See discussions, stats, and author profiles for this publication at: https://www.researchgate.net/publication/267269349 The Hyperion Green Aircraft Project-Presentation Conference Paper · January 2012 DOI: 10.13140/2.1.1868.0329 CITATIONS READS 0 102 2 authors , including: Jean N Koster University of Colorado Boulder 111 PUBLICATIONS 1,049 CITATIONS SEE PROFILE Some of the authors of this publication are also working on these related projects: Indium-Antimonide Crystal Growth View project Convection in isopycnic/miscibility-gap liquids View project All content following this page was uploaded by Jean N Koster on 23 October 2014. The user has requested enhancement of the downloaded file.
The Hyperion Green Aircraft Project Jean Koster & Lydia McDowell University of Colorado Boulder
Purpose pose Image credit: NASA RION ? WHY HYPERION WH • Soci ciety/ ety/ in indu dustry stry nee eeds ds – NASA-ERA goals: • Reduce fuel consumption, emissions, noise: higher efficiency – Prepare workforce in global environment • His istor tory – Senior students developed hybrid propulsion for aircraft – Boeing interest in “follow -the –sun” process – AIAA-ASM Meeting January 2010, Orlando: • NASA: “Environmentally Responsible Aviation (ERA) Project” – Boeing X48B prominently presented • Focus on aviation alternative fuels, fuel savings, reduced noise Moti tivati tion 2012 AIAA-ASM Nashville, TN
Motiv ivation: ation: Reduce uce Noise Airport port Noi oise se Cha hall llenge enge: : Aircraft noise regarded most significant hindrance to National Airspace System Image credit: NASA -Moti tivati tion- 3 2012 AIAA-ASM Nashville, TN
Motiv ivation: ation: Reduce uce Fuel l Burn n Fuel el Probl blem: em: In 2008 U.S. Commercial air burned 19.7 Billion Gallons + D.O.D. burned an additional 4.6 Billion Gallons 250,000,000… Tons of Carbon Dioxide (CO 2 ) [1] Nitrogen Oxide (NO x ) Goals ls Reduce NO x Emissions: Reduce Fuel Burn: 20% by 2015 33% by 2015 50% by 2020 50% by 2020 [1] [1] >50% beyond 2025 >70% beyond 2025 -Moti tivati tion- 4 2012 AIAA-ASM Nashville, TN
First Year Fall 2010 – Spring 2011 11th Hyperion 1.0 5
Global al Team am See: AIAA-2012-1223 FTS - Purp rpose - 6 2012 AIAA-ASM Nashville, TN
System em Confi figur gurati ation on • Flying Wing design led by Sydney Team • Raked Wingtips & Vertical Stabilizers designed by Stuttgart Team • Internal Structure Design, & Systems Integration by CU Team -Project t Overvie verview- 7 2012 AIAA-ASM Nashville, TN
Aerodynami odynamic c Analys ysis is Aero rodyn dynamic mic Requirements uirements: Aerodynamic testing was performed using multiple methods L/D greater than 20 CFD Statically stable 1/2 scale wind tunnel testing Stall velocity less than 15 m/s Span efficiency (e) greater than 0.8 Wing loading less than 15 kg/m² -Tech chnology Ove verv rview- 8 2012 AIAA-ASM Nashville, TN
Aerodynami odynamics cs Requirem uirements ents Verifi ification ation • L/D D grea eate ter r than an 20 CFD/W D/WTT • Static tical ally y stable ble Flig ights hts • Stal all l velo locity city less ss than an 15 15 m/s Calcu lculat ation on • Span an effi ficiency ciency (e) grea eate ter r than an 0.7 AVL AVL • 15 kg/m 2 Calcu Wi Wing g load ading ng less s than an 15 lculat ation on • L/D D ~1 ~18.5 WTT – Wind Tunnel Testing • Stal all l velo locity city ~15.7 m/s – Not met due to increased weight of aircraft -Aero rodyna ynamic mics- 9 2012 AIAA-ASM Nashville, TN
Aerodynami odynamic c Results lts • Wind tunnel testing done in Sydney on ½ scale model – No landing gear – Wing tips had no 6 ° cant angle due to manufacturing and time • CFD analysis lysis done e in Germany any -Aero rodyna ynamic mics- 10 2012 AIAA-ASM Nashville, TN
Foam m Prototypes totypes • Prototypes were a key for trim, weight distribution and flight characteristics • Helped develop methodology for wing construction of full scale aircraft Cheap models to tweak performance • Constructed out of foam • Hot wire cut along acrylic template • Sanded to “perfection” • Held together with rods and glue… and tape • Monocoated for damage resistance and aerodynamics Half f Sca cale Construc tructi tion 2012 AIAA-ASM Nashville, TN
Aerodynami odynamic c Results lts • Neutr tral al Point nt shift ft due to Prop p Wash – Test done for freestream velocity of 20 m/s and 20x10 propeller at 8000 RPM – At α =4 ° neutral point moves from x = 0.638m to 0.599m -Aero rodyna ynamic mics- 12 2012 AIAA-ASM Nashville, TN
