This paper introduces the Shape Adaptive Blades for Rotorcraft Efficiency (SABRE) Horizon 2020 research program and presents initial comprehensive analysis results on efficacy of adapting blade shapes as a means reducing rotorcraft power requirements emissions. The aims are introduced, followed by discussion six different morphing concepts that will be explored. mechanisms based active camber, chord extension, twist, tendon technologies. SABRE explore use these individually in combination,...

Many traditional ship–rotorcraft interactional simulation approaches, including those used for pilot training, use a one-way coupling between aerodynamics and flight dynamics. In coupled method, the standalone ship airwake is superimposed on rotor, modifying its inflow. However, because rotor wake does not alter unaffected by landing deck or superstructure, may capture all relevant phenomena. To important aerodynamic phenomena such as dynamic ground wall effects, two-way fully simulations be...

During rotorcraft ship-deck landing operations, complex interactional aerodynamic phenomena occur between the rotor and ship airwakes which are not fully understood. To aid in ship–rotorcraft investigations, efficient mid-fidelity airwake solutions needed. Additionally, effects of motion have been explored much. In this study, NATO Generic Destroyer, a shared, representative geometry created for collaborative studies, was investigated numerically using GPU-accelerated Lattice-Boltzmann...

Rotorcraft shipboard operations are risky and demand high piloting skills. To gain further understanding familiarize pilots with these complicated scenarios, various methods of computational simulations have been used in the past decades. Yet, some simulation may not capture a realistic response rotorcraft due to simplified modeling interactional aerodynamics order achieve real-time capability for pilot training. Thus, improvements required, experimental data that unveil dynamics between...

The aeromechanics of a model-scale, lift-offset rotor system designed for high-advance-ratio forward flight were investigated by means numerical comprehensive analysis as well hover and wind-tunnel testing. 2-m-diam was tested in single-rotor coaxial counter-rotating configuration. focus on the development computational model its validation advance ratios up to 0.5, at lift offsets 20%. Blade structural characteristics modeled according measured elastic properties, reduced-order aerodynamics...

An evaluation of two simulation techniques applied to ship airwakes is performed and correlated with high-quality wind tunnel measurement data. The objective provide further understanding the flowfield evaluate a new cost-effective approach that promises rapid turnaround so it can be in flight simulators enhance pilot training safety for shipboard aviation operations. Flowfield results from high-fidelity, conventional unstructured unsteady Reynolds-averaged Navier–Stokes (uRANS)...

The edm aerotec CoAX 600 rotorcraft was converted to an uncrewed aerial vehicle at the Technical University of Munich. In this work, a higher-order physics-based model system identified based on flight test data and blade element momentum theory (BEMT). paper describes structure identification techniques used in process. validated for control design pilot training purposes. simulation consists developed by coupling dynamic rotor with rigid-body fuselage. Aerodynamic models both fuselage...

A 600kg helicopter drone was developed at the Technical University of Munich based on edm aerotech GmbH CoAX 600 rotorcraft. In this work, a simulation model for and validated control design pilot training purposes. The consists physics-based structure, by coupling dynamic rotor with rigid body fuselage. Both aerodynamics, which utilizes blade element momentum theory to compute forces moments, fuselage aerodynamics include unknown parameters, are estimated flight test data, using Output...

A coaxial helicopter with a maximum take-off weight of 600 kg was converted to an unmanned aerial vehicle. minimally invasive robotic actuator system developed, which can be retrofitted onto the copilot seat rotorcraft in short period time enable automatic flight. The flight control robot includes electromechanical actuators, are connected cockpit inceptors and helicopter. Most sensors avionic components were integrated into modular for faster integration rotorcraft. mechanical design...

Safe flight with maneuvers of rotorcraft systems in the near vicinity Naval ships poses a number challenges due to complex, unsteady wake shedding from ship surface. To prepare pilots operate these conditions, it is desired ensure accurate airwake simulation capabilities that provide an understanding flow field and are sufficiently cost-effective so they can be applied simulators enhance pilot training safety. While simple frigate shape (SFS2) geometry has been extensively studied,...

In a closely spaced, coaxial counter-rotating (CCR) rotor, the passage of upper and lower rotor blades over each other results in transient loads blade deformation. This paper describes measurement numerical modeling these deformations single-bladed, 2-m-diam, rigid CCR system hover. Three-dimensional deformation was measured using time-resolved digital image correlation technique, simultaneously with thrust pitch link loads. A model developed comprehensive analysis CAMRAD II. validated by...

Time-resolved particle image velocimetry measurements were made in the turbulent flow environment below a hovering rotor near ground plane that was covered with mobile sediment particles. The results compared to near-wall produced by nominally equivalent two-dimensional wall jet. objective understand fluid dynamic mechanisms of how mean flow, stochastic turbulence, and concentrated vorticity affected mobilization pickup particles from bed. Another better assumptions would be required for...

This paper investigates the modeling approach for simulation of a rotorcraft encountering vortex or wake trailing from solid structure. The flow field surrounding rotorcraft, including inflow into main rotor, was computed using computationally efficient Lattice-Boltzmann method (LBM). fluid solver enhanced GPU computing and an interface included to exchange thrust between flight dynamics simulations. interaction with modeled by superposition fully-coupled model. added vortex/wake induced...

The aerodynamics and dynamics of a sub-scale coaxial rotor model designed for high-advance-ratio forward flight were investigated by means comprehensive analysis. Hover measurements used to calibrate validate the numerical predictions. system analyzed with focus on interactional responsible in-creased hub loads, blade deflections. A aeromechanics reduced-order modeling using free vortex wake method was ensure computational efficiency. Performance predictions as well predicted flap...

View Video Presentation: https://doi.org/10.2514/6.2023-1752.vid Recent advances in technology have enabled a range of electric-powered aircraft for missions from package delivery to urban air taxi operations. Many these designs rely on wingborne flight using distributed electric propulsion or multiple propellers mounted the wings. From safety and performance perspective, it is important understand physics aerodynamic phenomena, especially interactions between single wings, their impact....

Rotor-rotor and rotor-body interactions can have a first-order impact on multirotor vehicle performance. Identification of these performance impacts has previously been limited to numerical analysis controlled environment testing, they are largely unknown for full-scale flight vehicles. To capture interactional effects, the work presented in this paper used series wind tunnel test experiments quadrotor at multiple speeds sideslip angles estimate rotor-rotor interactions. Performance data was...