Dane BatemaBenoit Blier Drew Capps Patricia Roman Kyle Ryan Audrey Serra John TapeeCarlos Vergara Team 1: Propulsion QDR 3 Team 1 October 17, 2006.

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Presentation transcript:

Dane BatemaBenoit Blier Drew Capps Patricia Roman Kyle Ryan Audrey Serra John TapeeCarlos Vergara Team 1: Propulsion QDR 3 Team 1 October 17, 2006

AAE 451 Team 1 2 Propulsion System Design Method Goal: Design a single propulsion system capable of performing the design mission (one prop, one gearbox, one battery system). –Undesirable to require two propellers to complete design mission –Superior marketability of multi-functional aircraft Method: 1) Determine propeller diameter and pitch for dash RPM < 10,000 2) Size propulsion system to meet dash requirements 2a) Select batteries to supply maximum power at minimum cost 2b) Find a cost-efficient gearbox with high gear ratio for 480 class motor 2c) Select motor with correct Kv that can handle the necessary current 3) Ensure that loiter requirement can be met with dash-optimized system 3a) Calculate energy available with dash-sized battery 3b) Loiter = 500 ft radius circular flight path 40 ft/s air speed 3c) Determine flight time (must be > 7 minutes)

AAE 451 Team 1 3 Max Speed (battery current limited) ft/s ~ 80.3 mph Propeller –APC (LP11011) 11x Pattern Propeller ($7.95) Gearbox & Mounting Hardware –MP Jet (MP8104) 4.1:1 Gearbox for 480 Size ($19.90) –MP Jet (MJ8030) Short Prop Adapter for APC Props ($4.60) –MP Jet (MJ7250) 2" Black Lightweight Spinner ($3.20) Motor –MEGA ACn 16/25/3 ($84.00) Speed Controller –JETI Spin 44 ($137.95) Batteries (in series) –2 x Apogee 3-Cell 11.1 V 1200mAh 20C LiPo (2 x $25.00) Total Propulsion Chargeable Cost = $ (neglects speed controller) Propulsion System

AAE 451 Team 1 4 Loiter (Main_System_Design - Modified) –Estimated Loiter Time: 20.7 mins (nearly 3X requirement) –Motor Voltage input: 9.68 V –Motor Current input: 7.97 A –Motor RPM: 16,200 RPM –Motor  : 75.1% Motor/Battery Loiter Performance Stall P req > P avail (40,0.03) Loiter mission is steady turn at a 500 ft radius. Aircraft Constants: C D0 = e = 0.75 AR = 5.6 W = 5 lb S = 4.16 ft 2

AAE 451 Team 1 5 Motor/Battery Dash Performance Dash (Main_System_Design - Modified) –Motor Voltage input: 20.9 V –Motor Current input: 24.0 A* (Motor Max Continuous 30 A) –Motor RPM: 34,900 RPM (Motor Maximum 55,000 RPM) –Motor  : 90.3% –M tip,prop = 0.38 Vmax = ft/s Gear Ratio = Actual Gear Ratio: 4.1 Actual Vmax = ft/s * Max battery continuous output 24 A Stall P req > P avail (117,0.37)

AAE 451 Team 1 6 Dash System Performance  =98%  =94% 426 W 0.57 hp  =65% 454 W 0.61 hp 502 W 0.67 hp  =90% 513 W 0.69 hp 278 W 0.37 hp 1.74 lbf Propeller power required increased by 1/0.75=33.3% per guidance from gold.m file.

AAE 451 Team 1 7 Summary No need for multiple propulsion systems Battery required for dash exceeds loiter requirements Speed controller powers servos → no separate battery Zero control power for trim at high speed is important

AAE 451 Team 1 8 Questions??