MEMS PLASMA-AKTUATOREN ZUR ANWENDUNG AUF KLEINDROHNEN
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1 MEMS PLASMA-AKTUATOREN ZUR ANWENDUNG AUF KLEINDROHNEN Berkant Göksel Voltastr Berlin Phased Plasma Actuators Workshop zum Thema Unbemannte Flugzeuge EADS Military Air Systems Manching, 31. Mai und 1. Juni 2006 Quelle: DGLR B. Abteilung/Name Göksel MEMS Plasma Actuators Projektname
2 MEMS PLASMA-AKTUATOREN ZUR ANWENDUNG AUF KLEINDROHNEN List of Contents MEMS Plasma Actuators for Separation Flow Control MEMS Plasma Actuators for Wave Propulsion Conclusion and Outlook Phased Plasma Actuators Quelle: DGLR B. Abteilung/Name Göksel MEMS Plasma Actuators Projektname
3 FOR SEPARATION FLOW CONTROL Eppler E338 Airfoil in Wind Tunnel Tests Run at 20,000 < Re < 140,000 Pulsing by Modulating High Frequency Plasma Excitation Voltage (4 khz, 10 kv p-p) MEMS Fabricated Dielectric Barrier Discharge Actuator (100 µm Kapton) B. Abteilung/Name Göksel MEMS Plasma Actuators Projektname
4 FOR SEPARATION FLOW CONTROL Eppler E338 Airfoil in Wind Tunnel Tests Run at 20,000 < Re < 140,000 Pulsing by Modulating High Frequency Plasma Excitation Voltage (4 khz, 10 kv p-p) Pulsing at Strouhal Number (f*c/u) F + =1 and Duty Cycles from 1 to 100% MEMS Fabricated Dielectric Barrier Discharge Actuator (100 µm Kapton) Actuator Calibration Using Two-Component Laser Doppler Velocimetry (LDV) B. Abteilung/Name Göksel MEMS Plasma Actuators Projektname
5 FOR SEPARATION FLOW CONTROL Conventional Reynolds number UAVs at Re > 200,000 achieve loiter targets by deploying flaps At Re < 50,000 the aerodynamic efficiency is very low to reach high lift coefficients 9 V stall target loiter speed Re=83,000 41,500 small MAV, AR=1 small MAV, AR=2 large MAV, AR=1 large MAV, AR=2 44,000 Re=22, ,5 1 1,5 C 2 2,5 3 L,max Pulsed plasma actuators can serve as plasma slats and plasma flaps to also realize circulation control 2 C l,max conventional airfoils Göksel (baseline) Göksel (plasma control) Re B. Abteilung/Name Göksel MEMS Plasma Actuators Projektname
6 FOR SEPARATION FLOW CONTROL % duty cycle, 24W/m 100% duty cycle, 24W/m 50% duty cycle, 13W/m 50% duty cycle, 13W/m 3 10% duty cycle, 2.5W/m 3 10% duty cycle, 2.5W/m y (mm) 5% duty cycle, 1.3W/m 1% duty cycle, 0.6W/m y (mm) 5% duty cycle, 1.3W/m 1% duty cycle, 0.6W/m u (m/s) u' (m/s) Actuator calibration at 3mm downstream for different duty cycles at = 0. U B. Abteilung/Name Göksel MEMS Plasma Actuators Projektname
7 FOR SEPARATION FLOW CONTROL 0,9 0,9 0, F ,8 0,7 0,7 ΔC L ΔC L 0,6 0,6 0, F + 0, Duty Cyle (%) Effect of Strouhal number on post-stall (a=18 airfoil lift at a low MAV Reynolds number; Re=20,500). C µ =0.05% and duty cycle = 3%. Effect of duty cycle on post-stall (a=18 airfoil lift at a low MAV Reynolds number; Re=20,500). B. Abteilung/Name Göksel MEMS Plasma Actuators Projektname
8 FOR SEPARATION FLOW CONTROL 1.5 Re = 20,500 1 C l Baseline -0.5 F+=1, 3.6mW/cm, 1% duty cycle F+=1, 1.2mW/cm, 0.66% duty l α ( ) B. Abteilung/Name Göksel MEMS Plasma Actuators Projektname
9 FOR SEPARATION FLOW CONTROL Increasing α (filled symbols) and decreasing α (open symbols) 1,5 1,5 Re = 20,500 Re = 20, C L C L 0,5 0, ,5 Baseline F+=1, Cw= α ( ) -0,5 Baseline F+=1, Cw= α ( ) Effect of plasma actuation on airfoil performance at a low MAV Reynolds number illustrating non-linear behavior at low C W. C µ =0.04% and duty cycle = 3%. V=8kVpp (corresponding to 0.5W/m or 5 mw/cm) Effect of plasma actuation on airfoil performance at a low MAV Reynolds number illustrating the minimum c W required for linear behavior. C µ =0.04% and duty cycle = 3%. V=10kVpp (corresponding to 0.9W/m or 9 mw/cm) B. Abteilung/Name Göksel MEMS Plasma Actuators Projektname
