this paper presents a gain scheduled autopilot for pitch channel of a flying vehicle. the selected method is based on polynomial fuzzy systems. the method does not involve linearization about operating point. first the polynomial fuzzy model of pitch channel of the flight body is derived. next, using polynomial fuzzy system methodology the controller is design such that the outputs of the nonli...

In this paper, a flight path rate demand two loop autopilot in pitch plane called lateral autopilot is considered where the steady state gain of the autopilot system is non-unity .The present work is an attempt to achieve a unity steady state gain of the autopilot system which generates a flight path rate output for a flight path rate command. For this, a PI controller is introduced in the redu...

–A flight path rate demand modified three-loop lateral missile autopilot design methodology for a class of guided missile, based on state feedback, output feedback, reduced order Das & Ghosal observer (DGO) is proposed. The open loop undamped model of three-loop autopilot has been stabilized by using pole placement and state feedback. The non-minimum phase feature of rear controlled missile air...

– A flight path rate demand modified three-loop lateral missile autopilot design methodology for a class of guided missile, based on state feedback, output feedback, reduced order Das & Ghosal observer (DGO) and Linear Quadratic Regulator (LQR), is proposed. The open loop undamped model of three-loop autopilot has been stabilized by using pole placement and state feedback. The non-minimum phase...

– A flight path rate demand modified two-loop lateral missile autopilot design methodology for a class of rear controlled guided missile, based on state feedback, output feedback, reduced order Das & Ghosal observer (DGO) and PI controller is proposed. The open loop undamped model of two-loop autopilot has been stabilized by using pole placement and state feedback. The non-minimum phase feature...

This paper presents the development and preliminary results of a rapidly reconfigurable autopilot for small Unmanned Aerial Vehicles. The autopilot presented differs from current commercial and open source autopilots mainly as it has been designed to: (i) be easily reprogrammable via Simulink (models are directly transferred to the autopilot through the Real-Time Workshop’s code-generation capa...

Field trial is very critical and high risk in autonomous UAV development life cycle. Hardware in the loop (HIL) simulation is a computer simulation that has the ability to simulate UAV flight characteristic, sensor modeling and actuator modeling while communicating in real time with the UAV autopilot hardware. HIL simulation can be used to test the UAV autopilot hardware reliability, test the c...

The need for autonomous Unmanned Aerial Vehicles (UAVs) is very interesting nowadays. Autonomous UAVs provide the possibility of performing tasks and missions that are currently hazardous or can cost humans or money, enable autonomous search, persistent combat intelligence, surveillance and reconnaissance (ISR), and many other applications. This paper presents an overview of autopilot design wi...

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...