Design of a flight stabilizer for fixed-wing aircrafts using H_∞loop shaping method

Adaptive Model Predictive Control of a Two-wheeled Robot Manipulator with Varying Mass

“…We are also investigating the possibility of applying AMPC methods to other test platforms developed by our research group. These include improving the performance of flight stabilizer systems of fixed-wing aircraft [48][49][50] and rotorcraft, 51 building better software-in-the-loop (SIL) and hardware-in-the-loop (HIL) testbeds, 52,53 investigating novel approaches to provide robustness against parametric uncertainties, 54 and constructing specialized autopilots for control loss scenarios. 55,56…”

Robust Design of H∞Controller for a Launch Vehicle Autopilot against Disturbances

“…Since the pitch rate trajectory is desired to be tracked, a new variable change is considered to meet our goal. So the pitch rate can be stated in terms of tracking error as: e q q c   (9) where qc is the nominal pitch rate profile. So a new state vector is defined as: In this approach, in order to find the appropriate control, first the dynamic coefficients at the moment of 100 seconds are extracted as shown in Table 1.…”

“…This problem is relevant, for instance, for disturbance rejection and tracking. It is known that H∞ control [5,6] is an effective method for attenuating such disturbances [7,8] and can be applied on vehicles requiring robust controllers such as flight stabilizer [9], VSTOL aircraft [10], and remote passive acoustic monitoring (PAM) vehicles that are used for data collection, call classification, and species identification [11,12]. In this theory the exogenous disturbances are modeled as bounded signals and performance is measured in terms of the resulted output.…”

“…Now by substituting(9) into the longitudinal equations of (6), the time-varying state space equations of ALV transform into following form:…”

A stability-guaranteed smooth-scheduled MIMO robust emergency autopilot for a lateral surface jammed UAV

“…While the literature cited deals with some individual aspects of the big picture, there is no single source devising a system that (i) obtains models for a surface-jammed aircraft as a whole (without separating lateral/longitudinal modes), (ii) derives conditions for stability and performance of smooth scheduled MIMO control over a large flight envelope, and (iii) verifies the proposed procedure through accurate numerical simulations. This work is partly based on the previous work of our research group constituting these individual ingredients, [17][18][19][20][21][22][23][24][25][26] but none of these amalgamate all into a theoretically supported and experimentally verified solution as presented here.…”