Modeling of Dive Maneuvers for Executing Autonomous Dives With a Flapping Wing Air Vehicle

2017 ◽  
Vol 9 (6) ◽  
Author(s):  
Luke J. Roberts ◽  
Hugh A. Bruck ◽  
S. K. Gupta
Keyword(s):  
Computational Model ◽  
Operation Mode ◽  
Open Loop ◽  
Flapping Wing ◽  
Minimal Amount ◽  
University Of Maryland ◽  
Roll Control ◽  
Wind Speeds ◽  
Air Vehicle ◽  
The University

This paper is focused on design of dive maneuvers that can be performed outdoors on flapping wing air vehicles (FWAVs) with a minimal amount of on-board computing capability. We present a simple computational model that provides accuracy of 5 m in open loop operation mode for outdoor dives under wind speeds of up to 3 m/s. This model is executed using a low power, on-board processor. We have also demonstrated that the platform can independently execute roll control through tail positioning, and dive control through wing positioning to produce safe dive behaviors. These capabilities were used to successfully demonstrate autonomous dive maneuvers on the Robo Raven platform developed at the University of Maryland.

Performance Characterization of Multifunctional Wings With Integrated Solar Cells for Unmanned Air Vehicles

2014 ◽  
Author(s):  
Ariel Perez-Rosado ◽  
Adrian G. J. Griesinger ◽  
Hugh A. Bruck ◽  
Satyandra K. Gupta
Keyword(s):  
Solar Cells ◽  
Flapping Wing ◽  
Image Correlation ◽  
Unmanned Air Vehicles ◽  
University Of Maryland ◽  
Battery Power ◽  
Cell Test ◽  
The University ◽  
Air Vehicles

Flapping wing unmanned air vehicles (UAVs) are small light weight vehicles that typically have short flight times due to the small size of the batteries that are used to power them. During longer missions, the batteries must be recharged. The lack of nearby electrical outlets severely limits the locations and types of missions that these UAVs can be flown in. To improve flight time and eliminate the need for electrical outlets, solar cells can be used to harvest energy and charge/power the UAV. Robo Raven III, a flapping wing UAV, was developed at the University of Maryland and consists of wings with integrated solar cells. This paper aims to investigate how the addition of solar cells affects the UAV. The changes in performance are quantified and compared using a load cell test as well as Digital Image Correlation (DIC). The UAV platform reported in this paper was the first flapping wing robotic bird that flew using energy harvested from on-board solar cells. Experimentally, the power from the solar cells was used to augment battery power and increase operational time.

Design, analysis and experimental validation of a morphing UAV wing

2011 ◽  
Vol 115 (1174) ◽  
pp. 761-765 ◽  
Author(s):  
M. Bolinches ◽  
A. J. Keane ◽  
A. I. J. Forrester ◽  
J. P. Scanlan ◽  
K. Takeda
Keyword(s):  
Structural Design ◽  
Experimental Validation ◽  
3D Printer ◽  
Hot Wire ◽  
Polystyrene Foam ◽  
Element Analysis ◽  
Roll Control ◽  
Unmanned Air Vehicle ◽  
Air Vehicle ◽  
The University

Abstract The design of wings with morphing capabilities is known to give aerodynamic benefits. These aero-dynamic benefits come from both the use of hinge-less surfaces and the greater adaptability to flight conditions. This paper describes the structural design of a twisting wing to be used for an unmanned air vehicle (UAV) and presents finite element analysis and experiment results. This is part of a research project carried out at the University of Southampton in which one of the goals is to compare different novel wing designs and technologies to determine which one of them gives the best performance. The twisting capability provides roll control without hinged surfaces hence providing aerodynamic improvement. The wing is manufactured using polystyrene foam and is cut out of block of this material using a hot wire machine. In order to link this foam structure to a main spar, ABS plastic inserts were manufactured using a 3D printer. The mechanisms used to actuate the wing are also made from this material. A full scale UAV wing has been manufactured and tested in order to compare with FEA results.

Horizontal Planform Morphing Tail for an Avian Inspired UAV Using Shape Memory Alloys

2018 ◽  
Author(s):  
Kevin P. T. Haughn ◽  
Lawren L. Gamble ◽  
Daniel J. Inman
Keyword(s):  
Shape Memory ◽  
Structural Integrity ◽  
Large Strain ◽  
Bottom Layer ◽  
Open Loop ◽  
Control Surface ◽  
Wind Speeds ◽  
3D Printed ◽  
The University ◽  
Horizontal Control

