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.
Highlights
In order to control helicopters, collective and cyclic rotor blade pitches are used
In order to see the benefits of using Moving horizontal tail (MHT) on helicopters, the relative variation of the helicopter Flight Control System (FCS) energy, %J, was computed using %J = 100(Jn − Jr)/Jn
Moving horizontal tail (MHT) idea is investigated in order to reduce helicopter flight control system (FCS) energy
Summary
In order to control helicopters, collective and cyclic (i.e., longitudinal and lateral) rotor blade pitches are used. Throughout history some other control methods have been considered in order to avoid these drawbacks and for some other reasons such as reduction of control energy and redundancy in case of failures Some of these alternatives are using trailing edge flaps (TEFs) with (see [2,3,4]) and without (see [5,6,7]) classical swashplate mechanism, passive (see [8,9,10]) and active (see [11,12,13]) helicopter morphing, and MHT (see [14,15,16,17,18]). The specific optimization method, namely, SPSA, applied in order to trim the system is summarized This simultaneous design idea is applied for Puma SA 330 helicopter and closed loop responses of classical helicopter and helicopter with MHT are compared
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