Mitchell Aerospace and Engineering Mitchell Community College October 3, 2011 Conceptual Design Review RockSat- C

Mission Description and Project Scope Design - Mechanical Design - Electrical Layout and Data Flow Design - Test Sequences Pr oject Management and Plan Control Conclusion Outline of Presentation

Mission Overview Goal Statement:  Our goal is to design and implement various generators to passively collect energy for possible use for space based instrumentation. We expect to harvest energy from the flight of the rocket, solar, magnetic and other various sources.

Mission Overview Theory and Concepts:  Electromagnetic transducers will utilize Faraday’s Law.  Solar transducers will utilize Photoelectric effect.  Thermal transducers will utilize the Seebeck and Peltier effect.  Sound transducer(s) will utilize electromagnetic induction or the piezoelectric effect.

Mission Overview Mission Requirements  Payload Will:  Harvest electrical energy from various sources during flight.  Measure electricity generated and then dispose/store of excess energy.  Measure various environmental factors throughout flight such as humidity, magnetic field and acceleration.

Mission Overview Concepts of Operations

Mission Overview Expected Results  Photovoltaic transducers will produce a maximum of 3.3 volts.  Electromagnetic transducer output will range from millivolts to volts.  Electromagnetic induction transducers will output a maximum of 10 volts.  Output of all sensors will be recorded and measured.  A current off-the-shelf (COTS) data sensing package will measure environmental variables and the power used will be recorded.

Mission Overview Expected Results  Measurable current from all transducers will be produced throughout the flight profile, with the peak output from some sensors occurring during engine burn.  Thermo-electric transducer output will be in the microvolt range.  Piezoelectric transducers output will be measured in volts, proportional to strain on piezoelectric material.

Design Overview

Mechanical Designs

Design Overview Mechanical Designs

Design Overview Mechanical Designs

Design Overview Mechanical Designs

Design Overview Mechanical Designs

Design Overview Mechanical Designs

Design Overview Mechanical Designs

Design Overview Electrical Functional Block Diagram

Design Overview Electrical Designs  The electrical system will be triggered by a G-Switch, indicating rocket launch.  An internal countdown program will begin counting down from our expected flight time delta.  Master Arduino will come out of sleep mode and start the analog read loop.  The slave Arduino will begin receiving and recording data from the balloon board sensors.  After end of flight profile, the Arduino countdown timer reaches zero.  The Arduino saves all data in buffer and shuts down.

Design Overview Electrical Designs  Arduino provides 10 bit integer measurements at 1000 Hz for analogRead() command.  The analog reference voltage allows measurement from 0 – 5 V DC.  Amplification will increase noise, reducing measurement resolution.  Further design and testing will address this issue.

Design Overview Electrical Designs  We will use a microSD flash card to store all data from generators and sensors.  Pending further testing, we will decide between the OpenLog and the Arduino microSD shield. OpenLogmicroSD Shield

Design Overview Software Flowchart

Design Overview Functional Project Testing  Testing will utilize a shake table and rocket test flights to functionality of components and full payload.  Shake table is currently in design.  Will perform component testing with a small scale rocket.  Will perform full scale mock up canister test with a high power rocket.  More test will occur as needed.

 Length – 46 inches  Diameter – 4 inches  Cesaroni – H 400 Motor  Max Acceleration – 26 (gees) (approx.)  Max Altitude – 1600 ft (approx.) Component Rocket Specs Design Overview

Full Scale Test Rocket Specs  Length – 93 inches  Diameter – 10 inches  Cesaroni – J 1520 Motor  Max Acceleration – 25 (gees) (approx.)  Max Altitude – 1900 ft (approx.) Design Overview

RPP Mock Up Canister Full Scale Mock Up Rocket Flight + Canister Specs Full Scale Mock Up Payload Design Overview

RockSat-C User’s Guide Compliance  Project PEGASIS will use half a canister and require a partner.  Useable payload space = 9.3” Diameter x 4.75” high.  Center of gravity  Payloads must conform to a center of gravity that lies within a 1x1x1 inch envelope of the geometric centroid of the integrated RockSat payload canister.  Approximate weight < 3.45 lbs without cap head screws.  Total weight of canister = 20+/- 0.2 lb.  Cannot modify canister.  Must be able to pass vibration test.

