Attitude control law design for spacecraft large angle maneuvers is investigated in this paper. The feedback linearization technique is applied to the design of a nonlinear tracking control law. The output function to be tracked is the quaternion attitude parameter. The designed control law turns out to be a combination of attitude and attitude rate tracking command. The attitude-only output fu...

This paper proposes several nonlinear control strategies for trajectory trackingof a quadcopter system based on the property of differential flatness. Its origi-nality is twofold. Firstly, it provides a flat output for the quadcopter dynamicscapable of creating full flat parametrization of the states and inputs. Moreover,B-splines characterizations of the flat output and the...

In this paper, we develop a method to design the input control to track the output of a nonminimum-phase nonlinear systems asymptotically. The design of the control inputs is based on an exact linearization. To perform the exact linearization, the other output should be selected such that its relative degree is equal to the dimension of the system. Furthermore, the desired output of the output ...

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...

In this paper, a control strategy combining the feedback linearization theory and sliding mode variable structure is proposed to solve various nonlinear factors, uncertainty of external disturbance high-precision pressure problems in Direct-Drive Volume Control (DDVC) electro-hydraulic servo system. The mathematical model DDVC system established, factors are accurately linearized by theory. com...

A straight forward application of feedback linearization to the missile autopilot design for acceleration control may be limited due to the nonminimum characteristics and the model uncertainties. As a remedy, this paper presents a cascade structure of an acceleration controller based on approximate feedback linearization methodology with a time-delay adaptation scheme. The inner loop controller...

The general goal of this paper is to identify a transformation group that can be used to describe a class of feedback interconnections involving subsystems which are modeled solely in terms of Chen–Fliess functional expansions or Fliess operators and are independent of the existence of any state space models. This interconnection, called an output affine feedback connection, is distinguished fr...