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)