Detailed Design Review P UAV Telemetry Chris BarrettProject Manager Gregg GolembeskiInterface Manager Alvaro PrietoRadio Concepts Cameron BosnicSoftware Concepts Daron BellPower Concepts R09230 Project Family

Mission Statement Customer Needs Deliverable Summary System Architecture Subsystem Design Bill of Materials Risk Assessment Outline

Mission Statement The goal of this project is to create an open source, multi platform, bidirectional telemetry system. Carried on UAV Airframe C Interface with Control System(P10236) Send flight data to ground Remotely Trigger On-Board Camera

Deliverables Wireless System for Bidirectional Communication between control system and ground PC GUI Application that displays flight data multi platform, open-source, in real-time

System Design

Radio Goals: Two radios that send and receive data with high throughput and data integrity. The radios should be transparent to both the control system and base station as if it were a physical connection. This “radio as a wire” concept allows interchangeability of various radios using different wireless technologies.

Radio Components Radio: 2 Digi Xtends PKG 900 MHz. Ground Antenna: 65’’ 8.1 dBi Omni- directional antenna. UAV Antenna: 6’’ 2.1 dBi Omni-directional antenna.

Specifications Engineering Specifications Ideal ValueMarginal Value Range Refresh Rate (Hz)105

Analysis c Speed of Light L Wavelength f Frequency Pr Power Received Pt Power Transmitted Gr Receiving Antenna Gain Gt Transmitting Antenna Gain R Distance Between Antennas

Analysis Calculated Values Range bps Range 9600 bps Refresh Rate bps Refresh rate 9600 bps Max Packet size Min Packet Size

Testing Transfer of Serial Data: Connect computer to each radio Transmit data using simple terminal program Tester confirms data is accurate Repeat at both available baud rates to confirm proper orientation

Testing Range: Place one radio in a high place and the another on a mobile platform Send data back and forth between the radios using an automated program Move away with the mobile radio until you can no longer receive data.

Interface Radio >> Controller DB 9 M/F cable Molded Radio >> Computer Serial Cable USB to Serial Adapter

Power Supply Power solution must... not interfere with other on-board power systems. sustain radio communication throughout flight time. Components: Battery: 11.1V 5500mAh Li-Poly Lipo Battery Pack

Specifications Engineering Specifications Ideal ValueMarginal Value Flight Time (min)4530 Design Specs Min. Battery Charge rating (mA-h) 900

Analysis Current requirement for radio: Battery Current mA x Time hours=mAh 900 mA x 1 Hour=900 mAH Battery Life: Battery Current Rating /Current Draw = Run Time 5500 mAh/900 mA=6.11 hours

Testing Battery Life: Connect battery across a ten ohm resistor and monitor its output voltage until it drops below the level that is accepted by the radio The time it takes the voltage to drop below the acceptable amount is the approximate run time of the battery

Interface Battery >>Radio: Barrell power connector, size type M (5.5mm x 2.1mm barrell type connector) Battery output cables will be soldered to connector

Mounting and Packaging The Mounting and Packaging solution must... securely attach the aerial radio and power systems to UAV C. provide protection to onboard components in the event of a hard landing. add minimal weight to the system. add minimal size to the system. allow for easy access to components.

Mounting and Packaging

Specifications Engineering Specifications Ideal ValueMarginal Value Weight (kg) Size (cm)15.25x15.25x x17.75x17.75 Flight Time (min)4530 Max Acceleration(m/s 2 ) Design Specifications Associated ES Max Stress (kPa)2.82e5Max Acceleration Max Weight (kg)2.27Weight Max Size (cm)17.75x17.75x17.75Size Max Temp.(ºC)80Flight time

Analysis Assumptions: o Motion of system is considered to be free vibration o Foam acts a linear spring o PCB in radio is analogous to PCBs used in phones o m1 and m2 are homogenous o Damping can be neglected o Can simplify to a system with two degrees of freedom m 1 = 0.2 kg m 2 = kg k 1 = 1310 N/mm k 2 = 592 N/mm V i = 6 m/s

Analysis FBD 1 FBD 2 Equations of motion Mass and stiffness Matrices K t = M -1/2 KM -1/2 Normalized stiffness Matrices w = [w 1 w 2 ] T Natural Frequency MatrixEigenvector Matrix P = [v 1 v 2 ]

Analysis. Initial conditions for modal coordinates Displacement of modal coordinates Displacement Response

Analysis. E g =2700 J m radio =0.2kg  max =42.2 C Eg = mc p  T Radio Eg Max Temperature: Assumptions: o Radio is well insulated o Energy usage is 1 Watt o Ambient Temperature is 37.8 C o Run time is 45 minutes Insulation

Testing. Overheating: Run the system in an environment that is insulated similarly to our system. Monitor the temperature of the radio while it is running. If the radio stays within its operating temperature for longer then the planned flight time we can be sure it will not overheat in the UAV.

Interfaces. System >> UAV C System will be attached to UAV C using Industrial strength Velcro. Housing >>Battery/Radio Industrial strength Velcro will be used to secure the battery/radio to the housing

Software Software application must... track and log UAV control variables. support multiple computing platforms. report all flight data through a visual interface. maintain open source concepts. refresh at acceptable rate. transmit remote shutter command.

Software Design

GUI Design Flight Plan

GUI Design Flight Info

GUI Design Data View

Bill of Materials

Risks Risk Management