Unlike most modern aircraft, which have a vertical tail component, birds fly utilizing a purely horizontal tail. In order to provide control normally associated with a vertical rudder, bird’s tails are incredibly mobile, twisting, pitching, and widening to perform necessary aerial maneuvers. This research primarily focuses on the development and testing of a mechanical planform morphing horizontal control surface, aiming to emulate the tail-spread control action of birds. This horizontal control surface is implemented on a small, tailless, avian inspired unmanned aerial vehicle (UAV). In this research, the horizontal control surface, made entirely of 3D printed material, comprises a rigid overlapping top layer held together by a soft and elastic honeycomb bottom layer, allowing for shape morphing without compromising structural integrity required to withstand aerodynamic forces. Using the relatively large strain and strength offered by shape memory alloy (SMA) springs, the 3D printed horizontal tail undergoes a notable and consistent geometric change. To quantify the system’s performance, the tail width and center was measured while actuating the springs through a range of frequencies from 0.01 to 10 Hz. Preliminary experiments were conducted in a 1ft. × 1 ft. open loop wind tunnel at the University of Michigan at wind speeds of 5, 10 and 15 m/s to quantify the effects of aerodynamic loading on actuation magnitude and speed.

Design of Propeller-Assisted Flapping Wing Air Vehicles for Enhanced Aerodynamic Performance

2015 ◽  
Author(s):  
Alex E. Holness ◽  
Hugh Bruck ◽  
S. K. Gupta
Keyword(s):  
Degrees Of Freedom ◽  
Aerodynamic Performance ◽  
Hybrid Vehicles ◽  
Biologically Inspired ◽  
University Of Maryland ◽  
Maryland College ◽  
Air Vehicle ◽  
Aircraft Performance ◽  
College Park ◽  
The University

Flapping flight is impressive because aerodynamic performance increases whereas fixed wing aircraft performance declines in low Reynolds regimes. In order to achieve biologically-inspired flapping, motion in multiple degrees of freedom is required and power density requirements must be satisfied. Given the mass of high output actuators, weight is a key limitation as it must be offset for flight. In light of this, only recently, with developments in motor technology, has independent wing control been achieved with consumer available components. Due to power demands, motor bandwidth is used largely to sustain flight, limiting the effect of wing independence. An interesting paradigm is one where the aerodynamic flight advantages of propeller-driven flight are utilized in addition to those of flapping wings to allow hybrid vehicles that can occupy unique operational bandwidth. In this work, a propeller-assisted version of Robo Raven, a miniature independent wing flapping air vehicle developed at the University of Maryland College Park, is presented. Having successfully flown with propeller assistance and having demonstrated improved force generation for aerodynamic performance over flapping alone, this modified Robo Raven will constitute the next major iteration of the vehicle as Robo Raven V.

Enhancing the Design of Solar-Powered Flapping Wing Air Vehicles Using Multifunctional Structural Components

2015 ◽  
Author(s):  
Ariel Perez-Rosado ◽  
Hugh A. Bruck ◽  
Satyandra K. Gupta
Keyword(s):  
Solar Cells ◽  
Flight Time ◽  
Flapping Wing ◽  
The Body ◽  
Flight Performance ◽  
Structural Components ◽  
University Of Maryland ◽  
The Difference ◽  
Solar Powered ◽  
The University

Flapping wing aerial vehicles (FWAVs) are limited to small batteries due to constraints on the available onboard payload. To increase the energy available for the vehicle, solar cells can be integrated to harvest energy during flight. This addition of available onboard energy increases the flight time of the vehicle and could eventually lead to an infinite flight as long as there is sunlight. However, integration of solar cells is expected to alter flight performance. The changes in performance must be measured and understood. Previously, solar cells have been integrated to the wings of Robo Raven III, a FWAV developed at the University of Maryland. Changes in flight performance were observed, but ultimately the vehicle was still able to maintain flight and an increase in flight time was observed. This paper extends the previous work and further integrates solar cells to the body and tail of the FWAV. Different tail designs were built and the change in performance caused by the difference in each tail was measured and compared. The new FWAV generated 1.8W more than the previous Robo Raven IIIv2 design. The best tail design has provided the longest operational flight time so far and is known as Robo Raven IIIv3. This new platform benefited from an improved tail design and carried 13g more than the original Robo Raven III tail, despite an increase in vehicle mass.

Design and Fabrication of an SU-8 Biomimetic Flapping-wing Micro Air Vehicle by MEMS Technology

ROBOT ◽  
2011 ◽  
Vol 33 (3) ◽  
pp. 366-370 ◽  
Author(s):  
Pengcheng CHI ◽  
Weiping ZHANG ◽  
Wenyuan CHEN ◽  
Hongyi LI ◽  
Kun MENG ◽  
...  
Keyword(s):  
Flapping Wing ◽  
Micro Air Vehicle ◽  
Air Vehicle ◽  
Mems Technology
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