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MRAC Control with Prior Model Knowledge for Asymmetric Damaged Aircraft.

Xu X, Yang L, Zhang J - ScientificWorldJournal (2015)

Bottom Line: A modification of linear model representation is given.An MRAC method is developed for the polytope model, of which the stability and asymptotic error convergence are theoretically proved.The proposed technique reduces the number of parameters to be adapted and thus decreases computational cost and requires less input information.

View Article: PubMed Central - PubMed

Affiliation: CNIGC Institution of Navigation and Control, Chedaogou No. 10, Haidian District, Beijing 100191, China.

ABSTRACT
This paper develops a novel state-tracking multivariable model reference adaptive control (MRAC) technique utilizing prior knowledge of plant models to recover control performance of an asymmetric structural damaged aircraft. A modification of linear model representation is given. With prior knowledge on structural damage, a polytope linear parameter varying (LPV) model is derived to cover all concerned damage conditions. An MRAC method is developed for the polytope model, of which the stability and asymptotic error convergence are theoretically proved. The proposed technique reduces the number of parameters to be adapted and thus decreases computational cost and requires less input information. The method is validated by simulations on NASA generic transport model (GTM) with damage.

No MeSH data available.


Related in: MedlinePlus

Commands and responses in simulation with step input signal.
© Copyright Policy - open-access
Related In: Results  -  Collection


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fig3: Commands and responses in simulation with step input signal.

Mentions: The damage case with loss of 20% semispan of the left wing tip is selected. Simulations are conducted on the nonlinear 6DOF GTM model, with maximum deflection of the control surfaces limited within ±30 degrees. The aircraft is flying normally at the beginning, injected with wing tip damage at 5 s during simulation. The simulation results with minor step commands are shown in Figure 3.


MRAC Control with Prior Model Knowledge for Asymmetric Damaged Aircraft.

Xu X, Yang L, Zhang J - ScientificWorldJournal (2015)

Commands and responses in simulation with step input signal.
© Copyright Policy - open-access
Related In: Results  -  Collection

Show All Figures
getmorefigures.php?uid=PMC4477241&req=5

fig3: Commands and responses in simulation with step input signal.
Mentions: The damage case with loss of 20% semispan of the left wing tip is selected. Simulations are conducted on the nonlinear 6DOF GTM model, with maximum deflection of the control surfaces limited within ±30 degrees. The aircraft is flying normally at the beginning, injected with wing tip damage at 5 s during simulation. The simulation results with minor step commands are shown in Figure 3.

Bottom Line: A modification of linear model representation is given.An MRAC method is developed for the polytope model, of which the stability and asymptotic error convergence are theoretically proved.The proposed technique reduces the number of parameters to be adapted and thus decreases computational cost and requires less input information.

View Article: PubMed Central - PubMed

Affiliation: CNIGC Institution of Navigation and Control, Chedaogou No. 10, Haidian District, Beijing 100191, China.

ABSTRACT
This paper develops a novel state-tracking multivariable model reference adaptive control (MRAC) technique utilizing prior knowledge of plant models to recover control performance of an asymmetric structural damaged aircraft. A modification of linear model representation is given. With prior knowledge on structural damage, a polytope linear parameter varying (LPV) model is derived to cover all concerned damage conditions. An MRAC method is developed for the polytope model, of which the stability and asymptotic error convergence are theoretically proved. The proposed technique reduces the number of parameters to be adapted and thus decreases computational cost and requires less input information. The method is validated by simulations on NASA generic transport model (GTM) with damage.

No MeSH data available.


Related in: MedlinePlus