Your Selections

Unmanned aerial vehicles
Show Only

Collections

File Formats

Content Types

Dates

Sectors

Topics

Authors

Publishers

Affiliations

Committees

Events

Magazine

Series

   This content is not included in your SAE MOBILUS subscription, or you are not logged in.

Numerical Simulation and Optimization for Combustion of an Opposed Piston Two-Stroke Engine for Unmanned Aerial Vehicle (UAV)

Beijing Institute of Technology-Zhenfeng Zhao, Fujun Zhang
Harbin Institute of Technology, Shenzhen-Lei Zhou, Hao Li, Zeyu Chen
  • Technical Paper
  • 2020-01-0782
To be published on 2020-04-14 by SAE International in United States
The opposed-piston two-stroke engine is more suitable for the UAV, due to its smaller size, better self-balancing, stable operation and lower noise. Consequently, in this work, based on the experimental data of a prototype opposed piston two-stroke engine, the numerical simulation model are established by AVL-FIRE. The mesh grid and solver parameters of the numerical model are discussed for guaranteeing the accuracy of numerical simulation, and then the ventilation efficiency of the engine with different dip angles and elevation angles have been studied and optimized. Moreover, the fuel spray process and subsequent combustion as well as NOx emissions have been analyzed in details. Finally, the engine combustion parameters have been optimized by orthogonal test design method.
   This content is not included in your SAE MOBILUS subscription, or you are not logged in.

Design Optimization and Aerodynamic Analysis of a Hybrid Blended Wing Body- VTOL Unmanned Aerial Vehicle

Delhi Technological University-Pranav Bahl, Vikas Rastogi, Amit bainsla, Nitin Sharma
  • Technical Paper
  • 2020-01-0472
To be published on 2020-04-14 by SAE International in United States
Unmanned Aerial Vehicles (UAVs) can be effectively used to serve humanitarian relief efforts during environmental disasters. Designing such UAVs presents challenges in optimizing design variables such as maximizing endurance, maneuverability and payload capacity with minimum launch and recovery area. The Blended Wing Body (BWB) is a novel aircraft configuration offering enhanced performance over conventional UAVs. Designing a blended wing configuration UAV takes into account interdependency between aerodynamic performance and stability. Designing BWB is peculiar and is investigated in this paper with a view to achieve an aerodynamically stable and structurally sound configuration. The designed UAV is a hybrid of a tailless blended-wing-body and a tri-copter configuration with two forward tilt motors for transition into cruise flight after vertical take-off and back to multirotor while landing (VTOL-Vertical Take Off and Landing). The BWB is iteratively optimized in XFLR-5 for Dynamic and static stability. The wing design was optimized for aerodynamic and structural fitness in MATLAB using Meta-heuristic optimization methodology based on genetic evolutionary algorithm. The 3D CAD design was conceived on SolidWorks and analyzed in Pressure…
   This content is not included in your SAE MOBILUS subscription, or you are not logged in.

Extended Endurance Unmanned Aerial Vehicle via Structural Electrical Power Storage and Energy Generation Devices

Geoffrey Smith Oetting
  • Technical Paper
  • 2020-01-0041
To be published on 2020-03-10 by SAE International in United States
As the application of unmanned aerial vehicles (UAV) have increased in the military, commercial and private sectors, special attention has been focused on improving upon high altitude long endurance (HALE) performance. Therefore, under a multi-year, multi-discipline senior project team comprised of Aerospace Engineering, Electrical Engineering, Computer Engineering, Mechanical engineering, and Chemical Engineering undergraduate teams, investigative and experimental research has begun into the substitution of various aircraft structural components with power storage and power generation devices used also as structure to improve flight endurance and performance capabilities of solar powered UAVs. One viable solution may be found in the reduction of the amount of parasitic weight due to the required power systems on board these types of aircraft. These power systems are usually found in the form of energy storage devices such as lithium polymer batteries and energy generation devices such as solar cells. This path led to the innovation of the ‘Flying Battery’. The ‘Flying Battery’ integrates various free energy generating devices such as structural solar cells, structural energy storage devices, thermo-electric generators, and vibration…
   This content is not included in your SAE MOBILUS subscription, or you are not logged in.

Design of Elevons for a Hybrid VTOL-Blended Wing Body Unmanned Aerial Vehicle

Delhi Technological University-Amit Bainsla, Vikas Rastogi, Pranav Bahl
  • Technical Paper
  • 2020-01-0047
To be published on 2020-03-10 by SAE International in United States
The two primary requirements for a safe flight of a UAV are its stability and manoeuvrability. The purpose of this study is to design and validate elevons for a UAV having Blended Wing Body configuration which requires knowledge of various domains applied in a complex combination. Elevons are the unconventional control surfaces for the flying wings which will cause a pitching moment when moved in same direction and will cause a rolling moment when moved differentially and their preliminary design is affected by the function which is dominant. A MATLAB© code was written to decide the position, shape and size of elevons and later on accurately evaluated using high fidelity Computational Fluid Dynamics simulations. The MATLAB© code calculates the required roll time rate taking into consideration the longitudinal and lateral control requirements. Using this coupled approach of MATLAB© code and Computational Fluid Dynamics simulations significant optimization is achieved in designing the elevons.
   This content is not included in your SAE MOBILUS subscription, or you are not logged in.

