ThesisPDF Available

Rotorcraft Flight Control Design with Alleviation of Unsteady Rotor Loads

Authors:
  • University of Maryland

Abstract and Figures

The objective of this research effort is to develop rotorcraft flight control laws that minimize unsteady rotor loads by acting solely through the primary flight controls (first harmonic swashplate control). As opposed to Higher-Harmonic Control, this strategy does not affect stationary (periodic trim) loads, and is therefore effective only in maneuvering flight. However, such system could be readily integrated with existing or future Automatic Flight Control Systems (AFCS). The study considers control designs for both conventional and compound configurations. Starting from a non-linear simulation model of the rotorcraft developed in FLIGHTLAB®, which includes sufficient fidelity to simulate rotor loads and vibrations, Linear Time-Periodic models (LTP) are derived via linearization. Next, the Harmonic Decomposition methodology is used to approximate the LTP systems with higher-order Linear Time-Invariant (LTI) systems. Reduced-order systems are subsequently obtained by using singular perturbation theory. By retaining the higher-harmonics of the rotor loads in the output, the reduced-order models are shown to accurately predicted the influence of the zeroth harmonics of the rigid-body and rotor flapping states on the higher-harmonics of the rotor loads. This way, previous limitations such as the reliance on non-physics-based models and curve fits to approximate rotor loads are lifted. Next, model following flight control laws are developed based on the reduced-order models. Parametric studies are performed to provide insights on how both the feed-forward and feedback paths of the model following control laws can be used to alleviate the rotor loads. Also, the impact of load alleviation on handling qualities is studied. It is shown that, for a standard helicopter configuration, load alleviation comes at the cost of a degradation in handling qualities. However, for the case of a compound rotorcraft, allocation of the control signal to the redundant control surfaces provides load alleviation without degradation in the handling qualities. The flight control laws are subsequently optimized using CONDUIT® to meet a comprehensive set of stability, handling qualities, and performance specifications for specific mission task elements while minimizing the unsteady rotor loads. Finally, since industry will not only rely on LTP systems obtained from simulation models, a novel methodology is developed to identify LTP systems from flight test data. The methodology is successfully applied to JUH-60A Black Hawk flight test data using CIFER®. The identified LTP systems capture the Nb/rev component of the rotorcraft dynamics. Further, it is shown how the higher-harmonics of the rotor states contribute to the overall rotorcraft dynamics for up to a 7%. On the other hand, the rigid-body states contribute to the overall rotorcraft dynamics almost entirely through their zeroth harmonic. Flight control design based on LTP systems identified from flight-test data could benefit the Future Vertical Lift (FVL) program. FVL is a plan to develop a new generation of military helicopters for the U.S. Army with increased capabilities in speed, range, and payload, and reduced maintenance and operational cost. Because these rotorcraft would operate at significantly higher speeds than the current helicopters, alleviation of the higher harmonic rotor loads and flight envelope protection are key elements to reduced maintenance cost. These rotorcraft are also likely to employ redundant control surfaces which, in connection with LTP-based flight control design, demonstrated outstanding effectiveness towards the alleviation of unsteady rotor loads.
Content may be subject to copyright.
A preview of the PDF is not available
ResearchGate has not been able to resolve any citations for this publication.
Conference Paper
Full-text available
The present study considers two notional rotorcraft models: a conventional utility helicopter, representative of an H-60, and a wing-only compound utility rotorcraft, representative of an H-60 with with a wing similar to the X-49A wing. An Explicit Model Following (EMF) control scheme is designed to achieve stability and desired Rate Command / Attitude Hold (RCAH) response around the roll, pitch and yaw axes, while alleviating vibratory loads through both feed-forward and feedback compensation. The harmonic decomposition methodology is extended to enable optimization of primary flight control laws that mitigate vibratory loads. Specifically, Linear Time Periodic (LTP) systems representative of the periodic rotorcraft dynamics are approximated by Linear Time Invariant (LTI) models, which are then reduced and used in LQR design to constrain the harmonics of the vibratory loads. The LQR gains are incorporated in the EMF scheme for feedback compensation. One innovative approach is the addition of rotor state feedback to standard rigid body state feedback. A Pseudo Inverse (PI) strategy is incorporated into the EMF scheme for redundant control allocation. Finally, simulation results with and without load alleviation are compared and the impact of PI feed-forward and rotor state feedback compensation on handling qualities is assessed in terms of ADS-33E specifications.
