Design of a TubeLaunched UAV

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Design of a Tube-Launched UAV

• Justin Ott and Daniel BiezadCal Poly State
  University, San Luis Obispo, CA.

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N04-T004 TITLE Sonobuoy Tube Launched UAV
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Sonobuoy Launch Concept

• Universal A size (4.875 x 36) Expendable
  Chute Sonobuoy
• 150-250 Kt Deploy Speed, 50 Kt Cruise
• Range 50 NM, Loiter 1.5 hr

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Preliminary Sizing

• Aero Optimized for One Flight Regime
• JASSM-like Deployable Wings
• 30o Wing Sweep (cg control with fit in buoy)
• Weight Driven by Propulsion (int vs
  elec)
• 9-14 lb for L/D of 9 for 1.5 lb payload

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Propulsion

• COTS Electric Motor
• Monitor Fuel Cell Technology
• Lithium Polymer Batteries
• High Discharge Rate
• No Excessive Internal Heat Problem
• 13 TP2100-3S Cells

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Performance Code Weight vs Payload at Endurance
1.5 Hours and Varying Cruise Speed Red Line
Shows CL 1 for Wing Area Limited within Sonobuoy
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Performance Code Weight vs Payload Varying
Endurance Red Line Shows CL 1 for Wing Area
Limited within Sonobuoy
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Control

• Elevons
• Allow Simple Deploy Mechanism
• Reduce number of actuators see below
• Used for both pitch and roll

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Wings Deployed by Torsion Springs
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Fixed Pitot Probe

• Aligns Payload without Reducing It
• Inexpensive and Reliable
• Would Jeopardize Entire Mission if Inactive
• Necessary for Autopilot Operation
• Jennings Autopilot (Dragon Eye, Desert Hawk

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Payloads 1 of 2

• Flexibility is Paramount
• Nose Module Unique to Each Item
• Preliminary TV IR Module Exists

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Payloads 2 of 2
HYPER SPECTRAL CAMERA IS NOT SUPPORTED 8 LB
RANGE FINDER
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AVIONICS

• Autopilot, Communications Board, GPS
• Uplink, Downlink Modules
• Flush with Fuselage
• Mounting Provides Necessary Cooling

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Cal Poly UAV Projects 2004

• Aircraft Altitude-Hold Closed Loop Control System
  by Implementing an Absolute Pressure Sensor by
  Felix Meneau
• Comprehensive System Identification of Ducted Fan
  UAVs by Dan Salluce
• Literal Factors Investigation of Flying Qualities
  for Micro UAVs as Camera Platforms by Chris
  Droney
• Helicopter UAV Systems Operation by Donald B.
  Stewart III

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Closed Loop Control System by Implementing an
Absolute Pressure Sensor F. Meneau
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Comprehensive System Identification of Ducted Fan
UAVs by Dan Salluce
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Literal Factors Investigation of Flying
QualitiesFor Micro UAVs as Camera
PlatformsChristopher K. Droney

• Current tail sizing techniques for UAVs are
  highly iterative requiring several flight test
  vehicles for size validation. This drives the
  design time and the development cost.
• The Boeing panel code A502I (PANAIR) was used
  to aide the development of the mathematical
  model.
• Frequency responses were generated with CIFER
• The mathematical model was within 11 of the
  measured natural frequency and within 35 of the
  measured damping ratio.
• The literal factors approximation provides
  reasonable estimates for yaw motion for small
  scale conventional vehicles.

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Team MAV

• 4 electric pico jets are on order
• Serve as flight trainers for each of the members
• These planes will be further modified to resemble
  true MAVs

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Team DBF
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Thanks for ListeningQuestions?