 The un-augmented open loop 6-DOF Aerosonde exhibits poor stability and control characteristics in compliance with MIL-F8785C flying quality standards.  As in most classical fixed wing aircrafts, the control inputs to Aerosonde result in pitch, roll and yaw rate responses (rate command characteristics). This has made manual trimming of the UAV, at a given flight condition, with a human pilot-...

The paper presents a methodology for the flight control law’s design for the trajectory pursuit using hierarchical dynamic inversion; this is based on separation of multi-time-scale and multi-loop closing method. The attitude angles are taken as slow variable while angular velocities as fast variables. The slow variables are controlled by the fast ones, which, in turn, are controlled by aerodyn...

More accurate attitude angles can make the control of four-rotor aircrafts more precise. Various filters have been adopted to get more precise attitude angles. However, so far there is no suitable analysis system to evaluate the performance of filters. In this paper, an analysis system has been designed which can get the realistic attitude angles directly and compare the processing results of f...

The advent of Global Navigation Satellite Systems has brought about an additional navigational aid for aircrafts. Due to their complementary error characteristic, various approaches involving Global Positioning System coupled with the Inertial Navigation System have been looked into for complete autonomous navigation and attitude estimation of the aircraft. In this paper, we study, through simu...

This paper presents the results of the modeling of a complex cooling system of a future commercial aircraft. The results from transient calculations will be presented, for instance the system behavior during the climb phase of the aircraft. Hereby the feasibility of a first control strategy will be investigated. Moreover the experience solving this modeling task coupling two different simulatio...