Design Overview Shared Canister  Project PEGASIS will use half a canister and require a partner.  The optic port will be used, but pressure port shall remain available.  Center of mass and all other requirements shall be fulfilled in compliance with RockSat-C Payload Canister User’s Guide.

Management Organization Chart

Management Safety  Electrical - rubber insulated gloves, safety goggles, make sure all switches are off for connect wire.  Mechanical - gloves, safety goggles, using common sense and caution around sharp tools, turn off power tools after use.  Safety officer will train team members on safe guidelines and practices.  Test-  Materials- use non-flammable material.  Motors- use certified motors.  We will strictly follow the TRIPOLI HIGH POWER SAFETY CODES.

Management Timeline 10/7 – RockSat-C meeting 10/14 – RockSat-C meeting 10/17 – Payment and online progress report due 10/26-10/27 – PDR and PDR teleconference 10/28 – RockSat-C meeting November to May – Open for Rocket Flight Testing 11/4 – RockSat-C meeting 11/7-11/11 – Component testing (shake table) 11/14 – Online progress report due 11/18 – Rock-Sat meeting 11/30-12/1 – CDR and then CDR teleconference 12/2 – RockSat-C meeting, begin legacy equipment testing 12/9 – RockSat-C meeting

Management Test Total: $ Electrical Total: $ Mechanical Total: $ Total Available Funds: $2,000 Equipment Budget Department MechanicalEquipment Estimated Cost Cost Description Makrolon $ Mounting Plates for Sensors and Generators Bolts $ 16.75Mounting Wire $ 19.00Generators Magnets $ 33.50Generators Rubber Bushings $ 19.75Shock Absorbtion for Plates and Hardware Piezoelectric speaker element $ 52.50Generator Electrical Micro SD Card $ 30.00Data Storage G - Switches $ 42.00Electronic Activation Op Amps $ 23.50Voltage Output Amplification Blank Printable Circuit Board $ 21.50Electronics Various Resistors $ 24.25Electrical System Etchant $ 48.00Cicrcuit Board Arwdino Atmega $ 83.00Program Controller Data Loggers ( Micro SD Shield of Open Log ) $ 42.00Data Collection Test Plywood $ 22.25Shake Table t $ Shake Table and Test Rocket Construction Assorted hardware $ 40.00Shake Table and Test Rocket Construction Cardboard tube $ 26.25Test Rocket Epoxy resisn $ 14.00Test Rocket Fiberglass $ 20.50Test Rocket Motors & Propellent $ Test Rocket Tubular Nylon $ 32.50Test Rocket Nose Cone $ 23.00Test Rocket Ignitors $ 32.25Test Rocket Kevlar Sheeting $ 42.00Test Rocket Rocket Electronics $ 85.25Test Rocket Parachute $ 22.00Test Rocket Table for shake test $ 35.25Test Rocket Vibration electronics and sensor $ 50.50Test Rocket Total MechanicalElectricalTest $ 1, $ $ $ Budget Overview

Management Mentor Doug Knight Ph.D  B.S. in physics, M.S. Applied Physics, Ph.D. Mechanical Engineering with Precision Engineering Concentration  Former Senior Test Engineer, Digital Optics Corporation  Mentor to winning TARC team, 2006  NASA SLI and USLI mentor,  Physics instructor, Mitchell Community College  TRA Level 2 Certified, high powered rocketry

CNC Machine Shop Facilities Electronics Lab Rapid Prototype Machine

Further Research and Considerations Further Research  Electromagnetic generators  Efficient Solar cells  Voltage amplification and noise reduction  Programming completion  Update Budget  Writing to Micro SD flash card Considerations Electricity generated be stored or dumped. Specific equipment for electrical transduction.

Conclusion  This project will measure and record the output of various transducers passively collecting energy during flight profile of a sounding rocket.  The design, manpower, and facilities necessary to make this project feasible have been presented and are sufficient to complete the mission.