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Jay Carter, Founder & CARTER AVIATION TECHNOLOGIES An Aerospace Research & Development Company Jay Carter, Founder & CEO CAFE Electric Aircraft Symposium www.CarterCopters.com July 23rd, 2017 Wichita©2015 CARTER AVIATIONFalls, TECHNOLOGIES,Texas LLC SR/C is a trademark of Carter Aviation Technologies, LLC1 A History of Innovation Built first gyros while still in college with father’s guidance Led to job with Bell Research & Development Steam car built by Jay and his father First car to meet original 1977 emission standards Could make a cold startup & then drive away in less than 30 seconds Founded Carter Wind Energy in 1976 Installed wind turbines from Hawaii to United Kingdom to 300 miles north of the Arctic Circle One of only two U.S. manufacturers to survive the mid ‘80s industry decline ©2015 CARTER AVIATION TECHNOLOGIES, LLC 2 SR/C™ Technology Progression 2013-2014 DARPA TERN Won contract over 5 majors 2009 License Agreement with AAI, Multiple Military Concepts 2011 2017 2nd Gen First Flight Find a Manufacturing Later Demonstrated Partner and Begin 2005 L/D of 12+ Commercial Development 1998 1 st Gen 1st Gen L/D of 7.0 First flight 1994 - 1997 Analysis & Component Testing 22 years, 22 patents + 5 pending 1994 Company 11 key technical challenges overcome founded Proven technology with real flight test ©2015 CARTER AVIATION TECHNOLOGIES, LLC 3 SR/C™ Technology Progression Quiet Jump Takeoff & Flyover at 600 ft agl Video also available on YouTube: https://www.youtube.com/watch?v=_VxOC7xtfRM ©2015 CARTER AVIATION TECHNOLOGIES, LLC 4 SR/C vs. Fixed Wing • SR/C rotor very low drag by being slowed Profile HP vs. Rotor RPM, PAV Rotor Drag per WADC TR 55-410: @ 250 kts @ SL 3 2 600 0 C AR 1 4.6 8 Db HP 0 500 O 550 400 299 300 HPo - Full Profile Profile HP 200 HPo - Rot Only 100 54 155 0 5.7 0 100 200 300 400 Rotor RPM • SR/C wing very small because rotor supports aircraft at low speeds – wing can be sized for cruise • Fixed-wing wing must be sized for low speed/landing • SR/C slowed rotor & small wing equivalent to fixed-wing’s larger wing ©2015 CARTER AVIATION TECHNOLOGIES, LLC 5 SR/C Electric Air Taxi Ø34’ 54” Cabin Width 36’ ©2015 CARTER AVIATION TECHNOLOGIES, LLC 6 SR/C Electric Air Taxi– Features High inertia, low disc Lightweight, low Slowed rotor enables 10’ diameter scimitar loaded rotor acts as profile, streamlined high speed forward tail prop rotates to built-in parachute, but tilting hub greatly flight, low drag, low tip provide counter torque safer because it works reduces drag. No speed/noise, no for hover or thrust for at any altitude / spindle, spindle retreating blade stall forward flight speed, and provides housing, bearings or directional control lead-lag hinges Tall, soft mast isolates airframe from rotor vibration for fixed-wing smoothness Tilting mast controls Mechanical flight aircraft pitch at low control linkages to speeds & rotor rpm for optional pilot in parallel high cruise efficiency with actuators for true at high speeds redundancy Extreme energy Simple, light, absorbing fail safe High aspect ratio wing Battery pack in nose to structurally efficient landing gear up to with area optimized for balance tail