A design method of vertical tail and horizontal tail configurations for outward inclined twin vertical tail configurations

Abstract

The invention discloses a design method of vertical tail and horizontal tail configurations for outward inclined twin vertical tail configurations, comprising the following steps: 1) establishing a calculation model of the aerodynamic derivatives of the vertical tail and the horizontal tail of the outward inclined double vertical tail configuration; 2) calculating the aerodynamic derivative of thevertical tail of the aircraft based on the calculation model in step 1; 3) establishing constraint equations of vertical tail configuration design for outward inclined double vertical tail configuration; 4) bringing that aerodynamic derivative of the vertical tail of the aircraft calculate in the step 2 into the constraint equation in the step 3 to be calculated, and completing the configurationdesign of the vertical tail; 5) calculating that influence of the vertical tail camber angle on the longitudinal static stability of the aircraft; 6) finishing the horizontal tail configuration correction, solving the problem that the conventional tail design method cannot be applied to the configuration design of the external tilt double vertical tail configuration tail; and the invention guarantees the longitudinal and heading stability handling quality of the aircraft with the external tilt double vertical tail configuration.

Description

technical field [0001] The invention relates to the technical field of aircraft empennage aerodynamic layout design, in particular to a configuration design method of a vertical tail and a horizontal tail with a camber double vertical tail layout. Background technique [0002] Modern fighter jets often adopt the aerodynamic layout of cambered double vertical tails. The existence of the camber angle directly makes it impossible to apply the traditional conventional tail design method based on performance constraints to the vertical tail configuration design. Steering characteristics will also increase the longitudinal stability of the aircraft and reduce the agility of the aircraft control. Therefore, an aircraft with a cambered double vertical tail configuration needs an effective design method to solve the optimal design of the vertical tail area and correctly correct the longitudinal and lateral control performance of the aircraft. Contents of the invention [0003] The...

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Problems solved by technology

[0003] The purpose of the present invention: to propose a vertical tail and horizontal tail configuration design method with outwardly inclined double vertical tail layout, to solve the problem that conventional tail design methods cannot be applied to external Problems in Empennage Configuration Design of Inclined Double Vertical Tail Layout

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