Aerodynami odynamics cs & St Structures uctures ½ Scale Wind Tunnel Model Internal Structure Center Body/Integration Aerodynamic Validation Wing Integration/Assembly CFD Validation -Tech chnology Ove verv rview- 13 2012 AIAA-ASM Nashville, TN
Manufacturing: ufacturing: Center ter Body Pro roject ject Goal al and d Objectives jectives Distributed Manufacturing • Negative molds milled • Integration of internal from CAD-data structure from University • Fiberglass-foam-core skin of Colorado laminated by hand -Tech chnology Ove verv rview- 14 2012 AIAA-ASM Nashville, TN
Glo lobal bal Inte ntegrat gration ion Ma Manufac nufacturi turing ng Delocalized manufacturing increases integration risk! Risk Mitigation Similar ideas used for IDT (Interface Dimension wing manufacturing Template) • Device used to ensure Winglet Wing German center body matches USA wings -Inte tegra rati tion- 15 2012 AIAA-ASM Nashville, TN
Hybrid rid Gas-Elec Electr tric c Engine ine Pro roject ject Goal al and d Objectives jectives Objective: Design, build and test a hybrid propulsion system to be integrated into the aircraft Offset drive Coaxial drive No control system Multiple flight mode control Focus: Efficiency, proof of Focus: Reliability, operations concept See: AIAA-2012-0147 -Hyb ybri rid Propulsion- 16 2012 AIAA-ASM Nashville, TN
System em Concept ept of Operati rations ons -ConOps- 17 2012 AIAA-ASM Nashville, TN
Hybrid rid Engine ine System em Verifi ification cation • Dy Dynamomete mometer r testing ing – System torque output data – Obtain power, RPM data – Satisfy Hyperion ConOps • Therm ermal al testing ing – System fully enclosed for worst case scenario – Not exceed fiberglass softening point Test Like You Fly -Hyb ybri rid Propulsion- 2012 AIAA-ASM Nashville, TN
Hybrid rid Engine ine Testing ting Overvi view ew Mechanical Software/Control System Operational Operational reliability Engine/Aircraft Control Logic through endurance Integration Interface testing Taxi/Flight Testing Operational engine ICE & EM produce 2 hp each (4 hp total) control logic January-April 2012 Independent & Software/electrical Concurrent Engine interface Operations -Hyb ybri rid Propulsion- 2012 AIAA-ASM Nashville, TN
Hybrid rid Engine ine Goal l Real aliz ization ation • Hype perio rion n 1.0 aircraft craft fli ligh ght, t, April ril 2011 2011 – Electric motor of ~ 10 hp • Hybrid rid engi gine ne flight ight test t - Janu nuar ary – Stable aircraft: RASCAL • Hype perio rion n 2.0 taxi i test, st, March h – Risk mitigation • Hype perio rion n 2.0 flig ight ht test, t, April il – Maiden ICE flight – Maiden SOLSTICE HPS flight -Hyb ybri rid Propulsion- 2012 AIAA-ASM Nashville, TN
System em Testi ting ng • Elec ectric tric propulsion pulsion – Hybrid Engine fully bench tested, but not flight tested (maturity) • R/C /C Piloted loted – Successful takeoff, cruise, and landing -Maiden Test st- 21 2012 AIAA-ASM Nashville, TN
Second Year Continuation Fall 2011 – Spring 2012 Hyperion 2.0 22
Projec ject t Devel elopment opment Hyperion 2.0 Hyperion 1.0 2011-2012 2010-2011 • Hybrid engine • Wind tunnel flight testing • True BWB • Static and • CFD testing dynamic stability • Hybrid engine • L/D • Wind tunnel • True BWB testing • Prototype • CFD testing manufacturing • Successful flight • Autonomous • Follow-the-Sun control -Conti tinued Devel velopmen ment- 2012 AIAA-ASM Nashville, TN
HYPERION ERION 2. 2.0 • Cen enter ter bod ody y structure ructure is herita ritage; ge; wing ng desi sign gn is new ew • Proje oject ct has as comple mpleted ted an n aero rodyna dynamics mics /stru ructure ctures s TRR R and nd a guidan idance ce and nd control ntrol PDR DR – Wing structure redesign – Optimized aerodynamics – New landing gear – New control system – Better flight characteristics HYPE PERION RION 2.0 Ove verv rview 2012 AIAA-ASM Nashville, TN
Aerodynami odynamic c Redes esign ign 17° 35° 1.5 m 1.6 m • Composite center body and V-tail kept from previous model • Wings redesigned for better aerodynamics at low Reynolds numbers • Reduced total mass • Same design cruise speed (30 m/s) and wing loading (10 kg/m 2 ) - Aero rodynamics Desig sign - 25 Aero/Structures CDR
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