weight wing with no need for 30 ft/s improves cruise efficiency high lift devices landing safety ©2015 CARTER AVIATION TECHNOLOGIES, LLC 7 Performance Parameters Drag coefficients based on actual achieved data, not expected improvements 3200 lb empty weight with batteries 4000 lb max gross weight (800 lb max payload) 300 W-hr/kg battery energy density Assumed margin for 0.5 Empty Weight Fraction at 600 ft/s tip speed Mission: 30 sec HOGE for takeoff, Climb at Vy to 5k ft, Cruise at 175 mph, Descend at Vy, 2 min HOGE at landing (no reserve) Empty Wt (w/o batteries) vs. Rotor Range at 175 mph vs. Payload for Hover Tip Speed Various Hover Tip Speeds 2250 200 180 2200 2213 lbs 160 159 miles 140 2150 D=46 miles 120 113 miles 2100 D=213 lbs 100 80 Range, Range, miles 600 ft/s 2050 Empty Weight, lbs 60 550 ft/s 40 2000 2000 lbs 500 ft/s 20 450 ft/s 1950 0 400 450 500 550 600 650 700 0 200 400 600 800 1000 Rotor Hover Tip Speed, ft/s Payload, lbs Note: 150 mph cruise will extend range by Figure 1 Figure 2 ~10% at 800 lb payload ©2015 CARTER AVIATION TECHNOLOGIES, LLC 8 Air Taxi Concept Comparison • Compared three different configurations • SR/C • Hex Tilt Rotor • ‘T’ Tilt Rotor • Used common assumptions and methods for all three concepts SR/C • Based drag coefficients and parameters on measured flight data from PAV Carter PAV L/D vs. IAS 14 12 10 8 Hex Tilt Rotor L/D 6 Meas'd Model 4 2 0 0 50 100 150 200 250 IAS, mph Actual Measured Flight Data Note: Data scatter mostly attributable to gathering data when developing rotor rpm / mast control algorithms and varying rotor rpm considerably ‘T’ Tilt Rotor ©2015 CARTER AVIATION TECHNOLOGIES, LLC 9 Analysis Methods & Assumptions Parameter Assumptions Gross Weight 4000 lbs 200 lbs per person Pilot/Pax Weight 4 people max Empty Weight Calc’d with same method for all – modified Raymer Battery & Drive Efficiency 0.92 80% Useable Battery Capacity (top 10% unuseable with rapid charge, bottom 10% unuseable to avoid current spike) Scaled Linearly with Max Continuous Power Motor + Inverter Weight 0.4 lb/HP Assumed motor could be overloaded 1.87x for 30 sec for OEI Limited current to 40 amp per wire, running multiple wires per Wiring Weight leg to reach full current required. Per N.E.C., used AWG-10 with Class C Insulator Used same coefficients on all concepts & appropriately scaled Drag Coefficients misc drags as derived from calibrating model to actual flight data from PAV Hover Hover Out of Ground Effect (HOGE) at 6k ft with 1.1x margin Typical Mission 30 sec hover, climb, cruise, descent, 30 sec hover 120 sec hover, climb, cruise, descent, 120 sec hover Planning Mission +Reserve: 120 sec hover, 2nm divert, 120 sed hover ©2015 CARTER AVIATION TECHNOLOGIES, LLC 10 Common Footprint • Footprint driven by interface with vertiports • If certain size footprint can be justified, justification is applicable to all technologies • Single Rotor SR/C & Hex Tilt Rotor have similar disc loadings • ‘T’ tilt rotor has very high disc loading 39 ft ‘T’ TR Hex TR SR/C Rotor Area, ft² 144.9 791.5 907.9 Disc Loading, lb/ft² 27.6 5.1 4.4 Total Hover HP 774.0 368.4 424.0 ft 30 sec OEI HP 1869.6 467.8 N/A 34 34’ 34’ width Cruise HP at 175 mph 240 240 207 Total Installed Cont HP 1099.2 