초록 ▼

A single dielectric barrier aerodynamic plasma actuator apparatus based on the dielectric barrier discharge phenomenon is disclosed and suggested for application to aerodynamic uses for drag reduction, stall elimination and airfoil efficiency improvement. In the plasma actuator apparatus non-uniform

A single dielectric barrier aerodynamic plasma actuator apparatus based on the dielectric barrier discharge phenomenon is disclosed and suggested for application to aerodynamic uses for drag reduction, stall elimination and airfoil efficiency improvement. In the plasma actuator apparatus non-uniform in time and space, partially ionized gasses are generated by one or more electrode pairs each having one electrically encapsulated electrode and one air stream exposed electrode and energization by a high-voltage alternating current waveform. The influence of electrical waveform variation, electrode polarity, electrode size and electrode shape on the achieved plasma are considered along with theoretical verification of achieved results. Light output, generated thrust, ionizing current waveform and magnitude and other variables are considered. Misconceptions prevailing in the present day plasma generation art are addressed and are believed-to-be corrected. The influence of electrostatic shielding effects of the developed plasma on the applied electric field are also considered.

대표청구항 ▼

We claim: 1. Air vehicle dielectric barrier aerodynamic plasma actuator apparatus comprising the combination of: an aerodynamic vehicle having a vehicle airfoil component disposed in a moving air location thereof; a first dielectric barrier discharge electrical conductor element surrounded by an el