10 FOR SEPARATION FLOW CONTROL Boundary Layer Tripping with Turbulators 1.5 Boundary Layer Control with MEMS Plasma Actuator 1,5 Re = 50,000 Baseline: clean airfoil Re = 50,000 1 Baseline: 2D trip Baseline: 3D trip 1 C L C L 0.5 0,5 Baseline 100% duty cycle 50% duty cycle 10% duty cycle 3% duty cycle α ( ) α ( ) Example of the effect of boundary layer tripping and plasma actuation at F + =1 on airfoil performance at Reynolds number Re=50,000. B. Abteilung/Name Göksel MEMS Plasma Actuators Projektname
11 FOR SEPARATION FLOW CONTROL Boundary Layer Tripping with Turbulators 1.5 Boundary Layer Control with MEMS Plasma Actuator 1,5 Re = 65,000 Re = 65, C L C L 0.5 0,5 Baseline: clean airfoil Baseline: 2D trip Baseline 3% duty cycle Baseline: 3D trip α ( ) α ( ) Example of the effect of boundary layer tripping and plasma actuation at F + =1 on airfoil performance at Reynolds number Re=65,000. B. Abteilung/Name Göksel MEMS Plasma Actuators Projektname
12 FOR SEPARATION FLOW CONTROL Flying Wing with 2 Plasma-Actuators 2,4 kv at 7,4 khz, 2 Phases, 1 Period B. Abteilung/Name Göksel MEMS Plasma Actuators Projektname
13 FOR SEPARATION FLOW CONTROL Flying Wing with 2 Plasma-Actuators 2,4 kv at 7,4 khz, 2 Phases, 1 Period B. Abteilung/Name Göksel MEMS Plasma Actuators Projektname
14 FOR SEPARATION FLOW CONTROL Lift Enhancement by 52.6% at α=0 Lift Enhancement by 14.3% at α=20 Drag Reduction by 181 % at α=0 Drag Reduction by 43,4 % at α=0 Lift Enhancement by 63.2% at α=0 Lift Enhancement by 55.9% at α=20 Drag Reduction by 278 % at α=0 Drag Reduction by 85,1 % at α=0 B. Abteilung/Name Göksel MEMS Plasma Actuators Projektname
15 MEMS FABRICATED PULSED PLASMA ACTUATORS FOR ACTIVE FLOW CONTROL List of Contents MEMS Plasma Actuators for Separation Flow Control MEMS Plasma Actuators for Wave Propulsion Conclusion and Outlook Phased Plasma Actuators Quelle: DGLR B. Abteilung/Name Göksel MEMS Plasma Actuators Projektname
16 FOR WAVE PROPULSION Mechanical Wave Propulsion 1. Bionic Transformation 2. Bionic Transformation Electrostatic Wave Propulsion 3. Bionic Transformation (funded by Ministry BMBF) 1. Test Wing 4 Plasma Actuators 6,9 kv at 7,1 khz, 4 Phases, 1 Periode Source: J. D. DeLaurier Source: K. D. Jones Video 2. b-ionic Airfish Wing 2x4 Trailing Edge Plasma Actuators 11,0 kv at 7,7 khz, 4 Phases, 1 Periode Principle: Pumping fluid over the span width through mechanically flapping wings Pumping fluid over the span width through electrically flapping wings B. Abteilung/Name Göksel MEMS Plasma Actuators Projektname
17 FOR WAVE PROPULSION 1. Accelerated Air Faster than Free Stream Velocity Wave Propulsion generates Thrust 2. Accelerated Air Speed Equal Free Stream Velocity Wave Propulsion compensates Drag to Zero 3. Accelerated Air Slower than Free Stream Velocity Wave Propulsion reduces Drag (Source: K. D. Jones) B. Abteilung/Name Göksel MEMS Plasma Actuators Projektname
18 FOR WAVE PROPULSION Source: Karakaya, Roth sin(ωt+4φ) sin(ωt+3φ) sin(ωt+φ) sin(ωt+2φ) Ø = 360 o N sin(ωt) Quelle: DGLR B. Abteilung/Name Göksel MEMS Plasma Actuators Projektname
19 FOR WAVE PROPULSION BILDER VON MEHRPHASIGEN MEMS PLASMA AKTUATOREN B. Abteilung/Name Göksel MEMS Plasma Actuators Projektname
