is improved, and the actual needs of the aircraft are met.

Description

technical field [0001] The present invention aims at increasing the size of the throat offset aerodynamic vectoring nozzle and provides a rear body structure with unequal vector angles, mainly by changing the rear body shape near the outlet of the nozzle to form a throat offset aerodynamic vectoring nozzle Increase the vector angle, and at the same time, provide the aircraft with unequal up and down vector angles (that is, pitch vector angles). Background technique [0002] With the development of science and technology and the improvement of actual demand, more and more thrust vectoring aeroengines will be used in future aircraft. The core of the thrust vectoring aeroengine to realize the thrust vectoring function is the thrust vectoring nozzle. The traditional mechanical thrust vectoring nozzle has complex structure, poor reliability and troublesome maintenance. Therefore, it is imminent to develop a thrust vectoring nozzle with simple structure, light weight and good ma...

AI Technical Summary

Problems solved by technology

However, in the future, as the requirements for infrared stealth of aircraft increase, asymmetric binary nozzle configurations will gradually appear, but there are very few asymmetric aero-engine nozzles with thrust vectoring functions.

At the same time, most of the asymmetrical nozzle configurations are deformed Laval nozzles (that is, convergent-divergent nozzles) with non-uniform expansion sections, and very few also have non-uniform convergent sections, resulting in non-uniform engine jets.

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