This paper presents an integrated approach for the development of complex aerospace systems. To better illustrate the scope of this technique, a case study for a complex aerospace model based on the HL-20 personnel launch system is provided.
This paper shows how a vehicle’s geometry can be optimized, control coefficients calculated, open-loop plant model created, flight controller designed, and closed-loop simulation run, to confirm that system-level requirements are satisfied.
As any airline passenger who has experienced moderate turbulence knows, an aircraft is not a rigid structure. In certain circumstances, the complex interaction between the flexible structure and the aerodynamics can produce undesirable effects.