In this paper, an efficient strategy is proposed to design the altitude holdmode autopilot for a UAVwhich is non-minimum phase, and its model includes both parametric uncertainties and unmodeled nonlinear dynamics. This work has been motivated by the challenge of developing and implementing an autopilot that is robust with respect to these uncertainties. By combination of classic controller as ...

We design a feedback control architecture for longitudinal flight of an aircraft. The multi-level architecture includes the flight control loop to govern the short term dynamics of the aircraft, and the autopilot to control the long term modes. Using H∞ performance and robustness criteria, the problem is cast as a non-convex and non-smooth optimization program. We present a non-convex bundle me...

A cooperative autopilot is developed for the control of the relative attitude, relative position, and absolute attitude of two maneuvering spacecraft during on orbit proximity operations. The autopilot consists of a open-loop trajectory solver which computes a nine dimensional linearized nominal state trajectory at the beginning of each maneuver and a phase space regulator which maintains the t...

Modern missiles must deal with stringent performance requirements and ensure robustness across a wide range of operating conditions during flight time. Classic gain-scheduling designs have been successful in practice, but do not provide theoretically ensured bounds on both robustness. Controllers are interpolated at intermediate switching them may cause instability. On the other hand, polytopic...

A new approach to gain scheduling the classical \three-loop" autopilot structure is discussed for both the single-axis (pitch) case and the three-axis case. Simulation results in the single-axis case show that the new gain scheduled controller yields better performance than a traditional approach. Analysis of the three-axis case indicates an even greater potential for performance improvement wi...

In this research we consider the problem of path following control for a small fixedwing unmanned aerial vehicle (UAV). Assuming the UAV is equipped with an autopilot for low level control, we adopt a kinematic error model with respect to the moving Serret-Frenet frame attached to a path for tracking controller design. A kinematic path following control law that commands heading rate is present...

Traditionally, missile autopilots have been designed using linear control approaches with gain scheduling. Autopilot design is typically carried out in the frequency domain and the plant is linearized around various operating points on the trajectory. Moreover, three single axis autopilots are usually designed without considering the interaction among the motion axes, i.e., the autopilots in ea...

ISSN 2277 5064 | © 2013 Bonfring Abstract--Complexity in autopilot logic design and confusion involved in its mode transition is one of the major reasons for the accidents in highly automated airliner. In this paper we present the usage of a recently proposed array logic based technique for designing the autopilot mode transition logic for a commercial aircraft in the lateral direction. This de...

Ship autopilots can be divided into conventional, only capable of maintaining a given heading, and advanced, which additionally follow „track” connecting the navigation points along ship’s route. The article presents structure prototype autopilot ship implemented in CPDev environment formulas allowing to determine settings course controller (PID) track (PI) cascade control. For each them, indiv...

Autopilot is a system designed to guide a vehicle without aid. Due to increase in flight hours and complexity of modern day flight it has become imperative to equip the aircrafts with autopilot. Thus reliability and consistency of an Autopilot system becomes a crucial role in a flight. But the increased complexity and demand for better accuracy has made the process of evaluating the autopilot f...