We claim: 1. Air vehicle dielectric barrier aerodynamic plasma actuator apparatus comprising the combination of: an aerodynamic vehicle having a vehicle airfoil component disposed in a moving air location thereof; a first dielectric barrier discharge electrical conductor element surrounded by an electrically insulating dielectric barrier enclosure member and disposed in a selected position on said aerodynamic vehicle component in said moving air location; a second dielectric barrier discharge electrical conductor element located proximate said electrically insulating dielectric barrier enclosure member and said first electrical conductor element in said selected position of said moving air location of said vehicle; and a source of dielectric barrier discharge alternating current electrical energy of kilovolt peak electrical potential connected between said first and second electrical conductor elements; said first dielectric barrier discharge electrical conductor element, said second dielectric barrier discharge electrical conductor element and said source of dielectric barrier discharge alternating current electrical energy comprising a gaseous plasma generating dielectric barrier discharge portion of said aerodynamic vehicle airfoil; said gaseous plasma generating dielectric barrier discharge device portion of said aerodynamic vehicle enabling one of increased thrust and diminished drag enhanced aerodynamic performance of said vehicle. 2. The air vehicle dielectric barrier aerodynamic plasma actuator apparatus of claim 1 wherein said vehicle airfoil component comprises at least one of an aircraft wing, an aircraft wing flap, an aircraft aileron, an aircraft tail surface, an aircraft engine turbine blade, an aircraft propeller, a helicopter rotor blade and a munitions device. 3. The air vehicle dielectric barrier aerodynamic plasma actuator apparatus of claim 1 wherein said second dielectric barrier discharge electrical conductor element is a bare, air exposed, conductor. 4. The air vehicle dielectric barrier aerodynamic plasma actuator apparatus of claim 3 wherein said second dielectric barrier discharge electrical conductor element has thickness and width dimensions less than a thickness dimension of said first electrical conductor element and less than a thickness dimension of said electrically insulating dielectric barrier enclosure member. 5. The air vehicle dielectric barrier aerodynamic plasma actuator apparatus of claim 1 wherein said source of dielectric barrier discharge alternating current electrical energy of kilovolt peak electrical potential includes a voltage waveform having one of a sawtooth and a triangular waveform shape. 6. The air vehicle dielectric barrier aerodynamic plasma actuator apparatus of claim 1 wherein said source of dielectric barrier discharge alternating current electrical energy of kilovolt peak electrical potential is connected with said electrodes to provide said first electrode with a negatively increasing electrical potential with respect to said second electrode over a majority of an alternating current voltage waveform cycle. 7. The air vehicle dielectric barrier aerodynamic plasma actuator apparatus of claim 1 wherein said source of dielectric barrier discharge alternating current electrical energy of kilovolt peak electrical potential is connected with said electrodes to provide said first electrode with a positively increasing electrical potential with respect to said second electrode over a majority of an alternating current voltage waveform cycle. 8. The air vehicle dielectric barrier aerodynamic plasma actuator apparatus of claim 1 wherein said apparatus is characterized by a nonlinear relationship between generated aerodynamic force and peak electrical potential of said source of dielectric barrier discharge alternating current electrical energy. 9. The air vehicle dielectric barrier aerodynamic plasma actuator apparatus of claim 1 wherein said apparatus is characterized by one of: a (voltage)7/2 relationship between dissipated electrical power and peak electrical potential of said source of dielectric barrier discharge alternating current electrical energy, and a (voltage)7/2 relationship between generated plasma velocity and peak electrical potential of said source of dielectric barrier discharge alternating current electrical energy. 10. The air vehicle dielectric barrier aerodynamic plasma actuator apparatus of claim 1 wherein said aerodynamic vehicle airfoil component includes a plurality of said aerodynamic plasma actuator apparatus combinations. 11. The dielectric barrier discharge method of improving airfoil airflow characteristics of an aerodynamic vehicle component element, said method comprising the steps of: disposing along an airfoil flow surface of said aerodynamic vehicle component element a plasma film generating electrical discharge supporting electrode array having an extended electrode dimension generally orthogonal of airflow across said airfoil airflow surface; providing in said electrical discharge supporting electrode array a first dielectric barrier enclosure-surrounded electrode conductor and an overlying, adjacent, laterally displaced, second airflow exposed electrode conductor; growing a filamented, light-emitting, time dependent dielectric barrier discharge plasma film over a first electrode conductor-adjacent surface of said dielectric barrier enclosure; said time dependent growing plasma film extending in a direction determined by relative positioning of said first electrode conductor and said second electrode conductor on said airfoil-airflow surface and extending over a time dependent distance of said dielectric barrier enclosure; said growing step including energizing said second airfoil airflow exposed electrode conductor with a source of alternating current electrical energy of kilovolt peak electrical potential with respect to said first dielectric barrier-surrounded electrode conductor; and selecting a dielectric barrier plasma film enhancing alternating current electrical energy voltage waveform of relatively slow voltage change in one polarity direction and relatively fast voltage change in opposed polarity direction for said source of alternating current electrical energy of kilovolt peak electrical potential; said energized electrical discharge supporting array generating a plasma directed momentum influenced improved pattern of air flow across said aerodynamic vehicle component element airfoil airflow surface. 