Book
Reducing the theoretical methods of flight control to design practice, Practical Methods for Aircraft and Rotorcraft Flight Control Design: An Optimization-Based Approach compiles the authors’ extensive experience and lessons learned into a single comprehensive resource for both academics and working flight control engineers.
Article
Several methods for analysis of linear time periodic (LTP) systems have successfully been demonstrated using harmonic decompositions. Onemethod recently examined is to create a linear time invariant (LTI) model approximation by expansion of the LTP system states into various harmonic state representations, and formulating corresponding LTI models. Although this method has shown success, it relies on a second-order formulation of the original LTP system. This second-order formulation can prove problematic for degrees of freedom not explicitly represented in second-order form. Specifically, difficulties arise when performing the harmonic decomposition of body and inflow states as well as interpretation of LTI velocities. Instead this paper presents a more generalized LTI formulation using a first-order formulation for harmonic decomposition. The new first-order approach is evaluated for a UH-60A rotorcraft model and is used to show the significance of particular harmonic terms, specifically that the coupling of harmonic components of body and inflow states with the rotor states makes a significant contribution to LTI model fidelity in the prediction of vibratory hub loads.
Article
Linearized time-periodic models are extracted from a high-fidelity comprehensive nonlinear helicopter rotor model at a trim flight condition. Subsequently, a Fourier expansion-based model reduction method is used to obtain linearized timeinvariantmodels fromthe time-periodic models. These linearized models predict the effects of on-blade control systems such as active flaps on the rotor hub loads and hence are an important component required for vibration control and flight control interaction studies. The linearized models are verified against the nonlinear model at low-speed descending and cruise flight conditions. Inclusion of aerodynamic states corresponding to the unsteady aerodynamic model reduces the error in the peak-to-peak hubload amplitude predictions from over 80% to less than 10%. The time-periodic and time-invariant models are in excellent agreement. The linear time-invariant (LTI) models are also verified for closed-loop vibration reduction performance fidelity using active flaps activated through the higher harmonic controller. The flap deflection histories and the vibratory loads predicted using the LTI model and nonlinear model agree very well when the flap deflection is limited to 2?. The errors between the two models increase with the flap deflection amplitude.
Article
Formulation of linear time invariant (LTI) models of a nonlinear system about a periodic equilibrium using the harmonic domain representation of LTI model states is well established in the literature. This paper presents a computationally efficient scheme for implementation of a previously developed method for extraction of linear time invariant (LTI) models from a helicopter nonlinear model in forward flight. The fidelity of the extracted LTI models is evaluated using response comparisons between the extracted LTI models and the nonlinear model in both time and frequency domains. For time domain evaluations, individual blade control (IBC) inputs that have been tried in the literature for vibration and noise control studies are used. For frequency domain evaluations, frequency sweep inputs are used to obtain frequency responses of fixed system hub loads to a single blade IBC input. The evaluation results demonstrate the fidelity of the extracted LTI models, and thus, establish the validity of the LTI model extraction process for its use in integrated flight and rotor control studies.
Article
In a traditional single main rotor helicopter, only 4 controls arc available - lateral cyclic, longitudinal cyclic, main rotor collective pitch and tail rotor collective pitch. As such, redundancy is not available as all four controls arc needed to maneuver the aircraft in the four control axes - pitch, roll, yaw and heave. In contrast, high speed rotorcraft configurations (such as tilt-rotors and compound helicopters) have multiple redundant control effectors. The strategy for applying these control effectors, and in which proportion, is called 'control allocation1. This paper provides an evaluation and comparison of different control allocation methods, applied to a medium lift tilt rotor. The control allocation methods are evaluated based on a comprehensive set of time and frequency domain metrics, as well as robustness criteria. In addition to evaluation of standard control allocation methods, several control allocation methods arc further developed and evaluated for reducing flap motion of the rotors. A piloted fixed base simulation is performed, and pilot comments and data are presented. The paper concludes with discussion of the results and trade-offs of the most effective control allocation techniques.