Dymola fuel system simulation for Aerospace
Dymola includes a powerful library for the device-oriented modelling of one dimensional thermo-fluid flow in networks containing vessels, pipes, fluid machines, valves and fittings. Using this library detailed models of the aircraft fuel system can be created to consider the steady state and dynamic behaviour of the total system. By integrating the fuel system model with the control system model we can then begin to explore other modes of operation including fault conditions, refuel, defuel and in-flight trimming of the fuel tanks.
Using the Dymola MultiBody library the fuel system could be coupled to a flight dynamics model of the aircraft and by adapting the Modelica Fluids library the mass and inertia effects of the fuel in the pipes and tanks could be reacted on to the airframe. Coupling the fuel system and flight dynamics models in this way, along with the appropriate control systems, would enable the in-flight operations of the fuel system to be fully investigated to verify that the operational logic is correct but also to check that the resulting effect on the airframe can be managed correctly by the flight control system.
Reuse of the fuel system model to study many steady state and transient effects both in a static and dynamic flight situations will improve the robustness of the fuel system and control system and save time through the reuse of the same model in all simulations.
Modelica Fluid and Media libraries
A unique feature of Modelica.Fluid is that the component equations and the media models as well as pressure loss and heat transfer correlations are decoupled rom each other. All components are implemented such that they can be used for media from the Modelica.Media library. This means that an incompressible or compressible medium, a single or a multiple substance medium with one or more phases might be used with one and the same model as long as the modeling assumptions made hold. Furthermore, trace substances are supported.
Modeling assumptions can be configured globally in an outer System object. This covers in particular the initialization, uni- or bi-directional flow, and dynamic or steady-state formulation of mass, energy, and momentum balance. All assumptions can be locally refined for every component.
Aerospace