12. The dielectric barrier discharge method of improving airfoil airflow characteristics of an aerodynamic vehicle component element of claim 11 wherein said time dependent plasma film extends in a direction parallel with said airflow across said airfoil airflow surface; said time dependent growing plasma film extending in a direction determined by relative positioning of said first electrode conductor and said second electrode conductor on said airfoil airflow surface and extending over a time dependent distance of said dielectric barrier enclosure. 13. The dielectric barrier discharge method of improving airfoil airflow characteristics of an aerodynamic vehicle component element of claim 11 wherein said step of energizing said second airflow exposed electrode conductor with a source of alternating current electrical energy of kilovolt peak electrical potential with respect to said first dielectric barrier-surrounded electrode conductor and said waveform of relatively slow voltage change in one polarity direction and relatively fast voltage change in opposed polarity direction comprise energizing said conductors with alternating current energy of sawtooth voltage waveform. 14. The dielectric barrier discharge method of improving airfoil airflow characteristics of an aerodynamic vehicle component element of claim 11 wherein said filamented-light-emitting, time dependent dielectric barrier discharge plasma film includes an irregular and growing film boundary opposite a linear initial starting location proximate one of said electrodes. 15. The dielectric barrier discharge method of improving airfoil airflow characteristics of an aerodynamic vehicle component element of claim 11 wherein said dielectric barrier plasma film enhancing alternating current electrical energy voltage waveform comprises one of a sawtooth and a triangular voltage waveform. 16. Aircraft airfoil directed momentum single dielectric barrier aerodynamic plasma actuator apparatus comprising the combination of: an exposed dielectric barrier discharge first electrode member located in a first location of an airflow stream across an aerodynamic airfoil element of said aircraft; a dielectric barrier-surrounded and enclosed second electrode member located in an adjacent but displaced second downstream location of said aircraft aerodynamic airfoil element with respect to said first electrode member; and a source of plasma generation-efficient waveform alternating current electrical energy of kilovolt peak electrical potential connected between said first and second airfoil electrode members; said dielectric barrier discharge first electrode member and said dielectric barrier surrounded second electrode member being disposed adjacent a point of airflow separation of said airfoil. 17. The aircraft airfoil dielectric barrier aerodynamic plasma actuator apparatus of claim 16 wherein said airfoil comprises one of a wing, a tail and a force generating element of said aircraft. 18. The aircraft airfoil dielectric barrier aerodynamic plasma actuator apparatus of claim 16 wherein said directed momentum dielectric barrier discharge aerodynamic plasma actuator apparatus is disposed adjacent one of a leading edge and a trailing edge of said airfoil. 19. The method of generating airfoil aerodynamic performance enhancing time segregated bursts of filamentary single dielectric barrier discharge ionized gas plasma adjacent an airfoil airflow surface of an airborne vehicle component, said method comprising the steps of: energizing a pair of airborne vehicle airfoil airflow surface mounted electrodes with alternating current electrical energy of kilovolt electrical potential and selected voltage waveform; said pair of airborne vehicle airfoil airflow surface mounted electrodes including a first dielectric barrier-surrounded and enclosed electrode and an adjacent second, airfoil airflow exposed bare conductor, electrode displaced upstream along said airfoil airflow from said first electrode; said selected voltage waveform including first and second portions of selected electrode polarity, frequency and waveform rate of voltage change; and selecting separation dimension, airfoil airflow surface position, shape and cross sectional physical attributes of said first and second electrodes and said dielectric barrier and magnitude of said kilovolt electrical potential in response to desired dielectric barrier discharge characteristics of said generated ionized gas plasma adjacent said airfoil airflow surface. 20. The method of generating airfoil aerodynamic performance enhancing time segregated bursts of filamentary dielectric barrier discharge ionized gas plasma of claim 19 wherein said selecting step includes disposing said pair of airborne vehicle flow surface electrodes adjacent a point of airflow separation on said airfoil airflow surface. 21. The method of generating airfoil aerodynamic performance enhancing time segregated bursts of filamentary dielectric barrier discharge ionized gas plasma of claim 19 wherein said selecting step includes disposing said pair of electrodes adjacent one of a leading edge and a trailing edge of an airflow surface of said airfoil. 22. The method of generating airfoil aerodynamic performance enhancing time segregated bursts of filamentary dielectric barrier discharge ionized gas plasma of claim 19 wherein said step of selecting includes enhancing performance of said airborne vehicle airflow surface mounted electrodes by minimizing a thickness dimension of said airfoil airflow exposed bare conductor electrode. 23. The method of generating airfoil aerodynamic performance enhancing time segregated bursts of filamentary dielectric barrier discharge ionized gas plasma of claim 19 wherein said selecting step includes choosing an electrical breakdown immune thickness dimension of said dielectric barrier in response to an elected magnitude of said kilovolt electrical potential. 24. The method of generating airfoil aerodynamic performance enhancing time segregated bursts of filamentary dielectric barrier discharge ionized gas plasma of claim 19 wherein said selecting step includes choosing an optimum length dimension for said dielectric barrier surrounded electrode in response to a selected magnitude of said kilovolt electrical potential.