A model for the propulsion system of a small-scale electric unmanned aerial is presented. This based on blade element momentum (BEM) propeller, with corrections tip losses, Mach effects, three-dimensional flow components, and Reynolds scaling. Particular focus placed estimation scale effects not commonly encountered in full-scale application BEM modeling method. Performance predictions are presented geometries representative several commercially available propellers. These then compared...

A model for the propulsion system of a small-scale electric Unmanned Aircraft System (UAS) is presented. This based on Blade Element Momentum (BEM) propeller, with corrections tip losses, Mach effects, three-dimensional flow components, and Reynolds scaling. Particular focus placed estimation scale effects not commonly encountered in full-scale application BEM modeling method. Performance predictions are presented geometries representative several commercially available propellers. These...

Various Coanda active flow control (AFC) actuator nozzles and surfaces along the trailing edge of a wing were experimentally investigated in propeller slipstream flow. These included both continuous discrete slot blowing as well sweeping jets. Surfaces circular, elliptical, bi�convex profiles. Each configuration was mounted to on benchtop setup. A at leading provided momentum source, lift pitching moment measured with six-component load cell. The resulting data used characterize aerodynamic...

The primary objective of this study is to determine the optimal Coanda active flow control (AFC) actuator location relative propeller slipstream for hover flight scenario. A secondary compare effectiveness that a traditional deflection surface. Circular actuators with continuous slot blowing were investigated in study. Two trailing-edge sections fixed spanwise length designed, fabricated, and tested at varying locations. goal testing was which AFC placement provides greatest benefit terms...

With the rapid increase in number of multi-rotor small unmanned aerial systems (sUAS) recent years and a plethora possible applications, aerodynamic aeroacoustic characteristics these vehicles become very important issues. Due to limited research on sUAS which include an airframe or support arm, this paper presents comprehensive analysis flow acoustic features with inclusion said geometry. The influence rotor orientation—either mounted above below airframe—was comprehensively studied through...

A phenomenological model, suitable for coupling to Large Eddy Simulations (LES) of flow control applications, is developed simulate the effects a nanosecond dielectric barrier discharge (NS-DBD) actuator. The model considers various surface and volume heating profiles reproduce key qualitative quantitative features NSDBD actuators. tuned match unique wave shape observed in Schlieren imagery speed displacement data. induced structure, comprised cylindrical component with tail, can be...

Detect and Avoid (DAA) systems are complex communication locational technologies comprising multiple independent components. DAA support communications between ground-based space-based operations with aircraft. Both manned unmanned aircraft (UAS) rely on location for safe flight operations. We examined the occurrence duration of losses radar automatic dependent surveillance–broadcast (ADS-B) operating in proximate airspace using data collected during actual Our objectives were to identify...

A small inductively coupled plasma source has been developed for use in an ion thruster. 10.1-mm-diameter thick film silver spiral antenna is fabricated on a low-temperature cofired ceramic with 35-μm dielectric over the antenna. The able to sustain argon frequency range from 448 1020 MHz pressures ranging 50 mtorr 1.75 torr. Plasma start powers ranged 3 W minimum down 0.1 W. Antenna electric field measurements have made air and compared simulation of using COMSOL. These results show that...

Proper exploitation of derived angle attack (AOA) and sideslip from low-cost attitude heading reference system sensors found in general aviation aircraft is a candidate solution for improving flight safety. This approach uses equations AOA that are solved on board real-time, using state data information provided by sensors. These function vehicle parameters stability control derivatives, addition to the angular displacement rate sensor outputs. paper characterizes evaluates feasibility part...

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...

Given the success of NASA/JPL's Ingenuity helicopter, study Martian flight vehicles and their aerodynamic characteristics has become a rapidly growing field research. At NASA Ames, "Rotor Optimization for Advancement Mars eXploration" (ROAMX) team partners have published designs an advanced, second generation helicopter -- "Mars Science Helicopter" (MSH) which possesses novel rotor geometry. This paper presents independent development validation numerical model assessing rotorcraft...

The aerodynamic interactions between a propeller, wing, and control surface are investigated at zero freestream velocity to simulate flight conditions associated with hovering operations of tail-sitter aircraft. Oil flow visualizations Kiel probe surveys indicated that thrust-producing propeller operating generates wake over wing’s is significantly skewed towards the slipstream’s downwash component. This testing also showed profile given chord location follows bimodal distribution deficit...

Unmanned aircraft systems (UAS), commonly known as drones, are part of a new and budding industry in the United States. Economic public benefits associated with UAS use across multiple commercial sectors driving regulations which alter stringent laws currently restricting flights over people. As enacted more populate national airspace, there is need to both understand quantify risk impacts uninvolved public. The purpose this study was investigate biomechanical response injury outcomes Post...

For most orbital maneuvers, small satellites in the sub-10 kg range require thrusters capable of spanning micro-Newton to milli-Newton force range. At this scale, electrokinetic (EK) pumping offers precise metering monergolic or hypergolic liquid propellants under purely electrical control at pressures and flow rates well-suited microthruster applications. We have demonstrated direct indirect EK for delivery anhydrous hydrazine hydrogen peroxide monopropellants, respectively, into...

Aircraft ice accretion poses real challenges in the commercial and military aviation world. Significant work is required to certify an aircraft icing, often protection systems are minimize aerodynamic impact of ice. Models simulations a primary analysis tool used these efforts. Numerous tools exist for evaluating 2D 3D shapes, but each have benefits detriments. In this study, ANSYS FENSAP-ICE was assess growth on complex 3-dimensional inlet. The results compared scan shape show good...

Flight testing procedures for a small scale Unmanned Aerial System are presented. The major performance parameters estimated include the zero-lift drag coefficient, span efficiency factor, lift-to-drag ratios, and excess power across range of airspeeds. A ground based experimental method measuring thrust commercially available electric motor system is detailed. These compared to first order design estimates in close loop. detailed discussion onboard data acquisition sensor suite provided....

View Video Presentation: https://doi.org/10.2514/6.2023-2071.vid The Parametric Flutter Margin (PFM) method is utilized to identify the structural dynamic characteristics of an Unmanned Aerial Vehicle's wing in a series Ground Vibration Tests (GVTs) and initial flight-testing study. A self-contained electro-mechanical excitation system was developed excite measure resultant dynamics such that Frequency Response Functions (FRF) can be identified from recorded inertial data. finite element...