20 FOR WAVE PROPULSION BILDER VON MEHRPHASIGEN MEMS PLASMA AKTUATOREN Quelle: DGLR B. Abteilung/Name Göksel MEMS Plasma Actuators Projektname
21 FOR WAVE PROPULSION Polyphase High Voltage Generator in b-ionic Airfish Wing 4 Phases 90 shifted: Quelle: DGLR kv p-p, 5 15 khz, 360 Watt B. Abteilung/Name Göksel MEMS Plasma Actuators Projektname
22 FOR WAVE PROPULSION Plasma Induced Jet Velocity at Zero Free Stream Speed Quasisteady Operation B. Abteilung/Name Göksel MEMS Plasma Actuators Projektname
23 FOR WAVE PROPULSION Technical Data of b-ionic Airfish: Length: 7,50 m Span Width: 3,00 m Diameter: 1,83 m Surface: 26,8 qm FESTO Esslingen Test Flights at TU Berlin Overall Weight: Empty Weight: Thrust Range: Helium Volume: 9,04 kg 2,71 kg 8-10 g 9,00 cbm World Premiere Minimum Lift: Maximum Lift: 9,0 kg 9,3 kg Weight Generators in Wings/Tail: 4,25 kg Weight LiPo-Batteries in Wings/Tail: 2,08 kg Maximum Flight Velocity: 0,7 m/s Maximum Flight Duration with Tail Propulsion: 60 min. Maximum Flight Duration with Wing Propulsion: 30 min. LiPo-Batteries in Tail: 12 x 1500 mah, max. 8 A LiPo-Batteries per Wing: 9 x 3200 mah, max. 60 A Power Ion Jet Engine in Tail: 2 x 40 W, max. 2 x 60 W Power Plasma Wave Propulsionnl: 266 W, max. 360 W World Premiere First Test Flight Quelle: DGLR B. Abteilung/Name Göksel MEMS Plasma Actuators Projektname
24 FOR WAVE PROPULSION Second Test Flight Video2 Technical Data of b-ionic Airfish: Length: 7,50 m Span Width: 3,00 m Diameter: 1,83 m Surface: 26,8 qm FESTO Esslingen Test Flights at TU Berlin Overall Weight: Empty Weight: Thrust Range: Helium Volume: 9,04 kg 2,71 kg 8-10 g 9,00 cbm World Premiere Minimum Lift: Maximum Lift: 9,0 kg 9,3 kg Weight Generators in Wings/Tail: 4,25 kg Weight LiPo-Batteries in Wings/Tail: 2,08 kg Maximum Flight Velocity: 0,7 m/s Maximum Flight Duration with Tail Propulsion: 60 min. Maximum Flight Duration with Wing Propulsion: 30 min. LiPo-Batteries in Tail: 12 x 1500 mah, max. 8 A LiPo-Batteries per Wing: 9 x 3200 mah, max. 60 A Power Ion Jet Engine in Tail: 2 x 40 W, max. 2 x 60 W Power Plasma Wave Propulsionnl: 266 W, max. 360 W World Premiere First Test Flight Quelle: DGLR B. Abteilung/Name Göksel MEMS Plasma Actuators Projektname
25 MEMS FABRICATED PULSED PLASMA ACTUATORS FOR ACTIVE FLOW CONTROL List of Contents MEMS Plasma Actuators for Separation Flow Control MEMS Plasma Actuators for Wave Propulsion Conclusion and Outlook Quelle: DGLR B. Abteilung/Name Göksel MEMS Plasma Actuators Projektname
26 CONCLUSION AND OUTLOOK - Demonstration of separation and circulation control using steady and pulsed plasma actuation on an airfoil at typical MAV Reynolds numbers. - Modulating the actuators at frequencies corresponding to F+ 1, resulted in improvements to C L,max, which increased with reductions in Re. - At the low end of the MAV Reynolds number range (Re=20,500) modulation increased C L,max by more than a factor of 2. - Hysteresis associated with the baseline airfoil was eliminated. - C L,max was shown to increase with decreasing duty cycle, and hence power input. - In fact, duty cycles of around 3% were sufficient for effective separation control at MAV Reynolds numbers, corresponding to power inputs on the order of 0,5 W/m. - High power (up to 400 W/m) steady and pulsed plasma actuation can for instance be used to propell lighter than air flight vehicle (e.g. at high altitudes) B. Abteilung/Name Göksel MEMS Plasma Actuators Projektname
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