Unsteady Flow-field Coupling with Control Law Simulate the Aircraft Separation

摘要

Using unstructured dynamic mesh method, coupled with Euler equation solve, this paper establish the unsteady flow-field solve system. In this system, the rigid body motion is the result solved six-degree-of-freedom motion equation or user directly define. As a typical research model, AEDC [1] wind tunnel test model is computed in this paper. The computational solution is in very good agreement with the wind tunnel test result. The deflections of aircraft's four fins are defined for controlling aircraft attitude. Proportional and Proportional-Differential control law as the typical control law is used to control aircraft attitude that is in separation phase. Four fins were fixed, pitch angle controlled by Proportional or Proportional-Differential control law, the results of separation aircraft are contrasted to show differences. Those differences indicate that the control law is in effect. In time domain, through this simulate system, user can design and adjust the control law for separation aircraft. Last, this paper give the simulate result of the AEDC model separation those are controlled by three axes attitude control law.