National Aeronautics and Space Administration

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Determining the Size, Strength and Scope of a Quadcopter’s Ground EffectDetermining the Size, Strength and Scope of a Quadcopter’s Ground Effect

National Aeronautics and Space Administration

Unmanned Aerial Vehicles (UAV) applications have typically been restricted to short term, limited range fly-by missions with fixed-wing UAVs. The Native American Research Team (NART) has designed a proof-of-concept model with integrated solar and wind technology to address the short term flight limitations. To extend flight times and distances the UAV is equipped with in-flight re-charging capability via solar cells and loop wing wind turbines. Additionally, it is configured to operate as its own ground-based portable charging station allowing for multi-day missions over longer distances.

Abstract

Data Acquisition and Reconnaissance in variable environments: An eco-friendly Unmanned Areal Vehicle that has the ability to make environmental and scientific observations over long term missions.

Mission

•How to counteract energy consumption?•What design will be most efficient and

maneuverable?•Will solution to energy consumption disrupt

flight?•How will data be received?•Future?

Questions

The proof-of-concept quadrotor was designed using off-the-shelf components. Renewable energy systems will provide stable flight for 30 minutes and land in a pre-determined location to enter a charging/data transmission mode. After recharging, it will "hop" from waypoint to waypoint as needed.

Hypothesis

Computational Fluid Dynamics (CFD) examinations illustrated that the presence of the loop wing wind turbines will not interfere significantly with the lifting and directional rotors. The downward mounted motors' downwash do not impinge upon the loop wing nor does the loop wing turbulence affect the motors.

Simulation

Proof-of-ConceptH-Frame quadrotor chosen for mountable area

Proof-of-concept designed with Rhino 3D CAD software

Concept model dimensions: 24" x 36" with a top deck area of 144 square inches

Suitable for:• hostile environments such as the polar

regions, extraterrestrial• environmental monitoring• agricultural monitoring• wildlife management

Discussion

Dr. William Warmbrodt - NASA, Aeromechanics Branch ChiefLarry Young - NASA, Aeromechanics Branch design EngineerNeeda Lin - NASA, Mechanical Engineer InternGary Brandt - Northwest Indian College, Native American Research Team Mentor

Unmanned Multirotor Applications of Renewable Energy Systems for Variable Environments

Acknowledgments

NART: Native American Research TeamWayne Yandell, Jessica Williams, Kirsch Davis, Gabriel Brien, Faye Clawson, Joshua Danny

ConclusionA large-scale vehicle with mounted solar cells and wind generators could fly (with stability) various missions in a "hop-charge/read-hop" method for a variety of applications. For a vehicle that matches the mission objective and specific functional requirements of various environments with minimal charging time, a frame large enough to house the necessary solar panels and wind generators would have to be constructed with lightweight materials and large bottom mounted propellers for efficient long-distance flights between charging. With further developments in power storage, solar/wind, and autonomous control technology as well as customization per application, this method should be unquestionably more effective than fixed-wing UAV's with standard fossil fuel or electric propulsion systems for autonomous low-altitude measurement and delivery in most conceivable environments.

National Aeronautics and Space Administration

www.nasa.gov

Native American Research Team

Gabriel Brien, Turtle Mountain Community College Fayetta Clawson, Navajo Technical CollegeJoshua Danny, Haskell Indian Nations University Kirsch Davis, Navajo Technical CollegeJessica Williams, Northwest Indian College Wayne Yandell, Haskell Indian Nations University

Tribal College and University Programs Undergraduate LevelCode: AVBranch Title: Aeromechanics Office and Native American Research Team

National Aeronautics and Space Administration

www.nasa.gov

• Unmanned Aerial Vehicle (UAV) applications have typically been restricted to short term, limited range fly-by missions dominated by relatively energy efficient fixed-wing UAVs. The Native American Research Team (NART) has designed a proof-of-concept model with integrated solar and wind technology to address the short term flight limitations on a multirotor format for maximum maneuverability and vertical take-off and landing capabilities. To extend flight times and distances the UAV is equipped with in-flight re-charging capability via solar cells and loop wing wind turbines. Additionally, it is configured to operate as its own ground-based portable charging station allowing for autonomous multi-day missions over longer distances.

Abstract

National Aeronautics and Space Administration

www.nasa.gov

Extended UAV missions in variable environments:An eco-friendly Unmanned Aerial Vehicle that has the ability to make environmental and scientific observations over long term missions.

Mission

National Aeronautics and Space Administration

www.nasa.gov

The proof-of-concept quadrotor was designed using off-the-shelf components. Renewable energy systems will provide stable flight for 30 minutes and land in a pre-determined location to enter a charging/data transmission mode.

Hypothesis

After recharging, it will autonomously take flight to its next determined waypoint according to the directives of the mission, repeating the process of flight mode followed by ground-charging mode in a pattern similar to a frog resting on a lily pad perhaps catching a fly as it makes its way across a pond.

National Aeronautics and Space Administration

www.nasa.gov

Computational Fluid Dynamics (CFD) examinations illustrated that the presence of the loop wing wind turbines will not interfere significantly with the lifting and directional rotors. The downward mounted motors' downwash do not impinge upon the loop wing nor does the loop wing turbulence affect the motors.

Simulation

National Aeronautics and Space Administration

www.nasa.gov

H-Frame quadrotor was chosen for mountable area.

Proof-of-concept designed with Rhino 3D CAD software

Concept model dimensions: 24" x 36" with a top deck area of 144 square inches

Proof of Concept

National Aeronautics and Space Administration

www.nasa.gov

Dr. William Warmbrodt - NASA, Aeromechanics Branch ChiefLarry Young - NASA, Aeromechanics Branch design EngineerNeeda Lin - NASA, Mechanical Engineer InternGary Brandt - Northwest Indian College, Native American Research Team Mentor

Acknowledgements

National Aeronautics and Space Administration

www.nasa.gov

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