A new approach to autopilot design for highly nonlinear missiles

Abstract

We propose a new approach to acceleration control of STT missiles which fully takes into account all nonlinearities of STT missiles, including the coupling effect due to bank and roll angles. We show that the missile dynamics with nonminimum phase can be transformed through a kind of partial linearization and singular perturbation techniques into the reduced system which is not only of minimum phase but also exactly I/O linearizable via feedback. Based on the resulting linear system, we can easily obtain a dynamic compensator which provides the desired input-output dynamic characteristics. We present a rigorous stability analysis of our autopilot controller and demonstrate the generality and practical use of our approach through simulation results. (Author) Page 1 Downloaded by KUNGLIGA TEKNISKA HOGSKOLEN KTH on July 30, 2015 | http://arc.aiaa.org | Abstract -In this paper, we propose a new approach to acceleration control of STT missiles, which takes into full account all nonlinearities of STT missiles including the coupling effect due to bank and roll angles. We show that the missile dynamics with nonminimum phase can be transformed through a kind of partial linearization and singular perturbation techniques into the reduced system which is not only of minimum phase but also exactly I/O linearizable via feedback. Based on the resulting linear system, we can easily obtain a dynamic compensator which provides the desired input-output dynamic characteristics. We present a rigorous stability analysis of our autopilot controller and demonstrate the generality and practical use of our approach through simulation results. (X, Y, Z) U,V,W p,g,r VM , M 7 m, p Q S, D

New parametric affine modeling and control for skid-to-turn missiles

“…for each yaw and pitch channel, where the time constant s. In fact, we could see that time constants larger or smaller than this gave negligible influence on performance as in [10].…”

“…[10], where fast maneuvering and high performance were achieved with this assumption. As for the equality in Assumption 2.4, the forward linear velocity is customarily assumed to be constant in the flight control area [6] and can be kept constant throughout maneuvers by throttle control [7], [8].…”

“…To handle this nonminimum phase problem, a partially linearized system has been applied to autopilot design [10] and the singular perturbation technique has been used to obtain an approximate minimum phase model for feedback linearizing control [11]. The controllers described in those articles require lookup tables for the inverses of aerodynamic lookup tables.…”

Full Envelope Missile Autopilot Design Using Gain Scheduled Robust Control

“…17,18, and 20 are characterized by the initial oscillations and a certain sensitivity to noise. Reducing controller bandwidth by adjusting the weights in the linear design procedure can improve both features.…”

“…The singular perturbation technique, together with a partial linearization,is employed in Ref. 18 to pursuethe same goal. A feedback linearization autopilot using an adaptive neural network structure is presented in Ref.…”