390.1 612.8 • ‘T’ TR Rotor Area only includes 4 lifting rotors (tails rotors for trim control only) • SR/C Total Hover HP includes tail rotor power to counter torque • All Hover HPs include 10% lift margin ©2015 CARTER AVIATION TECHNOLOGIES, LLC 11 Comparison Preliminary Results • ‘T’ Tilt Rotor has very high HP required due to disk loading – higher empty weight for installed HP • SR/C has better L/D @ 175 mph due to smaller wings & less wetted area from prop spinners, fuselage, & no LG sponsons Empty Weight vs. Width Range vs. Payload 2,100 180 SR/C - 40 ft 2,050 160 2,000 140 SR/C - 37 ft 120 1,950 SR/C - 34 ft 100 1,900 SR/C Hex TR - 40 ft 80 1,850 Hex TR Hex TR - 37 ft Range, Range, miles 60 1,800 T TR 40 Hex TR - 34 ft 1,750 20 'T' TR - 40 ft 1,700 0 'T' TR - 37 ft 32 34 36 38 40 42 0 200 400 600 800 1000 Empty Weight, Excluding Batteries, lb Overall Width, ft Payload, lbs 'T' TR - 34 ft L/D vs. Airspeed Mileage vs. Payload 16 1.4 SR/C - 40 ft SR/C - 40 ft 14 1.2 SR/C - 37 ft SR/C - 37 ft 12 1 hr 10 SR/C - 34 ft - SR/C - 34 ft 0.8 8 Hex TR - 40 ft Hex TR - 40 ft L/D 0.6 6 Hex TR - 37 ft Hex TR - 37 ft mile / kW 0.4 4 Hex TR - 34 ft Hex TR - 34 ft 2 0.2 'T' TR - 40 ft 'T' TR - 40 ft 0 0 'T' TR - 37 ft 'T' TR - 37 ft 0 50 100 150 200 0 200 400 600 800 1000 True Airspeed, mph 'T' TR - 34 ft Payload, lbs 'T' TR - 34 ft ©2015 CARTER AVIATION TECHNOLOGIES, LLC 12 Comparison Preliminary Results • SR/C has farthest range with least energy used in typical mission, due to better L/D at 175 mph • ‘T’ Tilt rotor has low useable energy because of high empty weight fraction. Has low percentage of energy available for cruise because of high HOGE power requirements for planning / reserve. Useable Energy Budget, 800 lb payload, 34' width 180 160 140 R3. Reserve 2 min HOGE 120 R2. 2 nm reserve at best endurance Reserve R1. Reserve 2 min HOGE hr - 100 P1. 90 sec + 90 sec add'l HOGE for planning Add’l HOGE for Planning 5. 30 sec HOGE 80 Energy, Energy, kW 4. Descend to Ldg Altitude 3. Cruise at 5000 at 175 mph 60 Typical Mission 2. Climb at Max ROC to Cruise Alt 40 1. 30 sec HOGE 20 0 SR/C (123 mile) Hex TR (110 mile) 'T' TR (49 mile) ©2015 CARTER AVIATION TECHNOLOGIES, LLC 13 Extreme Energy Absorbing Landing Gear • Extreme energy absorbing – 24” stroke for descent rates up to 24 ft/s at touchdown Carter Smart Strut • Responds to impact speed for near constant deceleration across full throw of gear Belleville Stackup • No rebound – no bouncing to control valve • Proven technology – used on all Carter to keep pressure prototypes Air Over on piston near • Lightweight due to efficient energy Hydraulic for constant based absorption Energy on impact PAV Single Strut Design Absorption velocity Energy Absorbing Cylinder Automatic Metering Valve Hydraulic Pressure in Lower Cylinder Main Gear for Gear Retract Trailing Arm Torque Tube ©2015 CARTER AVIATION TECHNOLOGIES, LLC 14 Energy Absorbing Landing Gear Video Video also available on YouTube: https://www.youtube.com/watch?v=MntCeJRl2YE ©2015 CARTER AVIATION TECHNOLOGIES, LLC 15 Energy Absorbing Landing Gear Note near constant pressure over full stroke 100 95 90 85 80 75 70 65 60 Piston position (8.44"
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