CFD and RBD coupling-based direct force and aerodynamic force composite control numerical simulation method

Abstract

The invention discloses a direct force and aerodynamic force composite control numerical simulation method based on CFD and RBD coupling. According to the method, a flow control equation and a rigid body motion equation are solved through coupling, the conditions of an aerodynamic rudder deflection angle and a transverse jet flow outlet are changed in real time according to flight control law closed-loop feedback, and numerical simulation of the direct force and aerodynamic force composite control process is achieved. According to the numerical simulation method, the complex nonlinear couplingcharacteristics between nonlinear aerodynamic force and motion and between transverse jet flows can be fully considered, so the direct force and aerodynamic force composite control process is accurately simulated, and the numerical simulation method has the advantages of being high in simulation reliability and high in calculation efficiency.

Description

technical field [0001] The invention belongs to the field of missile maneuvering flight control and simulation, and in particular relates to a numerical simulation method of direct force aerodynamic compound control based on CFD and RBD coupling. Background technique [0002] Due to the continuous improvement of the level of modern air combat tactics, in the face of fast and highly maneuverable control targets, whether they can quickly occupy positions, launch the enemy first, and effectively evade them will determine the outcome of the battle to a certain extent. It is foreseeable that the future combat environment will increasingly emphasize the mobility and quick response capabilities of tactical missiles. [0003] Generally speaking, the maneuverability of tactical missiles depends on two aspects: one is the rapidity of response to control commands, and the other is the accuracy of the response results. Commonly used control methods for missiles include aerodynamic rudd...

AI Technical Summary

Problems solved by technology

[0005] Direct force-aerodynamic compound control involves high-maneuver flight under conditions of high angle of attack, large sideslip, and large rudder deflection angle of the missile. Interference between the jet flow and the external flow field near its upstream and downstream, switching from aerodynamic control to direct force-aerodynamic compound control, ignition mode and ignition logic of the attitude control pulse engine, direct force-aerodynamic coupling control and mutual cooperation, etc. Aerodynamic layout optimization design, direct force-aerodynamic coupling modeling, and composite control design pose huge technical challenges

At present, the industrial sector usually uses the dynamic model based on the static aerodynamic database to carry out the simulation work before the test flight. Due to the large uncertainty of the model, this method does not take into account the potential nonlinear aerodynamic and kinematic coupling characteristics, which increases the The risk of flight test may lead to the extension of the design cycle and the increase of design funds

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