Thrust Force Analysis of a Rotating Ionocraft Under

Thrust Force Analysis of a Rotating Ionocraft Under High Voltage
Author: Rae-Zan Belen
Faculty Advisor: Hervé Collin, Ph.D.
Kapi‘olani Community College, Honolulu, Hawai‘i
Introduction
In the early 1920s, Brown and Biefeld [1] [2] discovered that when a very high voltage
is applied to an asymmetric capacitor, a force is produced parallel to the electrodes
and causes a thrust in the direction of the positive one. Modifying the geometry of the
asymmetric capacitor results in a lightweight ionocraft or “lifter,” that may represent a
candidate for an alternative novel propulsion system with no moving parts. The
potential of this ionocraft to revolutionize future transports with a novel technology has
piqued the interest of the US Army [3], [4], the US Navy [5], NASA [6], as well as
private companies such as the Honda Corporation [7].
Since the discovery of this thrust force in the nineteen twenties, its origin has been
highly speculated upon, and is still poorly understood. There have been several
theories proposed to predict the magnitude and origin of this force. The leading theory
involves the ionic wind effect (Biefeld-Brown), which describes the polarization of air
molecules as the source of propulsion. Other speculative theories also include
electrogravitics, which consider antigravity as a possible source. None of these
theories however are able to predict the correct magnitude of the thrust force (three
order of magnitude lower) [3]. An additional difficulty arises when attempting to
experimentally measure the thrust force through kinematic variables due to the high
variation of motion of the ionocraft’s lift. If the kinematic variables prove to be a
reliable method to infer the dynamics of the system, it is essential to control its
motion. Therefore, in this experiment, we decided to constraint the ionocraft into a
controlled rotational configuration in order to analyze the ionocraft’s motion on a fixed
flight path.
Sequence of data acquisition
1)Frictional force
Figure 1: Nonlinear Regression using
Figure 2: Nonlinear Regression using
2) Powered system
Figure 3: Linear Regression using Equation (1)
Figure 2: Experimental setup
A nonlinear regression was performed again between the above equation and the
experimental data of our powered system to adjust the optimum value of the thrust
force F in order to obtained the best possible fit.
Figure 1: Design of the ionocraft rotating setup
References:
[1] Brown, Thomas T.. “How I Control Gravity”. Science and Invention. August 1929.
[2] Brown, Thomas T. “Electrokinetic Apparatus”. “U.S. Patent No. 2,949,550’. August 16,1960.
[3] Bahder ,Thomas B. & Chris Fozi, “Force on an Asymmetric Capacitor,” Army Research Laboratory, March 2003
[4] Miller,William M., Paul B. Miller, Timothy J Drummond., “Force Characteristics of Asymmetrical Capacitor Thrusters in Air,” Army Research Lab-TR-3005, Dec 2002
[5] United State Department of Labor, “Ozone Chemical Sampling Information” http://www.osha.gov/dts/chemicalsampling/data/CH_259300.html
[6] “Is ablation responsible for Asymmetric Capacitor Thrust in Vacuum?,” Proposal by Quantum Potential Corporation in response to 2011 NASA SBIR Solicitation, Web pdf
[7] Martins, Alexandre A., “Modeling of an EHD Corona Flow in Nitrogen Gas Using an Asymmetric Capacitor for Propulsion,” Journal of Electrostatics, Vol 69, Issue 2, 133–138, April 2011
Acknowledgements:
I would like to acknowledge the National Science Foundation for the funding they have provided to support my research, my
advisor Dr. Hervé Collin, our STEM Coordinator Mrs. Keolani Noa, the Kapi`olani Community College STEM Program, Logan
Tamayo, Michelle Chu, James Bynes, and Lisa Kotowski. Much mahalo to my family and friends for their support towards the
completion of this project.