The traditional three-loop autopilot[11] suffers from coupling in pitch, yaws, roll channel as well as degraded performance due to huge aerodynamic uncertainties. Sliding mode control is applied to design autopilot for skid-to-turn missile (STT) missile systems to overcome the above stated difficulties. The design has two steps. The first step involves feedback linearization and the second stag...

This paper proposes an autopilot system that can be used to control the small scale rotorcraft during the flight test for linear-frequency-domain system identification. The input frequency swept is generated automatically as part of the autopilot control command. Therefore the bandwidth coverage and consistency of the frequency swept is guaranteed to produce high quality data for system identif...

This paper deals with a nonlinear adaptive autopilot design for agile missile systems. In advance of the autopilot design, an investigation of the agile turn maneuver, based on the trajectory optimization, is performed to determine state behaviors during the agile turn phase. This investigation shows that there exist highly nonlinear, rapidly changing dynamics and aerodynamic uncertainties. To ...

In this paper, a new methodology to design robust sliding-PID tracking motion controllers for a certain class of nonlinear systems is presented. The methodology is based upon the combination of the conventional PID control, sliding-mode control in Filippov’s sense, and relative degree concepts. The tracking of desired motion trajectories is performed in the presence of nonlinearities, modeling ...

A tactical skid-to-turn missile autopilot is designed and implemented using a two step design process that results in an optimal output feedback with a fixed, low-order dynamic compensator for reduced design and implementation cost. The gain design consists of minimizing a performance index in which measurements and controls are appropriately weighted to achieve the desired speed of response, w...

State-dependent Riccati equation based controllers are becoming increasingly popular because of having attractive properties like optimality, stability and robustness. This paper focuses on the design of a roll autopilot for a fin stabilized and canard controlled 122mm artillery rocket using state-dependent Riccati equation technique. Initial spin is imparted to rocket during launch and it quic...

Although intrinsically marine craft are known to exhibit non-linear dynamic characteristics, modern marine autopilot system designs continue to be developed based on both linear and non-linear control approaches. This article evaluates two novel non-linear autopilot designs based on non-linear local control network and non-linear model predictive control approaches to establish their effectiven...

This paper presents an initial study of the autopilot development of an unmanned surface vehicle (USV). The USV named Springer is being developed to carry out pollutant tracking, and environmental and hydrographic surveys in rivers, reservoirs, inland waterways and coastal waters, particularly where shallow waters prevail. The catamaran shaped autonomous vessel is modelled as a two input, singl...

This paper applies LPV(Linear Parameter Varying) control techniques to a blimp. The aim of the project is the development of a practical technique for the unmanned aerial observation and surveillance. In order for a blimp to perform observation and detection, precise flight path control is needed. The error resulting from modeling a real system cannot be avoided, however accurate the model is. ...

A nonlinear guidance law is presented for the im-pact time control of an interceptor against a stationary target. Exact closed form expressions for impact time and the guidance command are derived. For a given engagement geometry, a given impact time corresponds to a unique initial heading error. For interceptors launched with any other initial heading error, a term proportional to impact time ...