A Design Method of Rigid/Flexible Continuously Adjustable Inlet

Abstract

The invention discloses a rigidity / flexibility combined continuous variable inlet duct design method. The method comprises the steps of determining the angle distribution of a fixed compression surface and an adjustable compression surface of a shock wave attaching opening corresponding to a design point, determining the requirement of an inlet duct for the throat height under different working states, designing an adjustable compression surface profile, designing a throat section and a diffusion section, according to the motion trail expected by the throat section of the inlet duct, designing a connecting rod mechanism, and completing the body structure design of the inlet duct. Meanwhile, in the design process, on the basis of the careful wide-speed-region wave system configuration, expansion fans of the outer convex faces of shoulders of the compression surfaces are used for performing wave absorbing processing, and the influence caused by shock wave / boundary layer interference to the performance of the inlet duct is restrained. In addition, the design method determines the relationship between the throat height and the horizontal displacement of an actuating mechanism, the corresponding relation between the working mach number and the adjusting amount of an adjusting mechanism is determined, and the adjusting rule of the inlet duct is determined.

Description

technical field [0001] The invention relates to the field of aircraft design, in particular to a supersonic air inlet. Background technique [0002] The air-breathing supersonic vehicle is one of the key development directions in the aerospace field. It has high military and social value, so it has been valued by various countries. As the air intake device of the engine, the air intake is one of the three key aerodynamic components of the air-breathing propulsion system. It directly faces the combustion chamber with high Mach number incoming flow and complex working conditions, and its design form and working characteristics significantly affect the It affects the overall performance of the entire propulsion system and even the aircraft. In practical applications, the engine needs to work in a wider flight envelope, which requires the inlet to have a wider working range of Mach number. [0003] The internal contraction ratio of the intake port is a key parameter in the des...

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Problems solved by technology

[0005] However, the existing scheme has problems such as complex adjustment mechanism, long response time, low reliability, etc. There are many problems in the adjustment, and the adjustment range of the existing scheme for the internal contraction ratio is relatively limited

In addition, in the design process of the existing adjustable inlet, the influence of controlling the shock wave / boundary layer interference inside the inlet on the inlet is often neglected

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