scholarly journals Design and Test of Portable Hyperspectral Imaging Spectrometer

2017 ◽  
Vol 2017 ◽  
pp. 1-9 ◽  
Author(s):  
Chunbo Zou ◽  
Jianfeng Yang ◽  
Dengshan Wu ◽  
Qiang Zhao ◽  
Yuquan Gan ◽  
...  
Keyword(s):  
Hyperspectral Imaging ◽  
High Performance ◽  
Small Volume ◽  
High Spatial Resolution ◽  
Flight Test ◽  
High Spectral Resolution ◽  
Imaging Spectrometer ◽  
Low Weight ◽  
Aerial Vehicle ◽  
Small Platform

We design and implement a portable hyperspectral imaging spectrometer, which has high spectral resolution, high spatial resolution, small volume, and low weight. The flight test has been conducted, and the hyperspectral images are acquired successfully. To achieve high performance, small volume, and regular appearance, an improved Dyson structure is designed and used in the hyperspectral imaging spectrometer. The hyperspectral imaging spectrometer is suitable for the small platform such as CubeSat and UAV (unmanned aerial vehicle), and it is also convenient to use for hyperspectral imaging acquiring in the laboratory and the field.

Design, Fabrication and Flight Testing of a Surveillance UAV

2015 ◽  
Vol 1115 ◽  
pp. 450-453 ◽  
Author(s):  
Moumen Idres ◽  
Burhani Makame ◽  
Bala Nabil Ahmad ◽  
Saleh Naji ◽  
Ahmad Safiuddin
Keyword(s):  
Design Process ◽  
Low Cost ◽  
Flight Test ◽  
Wing Loading ◽  
Rescue Operation ◽  
Low Weight ◽  
Carbon Rods ◽  
Power Loading ◽  
Final Design ◽  
Aerial Vehicle

Unmanned Aerial Vehicle (UAV) is becoming increasingly popular because it can perform variety of functions. These functions include surveillance, reconnaissance, monitoring, data collection and rescue operation. The purpose of this work is to design, fabricate and fly a low weight, low cost, small size UAV for a surveillance mission. The design is carried out based on Advanced Aircraft Analysis (AAA) software. The design process starts with the design specifications for a typical surveillance mission. Aircraft weight, wing loading and power loading were estimated in performance sizing process. Geometry was estimated using preliminary sizing. Aerodynamics of the aircraft was determined, which enabled the performance and stability to be analysed. If the desired performance is not achieved, the sizing is readjusted until a final design is reached. The aircraft was manufactured using foam, carbon rods, and fibreglass. The aircraft successfully flew at the first trial flight. This was followed by a successful flight with aerial photography. Keywords: UAV, design process, fabrication process, composite structure, flight test

Measurement accuracy and Cerenkov removal for high performance, high spatial resolution scintillation dosimetry

2005 ◽  
Vol 33 (1) ◽  
pp. 128-135 ◽  
Author(s):  
Louis Archambault ◽  
A. Sam Beddar ◽  
Luc Gingras ◽  
René Roy ◽  
Luc Beaulieu
Keyword(s):  
Spatial Resolution ◽  
High Performance ◽  
Measurement Accuracy ◽  
High Spatial Resolution

An Analytical Comparison Between Ball and Crossed Roller Bearings for Utilization in Actuator Modules for Precision Modular Robots

2003 ◽  
Author(s):  
Seong-Ho Kang ◽  
Delbert Tesar
Keyword(s):  
High Performance ◽  
Background Information ◽  
Modular Robots ◽  
Extensive Literature ◽  
Positional Accuracy ◽  
Precision Engineering ◽  
Friction Cost ◽  
Low Weight ◽  
Bearing Stiffness ◽  
Robot Configurations

A modular robot system is a collection of actuators, links, and connections that can be arbitrarily assembled into a number of different robot configurations and sequences. High performance modular robots require more than just sophisticated controls. They also need top-quality mechanical components. Bearings in particular must operate well at low speed, have high rotational accuracy, be compact for low weight, and especially be stiff for high positional accuracy. To ensure the successful use of bearings in precision modular robots, knowledge of the bearing properties and requirements are investigated. Background information on various topics such as modular robots, precision modular actuators, and their error sources are described with respect to precision engineering. Extensive literature on thin section bearings is reviewed to examine their use in precision robotic applications. Theoretical studies are performed to calculate bearing stiffness adopting a methodology based on Hertzian theory. This approach is applied to analyze two proposed designs of equivalent-sized crossed roller and four-point bearings, principal bearings used for transmitting all the payload and mass of the robot structure. The maximum deflections and contact stresses for the proposed actuator assembly and loading conditions are estimated and compared including a range of general bearing properties such as friction, cost, and shock resistance.

