Development of a Sonic Sensor for Aircraft Applications

Carroll, Jonathan D.

Title:

Development of a Sonic Sensor for Aircraft Applications

dc.contributor.advisor	Ahuja, Krishan K.
dc.contributor.advisor	Sankar, Lakshmi N.
dc.contributor.author	Carroll, Jonathan D.
dc.contributor.committeeMember	Jagoda, Jechiel I.
dc.contributor.committeeMember	Sabra, Karim G.
dc.contributor.committeeMember	Whitlow, Woodrow
dc.contributor.committeeMember	Lang, Randy
dc.contributor.department	Aerospace Engineering
dc.date.accessioned	2022-01-14T16:12:28Z
dc.date.available	2022-01-14T16:12:28Z
dc.date.created	2021-12
dc.date.issued	2021-12-14
dc.date.submitted	December 2021
dc.date.updated	2022-01-14T16:12:28Z
dc.description.abstract	The field of aeroacoustics has been an area of constant research over the past six decades. Acoustic waves have some special characteristics that allow for heating, cooling, and even active flow control over airfoil shapes using synthetic jets and other methods. They can also be used to measure properties of the flow over an aircraft, including the free-stream pressure ratio, density ratio, and total temperature. The current measurement techniques to obtain these parameters applied to aircraft require a specific probe. It is desired to apply knowledge of acoustics to develop an aircraft sensor that can measure multiple flow properties with minimal impact to the flow field. Adding a sensor that can read total temperature, static temperature, airspeed, and angle of attack will have the added benefit of reducing the number of sensors sticking into the flow and may result in a reduction in failure mode analysis due to the minimization of the number of sensors on the aircraft. This work explores the applicability of sonic anemometry to aircraft for high subsonic and sonic speeds. A computational simulation is developed as a validation of the concept and low speed experiments are shown to validate the theory. This effort identifies the underlying issues associated with applying sonic anemometry to high-speed flows and provides methods to overcome them. This work investigates the use of phased array technology to increase the accuracy and applicability at the higher speeds and smaller footprints (lighter and fewer systems). Phased arrays use the constructive and destructive interference to boost and direct the desired signal, in this case, acoustic waves. These acoustic waves have been shown to provide haptic feedback and levitate small particles utilizing a relatively inexpensive ultrasonic phased array system. It is shown that the ultrasonic phased array overcomes the hydrodynamic noise to produce a strong signal for use in the calculation of the flow parameters up to the maximum speed tested. It is also shown that the signal is strong enough to produce consistent time delay estimations, via cross-correlation, with a 0.05 second sample time to integrate into modern air data systems.
dc.description.degree	Ph.D.
dc.format.mimetype	application/pdf
dc.identifier.uri	http://hdl.handle.net/1853/66150
dc.language.iso	en_US
dc.publisher	Georgia Institute of Technology
dc.subject	Sonic Sensor
dc.subject	cross-correlation
dc.subject	ultrasonic anemometer
dc.subject	phased array
dc.subject	acoustics
dc.title	Development of a Sonic Sensor for Aircraft Applications
dc.type	Text
dc.type.genre	Dissertation
dspace.entity.type	Publication
local.contributor.advisor	Sankar, Lakshmi N.
local.contributor.advisor	Ahuja, Krishan K.
local.contributor.corporatename	College of Engineering
local.contributor.corporatename	Daniel Guggenheim School of Aerospace Engineering
local.relation.ispartofseries	Doctor of Philosophy with a Major in Aerospace Engineering
relation.isAdvisorOfPublication	22a68276-4f0c-499c-9dd9-931e34bf40a8
relation.isAdvisorOfPublication	22e5838d-630c-400b-bee3-4ddf9759b86d
relation.isOrgUnitOfPublication	7c022d60-21d5-497c-b552-95e489a06569
relation.isOrgUnitOfPublication	a348b767-ea7e-4789-af1f-1f1d5925fb65
relation.isSeriesOfPublication	f6a932db-1cde-43b5-bcab-bf573da55ed6
thesis.degree.level	Doctoral