Advanced Search
Journal search
Journal cover: Aircraft Engineering and Aerospace Technology

Aircraft Engineering and Aerospace Technology

ISSN: 0002-2667

Online from: 1929

Subject Area: Mechanical & Materials Engineering

Content: Latest Issue | icon: RSS Latest Issue RSS | Previous Issues


Previous article.Icon: Print.Table of Contents.Next article.Icon: .

Flight demonstrations of micro-actuator controlled delta wing

Document Information:
Title:Flight demonstrations of micro-actuator controlled delta wing
Author(s):John Lee, (University of Arkansas, Fayetteville, Arkansas, USA), Scott Newbern, (AeroVironment, Inc., Monrovia, California, USA), Yu-Chong Tai, (California Institute of Technology, Pasadena, California, USA), Chih-Ming Ho, (University of California, Los Angeles, California, USA), Po-Hao Adam Huang, (University of Arkansas, Fayetteville, Arkansas, USA)
Citation:John Lee, Scott Newbern, Yu-Chong Tai, Chih-Ming Ho, Po-Hao Adam Huang, (2011) "Flight demonstrations of micro-actuator controlled delta wing", Aircraft Engineering and Aerospace Technology, Vol. 83 Iss: 5, pp.324 - 331
Keywords:Flight dynamics, Flight tests, Micro-electro-mechanical systems (MEMS), Remote control systems, Remotely-piloted vehicles, Vortex shift control
Article type:Research paper
DOI:10.1108/00022661111159933 (Permanent URL)
Publisher:Emerald Group Publishing Limited
Acknowledgements:The authors would like to acknowledge the funding agencies for this and associated projects over the past decade plus; they include DARPA MTO, AFOSR, NASA, and ONR. The authors would also like to acknowledge the numerous researchers involved in this project, counting over 30 personnel of all levels and responsibilities. Thank you all for your time and dedication.

Purpose – The goal of this research is to demonstrate micro-electro-mechanical systems (MEMS)-based transducers for aircraft maneuvering. Research in wind tunnels have shown that micro-actuators can be used to manipulate leading edge vortices found on aerodynamic surfaces with moderate to highly swept leading edges, such as a delta wing. This has been labeled as the MEMS vortex shift control (MEMS-VSC). The work presented in this paper seeks to detail the evolution of real-world flight tests of this research using remotely piloted vehicles (RPVs).

Design/methodology/approach – Four different RPVs were constructed and used for flight tests to demonstrate the ability of using MEMS devices to provide flight control, primarily in the rolling axis.

Findings – MEMS devices for high angle-of-attack (AOA) turning flights have been demonstrated and the paper finds that the success of a complex project like the MEMS-VSC requires the marriage of basic science expertise found in academia and the technical expertise found in industry.

Research limitations/implications – Owing to the need to test fly the RPVs at low altitudes for video documentation while performing high AOA maneuvers, the attrition of the RPVs becomes the dominant factor to the pace of research.

Practical implications – MEMS sensors and actuators can be used to augment flight control at high AOA, where conventional control surfaces typically experiences reduced effectiveness. Separately, the lessons learned from the integration efforts of this research provide a potentially near parallel case study to the development of ornithopter-based micro aerial vehicles.

Originality/value – This is the only research-to-date involving the demonstration of the MEMS-VSC on real-world flight vehicles.

Fulltext Options:



Existing customers: login
to access this document


- Forgot password?
- Athens/Institutional login



Downloadable; Printable; Owned
HTML, PDF (1449kb)

Due to our platform migration, pay-per-view is temporarily unavailable.

To purchase this item please login or register.


- Forgot password?

Recommend to your librarian

Complete and print this form to request this document from your librarian

Marked list

Bookmark & share

Reprints & permissions