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Helicopter Control Energy Reduction Using Moving Horizontal Tail.

Oktay T, Sal F - ScientificWorldJournal (2015)

Bottom Line: Control energy savings due to this MHT idea with respect to a conventional helicopter are calculated.Parameters of helicopter FCS and dimensions of MHT are simultaneously optimized using a stochastic optimization method, namely, simultaneous perturbation stochastic approximation (i.e., SPSA).In order to observe improvement in behaviors of classical controls closed loop analyses are done.

View Article: PubMed Central - PubMed

Affiliation: College of Aviation, Erciyes University, 38039 Kayseri, Turkey.

ABSTRACT
Helicopter moving horizontal tail (i.e., MHT) strategy is applied in order to save helicopter flight control system (i.e., FCS) energy. For this intention complex, physics-based, control-oriented nonlinear helicopter models are used. Equations of MHT are integrated into these models and they are together linearized around straight level flight condition. A specific variance constrained control strategy, namely, output variance constrained Control (i.e., OVC) is utilized for helicopter FCS. Control energy savings due to this MHT idea with respect to a conventional helicopter are calculated. Parameters of helicopter FCS and dimensions of MHT are simultaneously optimized using a stochastic optimization method, namely, simultaneous perturbation stochastic approximation (i.e., SPSA). In order to observe improvement in behaviors of classical controls closed loop analyses are done.

No MeSH data available.


Responses of helicopter Euler angle states.
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Related In: Results  -  Collection


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fig5: Responses of helicopter Euler angle states.

Mentions: In Figure 5, closed loop responses of helicopter Euler angle states are given when the 1st closed loop system (solid black line) and 2nd closed loop system (solid blue line) are both excited by white noise perturbations. From Figure 3 it can be easily seen that, for both classical helicopter and helicopter with MHT, the qualitative (i.e., shape of the response) and quantitative (i.e., magnitude of the response) behaviors of Euler angles are basically the same. This can be explained using the fact that the expected values (E∞yi2) of outputs of interest (i.e., helicopter Euler angles in this paper) are very close and satisfy the constraints (E∞yi2 ≤ σi2).


Helicopter Control Energy Reduction Using Moving Horizontal Tail.

Oktay T, Sal F - ScientificWorldJournal (2015)

Responses of helicopter Euler angle states.
© Copyright Policy - open-access
Related In: Results  -  Collection

Show All Figures
getmorefigures.php?uid=PMC4477250&req=5

fig5: Responses of helicopter Euler angle states.
Mentions: In Figure 5, closed loop responses of helicopter Euler angle states are given when the 1st closed loop system (solid black line) and 2nd closed loop system (solid blue line) are both excited by white noise perturbations. From Figure 3 it can be easily seen that, for both classical helicopter and helicopter with MHT, the qualitative (i.e., shape of the response) and quantitative (i.e., magnitude of the response) behaviors of Euler angles are basically the same. This can be explained using the fact that the expected values (E∞yi2) of outputs of interest (i.e., helicopter Euler angles in this paper) are very close and satisfy the constraints (E∞yi2 ≤ σi2).

Bottom Line: Control energy savings due to this MHT idea with respect to a conventional helicopter are calculated.Parameters of helicopter FCS and dimensions of MHT are simultaneously optimized using a stochastic optimization method, namely, simultaneous perturbation stochastic approximation (i.e., SPSA).In order to observe improvement in behaviors of classical controls closed loop analyses are done.

View Article: PubMed Central - PubMed

Affiliation: College of Aviation, Erciyes University, 38039 Kayseri, Turkey.

ABSTRACT
Helicopter moving horizontal tail (i.e., MHT) strategy is applied in order to save helicopter flight control system (i.e., FCS) energy. For this intention complex, physics-based, control-oriented nonlinear helicopter models are used. Equations of MHT are integrated into these models and they are together linearized around straight level flight condition. A specific variance constrained control strategy, namely, output variance constrained Control (i.e., OVC) is utilized for helicopter FCS. Control energy savings due to this MHT idea with respect to a conventional helicopter are calculated. Parameters of helicopter FCS and dimensions of MHT are simultaneously optimized using a stochastic optimization method, namely, simultaneous perturbation stochastic approximation (i.e., SPSA). In order to observe improvement in behaviors of classical controls closed loop analyses are done.

No MeSH data available.