The integrated navigation system is the inertial navigation system (INS), corrected by global
navigation satellite system (GNSS) data. The correction could be done algorithmically by …

The paper is focused to design a robust and a simple fixed structure H∞ control synthesis
for an Electrohydraulic Servo System (EHSS) and comparing its performance with the …

Despite fuel flow rates being low during descent compared to climb and cruise, the potential
exists for significant fuel savings during that phase of flight. Increased fuel use, costs and …

A hybrid approach to the design of the attitude control system for a launch vehicle (LV) in the
atmospheric flight phase is proposed in this paper, where a structured H∞ controller is …

The design of flight control actuation system is facing major challenge due to the
development of more electrical aircraft. The task is to find the combinations of power …

This paper present a novel and scrutinized parametric modeling of a laboratory scale
helicopter, a twin rotor multi input multi output system (TRMS), by employing a real-coded …

Purpose–Attitude control of unmanned aerial vehicle (UAV) is the purposeful manipulation
of controllable external forces to establish a desired attitude, which is inner‐loop of the …

In order to realize the high precision attitude determination of the spacecrafts by star
sensors, it is necessary to optimize accurately and rapidly the modeling of distorted star …

Attitude control is the inner-loop and the most important part of the automatic flight control
system of an unmanned aerial vehicle (UAV). The information fusion-based optimal control …

As part of a research activity at Politecnico di Torino, aiming to develop multi-disciplinary
design procedures implementing nature inspired meta-heuristic algorithms, a performance …