Simulation calculation method and system for transient synchronous unfolding of aircraft folding rudder

Abstract

The invention provides a simulation calculation method and system for transient synchronous unfolding of an aircraft folding rudder. The simulation calculation method comprises the following steps that hydrodynamic software and finite element software are applied to calculate an aerodynamic equivalent load borne by the aircraft at the initial unfolding moment of the folding rudder surface in the actual flight process; hydrodynamics and finite element software are applied to calculate the aerodynamic equivalent load borne by the aircraft in the unfolding process of the folding control surface in the actual flight process; the method also includes describing high-temperature and high-pressure gas generated after the explosive explodes by adopting a state equation, and simulating fluid-solid coupling interaction in real time through any Euler-Lagrange method; selecting and arranging the initial configuration and the initial orientation of the damping lug; and selecting the initial closed container volume and explosive equivalent of the folded rudder based on a simple model calculation result. According to the invention, high-temperature and high-pressure gas generated by explosion of the explosive is used as an expansion energy source, a simple model verification test and a fluid-solid coupling calculation method are adopted, the design efficiency is effectively improved, and repeated iteration in the design process is reduced.

Description

technical field [0001] The invention relates to a design calculation method in the field of aerospace, in particular to a simulation calculation method and system for instantaneous and synchronous deployment of a folding rudder of an aircraft. Background technique [0002] With the continuous innovation and development of aviation technology and guided weapons, airborne guided weapons are required to minimize the space occupied by the aircraft when on-hook, especially under the requirements of improving the stealth performance of military aircraft, airborne guided weapons are generally required style of mounting. On the other hand, guided weapons often require larger aerodynamic control surfaces to obtain sufficient aerodynamic control torque in order to obtain higher control maneuverability. The folding technology of the rudder surface has become the key technology to solve the contradiction between the control surface of the guided weapon and the mounting space of the car...

AI Technical Summary

Problems solved by technology

Therefore, the traditional mechanical folding technology has been unable to meet the technical requirements of synchronization and instantaneous design of folding rudders in complex environments.

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