Performance of Isolated UAV Rotors at Low Reynolds Number

Georgia Institute of Technology-Yashvardhan Tomar, Narayanan Komerath
Indian Institute of Technology-Dhwanil Shukla
  • Technical Paper
  • 2020-01-0046
To be published on 2020-03-10 by SAE International in United States
Vertical takeoff and landing vehicle platforms with many small rotors are gaining importance for small UAVs as well as distributed electric propulsion for larger vehicles. To predict vehicle performance, it must be possible to gauge interaction effects. These rotors operate in the less-known regime of low Reynolds number, with different blade geometry. As a first step, two identical commercial UAV rotors from a flight test program are studied in isolation, experimentally and computationally. Load measurements were performed in Georgia Tech’s 2.13 m × 2.74 m wind tunnel. Simulations were done using the RotCFD solver which uses a Navier-Stokes wake computation along with rotor-disc loads calculation using low-Reynolds number blade section data. It is found that in hover, small rotors available in the market vary noticeably in performance at low rotor speeds, the data converging at higher RPM and Reynolds number. This is indicative of the high sensitivity of low-Re rotor flows to minor geometrical differences/imperfections in the rotors. It requires proper handling in computations. CFD results show a higher deviation from the experimental thrust data…
new

Facility Focus: NASA Goddard Space Flight Center

  • Magazine Article
  • TBMG-35969
Published 2020-02-01 by Tech Briefs Media Group in United States

Dr. Robert Hutchings Goddard is considered the father of modern rocket propulsion. A physicist, Goddard also had a unique genius for invention. It is in his honor that NASA's Goddard Space Flight Center in Greenbelt, MD, was established on May 1, 1959 as NASA's first space flight complex.

new

Automatic Drone Detection System

  • Magazine Article
  • TBMG-36060
Published 2020-02-01 by Tech Briefs Media Group in United States

Tektronix Beaverton, OR 1-800-833-9200

Microrobot Powered by Soft Muscles

  • Magazine Article
  • TBMG-35828
Published 2020-01-01 by Tech Briefs Media Group in United States

Researchers have developed a microrobot called RoboBee powered by soft artificial muscles that can crash into walls, fall onto the floor, and collide with other RoboBees without being damaged. It is the first microrobot powered by soft actuators to achieve controlled flight.

   This content is not included in your SAE MOBILUS subscription, or you are not logged in.

Lighting Applications for Unmanned Aircraft Systems (UAS)

A-20B Exterior Lighting Committee
  • Aerospace Standard
  • ARP6336
  • Current
Published 2019-12-05 by SAE International in United States
This SAE Aerospace Recommended Practice (ARP) provides technical recommendations for the lighting applications for Unmanned Aircraft Systems (UAS). The technical content of this ARP discusses the unique trade-offs that are necessary to maintain commonality to the U.S. Federal Aviation Regulations (FARs)1 for aerospace lighting. The recommendations set forth in this document are to aid in the design of Unmanned Aircraft (UA) lighting for the size of aircraft and operation for which the aircraft is intended. In addition, certain concepts of operation for which UASs are suited will require unique lighting solutions.
This content contains downloadable datasets
Annotation ability available
   This content is not included in your SAE MOBILUS subscription, or you are not logged in.

Guidelines for Writing IVHM Requirements for Aerospace Systems

HM-1 Integrated Vehicle Health Management Committee
  • Aerospace Standard
  • ARP6883
  • Current
Published 2019-12-03 by SAE International in United States
This Aerospace Recommended Practice (ARP) provides guidance on developing requirements for systems that include Integrated Vehicle Health Management (IVHM) capability [REF1], [REF18]. IVHM is increasingly being implemented on military and commercial aircraft. Some examples include the F-35 Joint Strike Fighter (JSF) [REF1] and the AH-64 Apache [REF3] in the military domain, and the B787 [REF4] and A350XWB [REF5] in the commercial domain. This document provides a systematic approach for developing requirements related to the IVHM capabilities of a vehicle system. This document is not intended to repeat general guidelines on good requirements writing [REF13], [REF20]. Instead, the focus is on the unique elements, which need to be considered for IVHM and the resulting specific guidelines that will help define better requirements and hence better systems. The multi-faceted nature of IVHM should include the process of requirements gathering. Therefore, this document presents some guidance on how to go about this task. The document also includes some case studies that illustrate, in a practical manner, what a good set of IVHM requirements might look like. These have…
This content contains downloadable datasets
Annotation ability available