Design and ground-based simulation of an limited authority flight control system for the Westland Lynx Helicopter

A comparison of rate-limit compensation schemes for pilot-induced-oscillation avoidance

“…The (sub)-optimal compensator ensured the closed-loop satisfied a norm bound of γ = 1.51. Although, not investigated here, the possibility of model reduction would be quite appealing for such a high order compensator and previous results [11] suggest a reduced order compensator can often perform acceptably.…”

“…This compensator will be of the same order as the generalised plant, i.e., dim(A) = dim(K) + dim(W 1 ) + dim(W 2 ), although significant order reduction can sometimes be achieved in practice. For example, the work in [11], which used the original form of the scheme, achieved order reduction of over ten states. Note that in order to arrive at a solution, the following conditions must be satisfied:…”

Automatic take-off control system for helicopter &#x2014; An H<inf>&#x221E;</inf> apporach

“…The main components of helicopter automatic take-off system are a) altitude control rule b) position control rule and c) attitude control rule. A wide range of classical and nonconventional control methodologies have been applied to one of these components [1][2][3][4][5]. It should be emphasized that only few research works are available on complete integration of these components for automatic take-off system [6,7].…”

Adaptive Robust Control Techniques Applied to the Yaw Control of a Small-scale Helicopter

“…Since an adequate level of performance is required in practice, recent literatures have focused on quadratic stabilizing control with some performance such as LQR, H_ or H2 [6][7][8][9][10] disturbance attenuation and closedloop pole location based on LMI or other methods. A design technique well suited to the control of helicopters is the technique of H_ control.…”

“…Being an inherently multivariable technique and also being able to provide robust stability for systems subjected to uncertainty make H_ control an ideal candidate. A number of simulation studies and flight test [6][7][8][9] have investigated robust control methods on rotorcraft using H_ techniques. The effective method which can deal with H_ problem is the linear matrix inequality (LMI) method [11][12].…”