Abstract
The landing phase during a flight probably is the most dangerous part, as most of the accidents occur in this phase. A robust trajectory tracking controller is presented to autoland a civil aircraft subjected to severe wind disturbances to improve the aircraft’s safety. Firstly, the dynamic models of the aircraft and windshear are built. Secondly, a stable inversion (SI) based robust autolanding controller (SIRAC) is proposed. In this architecture, the SI algorithm is used to improve the output tracking precision, while the H ∞ synthesis is applied for enhancing robust stability against uncertainties caused by wind disturbances. Finally, two scenario simulations are carried out for the automatic landing control of a large civil aircraft. Significant performances on the system have been achieved without any disturbance. In addition to that, the proposed SIRAC can also track the desired autolanding trajectory with high precision, even under large wind condition.
Highlights
For the civil aircraft, the automatic control system plays an important role in assisting the pilot in all flight phases
This paper proposes an integrated control method that combines the stable inversion (SI) algorithm and H∞ synthesis for civil aircraft autolanding system in order to solve the trajectory tracking and disturbance rejection problem simultaneously, with the adaptive ways of thinking to propose some algorithms of control that are of wider application [21]
This paper presented a new approach to the Automatic Landing System (ALS) of the civil aircraft
Summary
The automatic control system plays an important role in assisting the pilot in all flight phases. BAE firstly developed the Automatic Landing System (ALS) for commercial aircraft in 1965 to increase the safety of the landing maneuver [1]. It has been widely used since as it can provide safe and comfortable landing. There are four segments in the landing maneuver [2] (see Figure 1): alignment, glide slope, flare, and taxiing. An aircraft aligns and localizes itself to a befitting altitude and approach angle, according to these transmitters. It starts landing and decreasing the altitude [3]. The autolanding control is inherently a trajectory tracking control problem
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