Cover Slide

CanSat Interim Presentation IISamuel Rustan (EE)Yasmin Belhaj (ME)Andrew Guerr (CE)Andrew Grant (ME)Maxwell Sandler(ME)

Technical Advisors: Dr. David Cartes, Dr. Victor DeBrunnerCourse Instructors: Dr. Kamal Amin, Dr. Michael Frank

ME Senior Design Team #18ECE Senior Design Team #10March 19, 2013

Mission Recap Finalized design and configurationsFabrication UpdateElectronics and IntegrationSoftware developmentTimeline and BudgetTasks remaining

Overview Presenter: Samuel Rustan 22CanSat Project OverviewDesign a container/payload system to be launched via rocket and develop autonomous descent control strategy to safely land CanSatContainer will house payload for initial descentPayload will house electronic components and sensor (egg)Telemetry data will be transmitted for flight durationSample Design Parameters and RestrictionsSize MassMaterialDescent Control Strategy

Presenter: Samuel Rustan 3

Presenter: Samuel Rustan 4CanSat Project Overview

Sequence of action Rocket supplied by AIAA, with specified rocket bay dimensionsPhase 1 from rocket detachment to 400 m: Per guidelines, a parachute or streamer must be used to decrease velocity to 20 m/s by 400 m mark.Phase 2 from 400 m to ground level: Payload must detach from container. An aero-braking device (non-parachute) must deploy at 400 m to safely land Payload. The initial parachute will continue to control descent of container.Telemetry data transmitted includes GPS data, altitude, air temperature, battery voltage, and flight software state.Force sensor will be used to calculate force of impact from Payload.

4Previous BenchmarksFinalized design for launch and descent Compared passive braking method Parachute vs. StreamerDetermined egg protection strategy Iterative trials, various materialsSelectable Objective Impact Force SensorProcured and tested electronic components Delivered successful Preliminary Design Review (PDR) Feedback: Scored 92% from AIAA/NASA Panel

Presenter: Samuel Rustan 5

Updated Launch Configuration Egg CompartmentElectronicComponentsShelvingSeparationMechanismParachuteAero-brakingStructureContainerPayload6Explain selection of each subsystem:Container is the entire length of structure. Made of plastic, it is open on the bottom.Payload is the portion inside that houses the electronic components and the raw egg.Parachute was selected by conducting an experiment on the braking efficacy and ease of implementation of parachutes and streamers for this application. The diameter of the parachute was calculated to achieve the desired 20 m/s at 400m.While under descent of parachute, the payload will detach from the container via this separation mechanism. A motor will provide the rotation of this ring to allow the payload to fall from out from the bottom.The aero-braking structure is secured in its launch configuration, surrounding the payload. Support rods connect the top and bottom portions of the aero-braking structure to the payload.Electronic components are in the top portion of the payload, and the egg is housed near the bottom.6

Updated Descent ConfigurationTorsion Spring Torque of 2.14 [in*lb] 7-Maintained idea to use ABS Plastic and 3-D print top and bottom of aero-braking structure, on top of which we can mount the motor that controls the separation mechanism-Torsional springs will be used to deploy these rods which have fabric attached in between-These springs are held in compression by a wire running through the bottom, and released when a heating element breaks the wire slightly below 400m-New components include a wire running from the bottom of the aero-braking structure to the ends of the rod, to secure the angle during deployment

7Fabrication Update

Parts have been procured and machinedDimensions finalized to fit in rocket bayMass budget concerns (underweight)8-Still waiting on parachute-Dimensions have not been changed since last presentation-Allow clearance in the rocket section of 130 mm x 250 mm -Overcome sizing issues of micro-controller, motor, and payload-Challenge meeting 700g weight requirements. Solution use alternative egg protection method and/or alter material of support rods (aluminum, wood, plastic)

8Fabrication Update

Top Left: Side View with Aerobrake deployedTop Right: Aerobrak cut-away with antennaBottom Left: Top View with aero-brake deployedPresenter: Andrew Grant9Release Mechanism PrototypePresenter: Andrew Grant10

Sensor (Egg) ProtectionPolystyrene beads chosen from experiment1050 [kg/m3]

Presenter: Andrew Grant11-Polystyrene beads chosen to protect egg-Will be inserted in the bottom portion of the CanSat as seen in above image

11Integration of Electrical ComponentsEach sensor on separate circuit board#2 & #1 screws used to attach to plastic platformsGlue to secure Rubber footpads used to separate components from platformHoles will be drilled in platform to provide wire bundle channel (not shown)

Presenter: Samuel Rustan 12-Multi-Level Electronics Arrangement-Permanently Affixed to Payload Half-Rigid shelves made of plastic

12Configuration of Telemetry ComponentsPresenter: Samuel Rustan 13

XBEEUSBAntennaGround StationTo AntennaCanSat Onboard ElectronicsNote: USB cables for programming only-Multi-Level Electronics Arrangement-Permanently Affixed to Payload Half-Rigid shelves made of plastic

13Integration of Electrical Components

Presenter: Samuel Rustan 14

AccelerometerPress/TempGPS ModuleMicrocontroller Battery XBEE Radio-Multi-Level Electronics Arrangement-Permanently Affixed to Payload Half-Rigid shelves made of plastic

14

Communications: Range TestsPacket Loss:0%10%30%50%LostGround LevelDistance [m]Test 1-6:456580110115+~3 [m] highTests 7-1060120140180190+

Results2.4 GHz, 60 mWInsufficient RangeImproper TestProposed SolutionsIncrease Gain of Receiver AntDigi Intl RF EngineerProper range test (5 [m] above any obstacle)Link Margin: 20 [dB]Receiver Sensitivity: 100 [dB]Received Power: 80 [dB]Link Margin = 100 80Enough margin to maintain link (accord. To Digi RF Tech)

Presenter: Samuel Rustan 15Ground Control SoftwareFlight SoftwareWorking Beta versionMigration is so far good No noticeable difference between the Uno and Mini functionality

Presenter: Andrew Guerr16Ground Station SoftwareVersion 5, working alpha versionWritten in PythonBoth Mac (shown) & PC versionsNot yet fully integrated with all subsystems

Flight Software

CurrentWorking Beta versionTransmits telemetry data packetIntegrated with altimeter and GPSErrors reading GPS dataNeedsIntegration with accelerometer, voltage divider, buzzer, and motorSupport for user entry of altitude correction dataAltitude smoothingPresenter: Andrew Guerr1717Updated Gantt

RevenueExpensesFunding SourceFunds ReceivedProcuredExpense AmountECE Department$200.00ECE Components (Telemetry)300Private Donation$750.00Mechanical & Structural70Dr. Shih$1000.00Shipping15.00State Farm$250.00Total Funds Generated$2200.00Total Procurement Expenditures385Total Available Funds Remaining$1815.00Funding / Project Budget Looking ForwardParachute attachmentComplete fabrication of CanSatEmphasis on Open House DisplayTest separation mechanism and aero-braking deployment using altimeter

Complete microcontroller migrationComplete range testingDemonstrate Telemetry with FSW & GCSW

Prepare User Manual Present AIAA Critical Design Review (Mar 29th)Prepare Open House Demonstration (April 18th)