In the last decade, computer vision field has seen significant progress in multimodal data fusion and learning, where multiple sensors, including depth, infrared, visual, are used to capture environment across diverse spectral ranges. Despite these advancements, there been no systematic comprehensive evaluation of fusing RGB-D thermal modalities date. While autonomous driving using LiDAR, radar, RGB, other sensors garnered substantial research interest, along with RGB depth modalities,...

In this paper, an adaptive feedforward control framework is proposed for the suppression of aircraft structural vibrations induced by gust perturbations to increase resilience !ight law in presence aeroelastic/aeroservoelastic interactions. Currently, with nonadaptive laws usually include roll-off or notch lters avoid However, if changes conguration aresignicant,the frequencies the!exible modesof may beshifted, andthe notchlterscould become totally ineffective. With approach, !exible modes...

In response to the concerns of aeroelastic community, NASA Dryden Flight Research Center, Edwards, California, is conducting research into improving flight flutter (including aeroservoelasticity) test process with more accurate and automated techniques for stability boundary prediction. The important elements this effort so far include following: (1) excitation mechanisms enhanced vibration data reduce uncertainty levels in estimates; (2) investigation a variety frequency, time, wavelet...

Adverse aeroservoelastic interaction is a problem on aircraft of all types causing repeated loading, enhanced fatigue, undesirable oscillations and catastrophic flutter. This adverse response traditionally suppressed using notch and/or roll off filters in the primary flight control system architecture. solution has pitfalls; rigid body performance degraded due to resulting phase penalty filter may not be robust nominal behavior. An adaptive approach been developed that determines optimal...

Atransferfunction estimationprocedurethatrelies on thetime-frequency analysis of input and output signalsis described. This method was developed in an attempt to better identify the aeroelastic behavior NASA Dryden’ s F-18 systems research aircraft predict its e utter boundaries using in-e ight experimental data. Numerical experimentson eld data show thatexploiting characteristics excitation inputscan bring enhanced accuracy cone dence when identifying multi-input/multi-output transfer...

This paper investigates the modeling of parameter-varying nonlinear aeroelastic systems using Volterra theory. With this approach, system dynamics are expressed in terms a set kernels. It is well known that parameters systems, such as natural frequencies and damping ratios, change with flight condition. Therefore, characterized by different kernels at each These must be extracted from data condition interest: relatively costly procedure. presents kernel extrapolation method designed to model...

Fly-by-feel (FBF) is a new paradigm for safely maximizing aircraft stability and performance across wide range of conditions wherein the autonomously intelligently senses aerodynamic environment efficiently adapts structure control surfaces to suit current mission objectives. FBF depends on an integrated active approach flight control, structural mode attenuation, flow control. Desired performance, gust load alleviation aerostructural in presence complex aeroservoelastic (ASE) model...

Flight testing for envelope expansion remains dangerous and costly because of difficulties in accurately predicting the onset flutter. Approaches have been developed that are able to identify optimal models aeroelastic dynamics based on flight data but not predict responses at all airspeeds. Those previous approaches extended include parameter variations models. Specifically, parameter-varying Volterra kernels identified inclusion with theoretical analysis. The new approach is applied a...

An extension of the program STARS (a general-purpose structural analysis program) has been developed. This implements a complete aeroservoelastic capability. Previous capabilities included finite-element modeling as well statics, buckling, vibration, dynamic response, and flutter analyses. The authors describe program, formulate fundamental aeroservoelasticity equations therein, provide examples dynamic, aeroelastic, analyses pertaining to X-29A aircraft. These include summaries vibration...

Representation and identification of a nonlinear aeroelastic pitch-plunge system as model the NARMAX class is considered. A difference equation describing this aircraft derived theoretically shown to be form. Identification methods for models are applied dynamics their properties demonstrated via continuous-time simulations experimental conditions. Simulation results show that 1) outputs closely match those generated using 2) provide accurate discrete-time parameter estimates. Application...