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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

Control surface deflections in simulation with step input signal.
© Copyright Policy - open-access
Related In: Results  -  Collection


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fig4: Control surface deflections in simulation with step input signal.

Mentions: The step input starts at 1 second with value [−1,1, 1]. Figure 3 shows that the response of the undamaged aircraft tracks the reference command from 0 to 5 seconds, which benefits from the proper selection of the initial values of α and f0. The damage is injected at 5 seconds, resulting in some transient oscillations during 5–8 seconds. The magnitudes of the oscillations are relatively small and admissible. After the oscillations, the angular rate responses track the reference signals again. Another step input is injected at 10 seconds. The response signal tracks the reference consistently, which proves the performance of the proposed method. The deflections of control surfaces are shown in Figure 4.


MRAC Control with Prior Model Knowledge for Asymmetric Damaged Aircraft.

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

Control surface deflections in simulation with step input signal.
© Copyright Policy - open-access
Related In: Results  -  Collection

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

fig4: Control surface deflections in simulation with step input signal.
Mentions: The step input starts at 1 second with value [−1,1, 1]. Figure 3 shows that the response of the undamaged aircraft tracks the reference command from 0 to 5 seconds, which benefits from the proper selection of the initial values of α and f0. The damage is injected at 5 seconds, resulting in some transient oscillations during 5–8 seconds. The magnitudes of the oscillations are relatively small and admissible. After the oscillations, the angular rate responses track the reference signals again. Another step input is injected at 10 seconds. The response signal tracks the reference consistently, which proves the performance of the proposed method. The deflections of control surfaces are shown in Figure 4.

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