Sine-Wave Exciting Circuit for Quartz Vibrating Gyroscope

2013 ◽  
Vol 562-565 ◽  
pp. 417-420
Author(s):  
Qing Yi Wang ◽  
Xiao Wei Liu ◽  
Rui Zhang ◽  
Liang Yin ◽  
Zhi Ping Zhou
Keyword(s):  
High Performance ◽  
Small Volume ◽  
Angular Rate ◽  
Sine Wave ◽  
Processing Technology ◽  
Angular Rate Sensor ◽  
Square Wave ◽  
Rate Sensor ◽  
Is Design ◽  
Cmos Processing

Quartz vibrating gyroscope is a kind of angular rate sensor which is the compromise between the high performance and the small volume. Improvement of the performance is a focus of reach. In this paper, a sine-wave exciting method is discussed. A sine-wave exciting circuit is design and processed with 0.5μm CMOS processing technology. During comparing the sine-wave exciting response and the square-wave one, the sine-wave exciting circuit is more beneficial to improve the performance of the quartz vibrating gyroscope.

scholarly journals Aerodynamic Analysis of Blended Wing Body - Unmanned Aerial Vehicle (BWB-UAV) Equipped with Horizontal Stabilizers

2019 ◽  
Vol 256 ◽  
pp. 02004
Author(s):  
Nornashiha Mohd Saad ◽  
Wirachman Wisnoe ◽  
Rizal Effendy Mohd Nasir ◽  
Zurriati Mohd Ali ◽  
Ehan Sabah Shukri Askari
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Cfd Simulation ◽  
Lift Coefficient ◽  
Angle Of Attack ◽  
Flight Test ◽  
Longitudinal Direction ◽  
Static Stability ◽  
Pitching Moment ◽  
Aerial Vehicle ◽  
Blended Wing Body

This paper presents an aerodynamic characteristic study in longitudinal direction of UiTM Blended Wing Body-Unmanned Aerial Vehicle Prototype (BWB-UAV Prototype) equipped with horizontal stabilizers. Flight tests have been conducted and as the result, BWB experienced overturning condition at certain angle of attack. Horizontal stabilizer was added at different location and size to overcome the issue during the flight test. Therefore, Computational Fluid Dynamics (CFD) analysis is performed at different configuration of horizontal stabilizer using Spalart - Allmaras as a turbulence model. CFD simulation of the aircraft is conducted at Mach number 0.06 or v = 20 m/s at various angle of attack, α. The data of lift coefficient (CL), drag coefficient (CD), and pitching moment coefficient (CM) is obtained from the simulations. The data is represented in curves against angle of attack to measure the performance of BWB prototype with horizontal stabilizer. From the simulation, configuration with far distance and large horizontal stabilizer gives steeper negative pitching moment slope indicating better static stability of the aircraft.

Design of the I-BoomCopter UAV for Remote Sensor Mounting

2017 ◽  
Author(s):  
Daniel R. McArthur ◽  
Arindam B. Chowdhury ◽  
David J. Cappelleri
Keyword(s):  
Flight Test ◽  
Force Sensor ◽  
Vertical Surface ◽  
End Effector ◽  
Autonomous Sensor ◽  
Remote Sensor ◽  
Line Force ◽  
Aerial Vehicle ◽  
Sensor Package ◽  
Reverse Thrust

This paper presents the design of the Interacting-BoomCopter (I-BoomCopter) unmanned aerial vehicle (UAV) for mounting a remote sensor package on a vertical surface. Critical to the design is the novel, custom, light-weight passive end-effector. The end-effector has a forward-facing sonar sensor and in-line force sensor to enable autonomous sensor mounting tasks. The I-BoomCopter’s front boom is equipped with a horizontally-mounted propeller which can provide forward and reverse thrust with zero roll and pitch angles. The design and modeling of the updated I-BoomCopter platform is presented along with prototype flight test results. A teleoperated wireless camera sensor mounting task examines the updated platform’s suitability for mounting remote sensor packages.

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