Preliminary Design Review Cyclone Student Launch Initiative
Overview Team Overview Mission Statement Vehicle Overview Avionics Overview Safety Overview Payload Overview Requirements Compliance Plan
Team Structure
Team Organization
Website & Social https://m2i.aere.iastate.edu/cysli/ Facebook: ISUcysli Instagram: cyclonestudentlaunchinitiative Twitter: @IowaStateCySLI
Mission Statement Cyclone Student Launch Initiative s mission is to successfully design, build, test, launch, and recover a reusable high-powered model rocket while meeting and exceeding the safety standard set by the competition. The rocket will reach an apogee of 4750 feet and, upon landing, will deploy an autonomous rover which will travel a minimum of ten feet and collect a minimum of 10 ml soil sample. Additionally, CySLI has set out to educate and inspire the engineers of tomorrow through demonstrations and hands on activities for all ages.
Vehicle Overview
Vehicle Mission Success Criteria Ability to launch again without modifications after recovery Retention of rover during flight Deployment of the rover safely upon RSO approval Ability to reach an apogee between 4650 feet and 4850 feet.
Vehicle Dimensions 11 feet 2 inches long 23.3125 lbs with motor (20.7 lbs without) 4 Outer Diameter
OpenRocket Diagram Main Parachute Bay Nose Cone & Fore Altimeter Bay Payload Bay Aft Altimeter Bay Drogue Bay Motor Mount Avionics Bay
Stability CG: 90.4 from nose cone CP: 102 from nose cone Stability Margin: 2.8 cal
Mass Statement Independent Sections under Drogue: Independent Sections under Main: Motor Mount: 8.47 lbs Motor Mount: 8.47 lbs Rest of Rocket: 12.19 lbs Nose Cone and Main: 4.74 lbs Rest of Rocket: 7.45 lbs Section: (without motor) Nose Cone Main Bay Payload Bay Aft Altimeter Bay Drogue Bay Avionics Bay Motor Mount Mass: (lb) 1.81 3.07 4.99 0.731 1.52 1.42 3.06
Performance Predictions Rail exit velocity 99.6 fps Maximum velocity 756 fps Maximum acceleration 614 ft/s^2 Apogee: 5641 ft
Minimum Diameter Reduces weight, cost, and build time significantly Decreases strength of fins Airframe experiences higher temperatures Motor Retention: Internal Less cross-sectional area 75mm vs 98mm 75 is too small for rover 98 has less motor selections
Fin Strengthening Tip-to-tip fiberglassing Fin Can Greatly increases strength without additional drag Low heat resistance Removable High Heat resistance Heavy Complex to manufacture More drag Using TTTF for strength Moving fins forward 2 to reduce thermal load
Material Selections Carbon Fiber Airframe Blue Tube Coupler Strong and light Will need antenna openings Easy to work with Light and thin Fiberglass Reinforced Motor Mount Heat resistant Strong
Nose Cone 5.5:1 Filament Wound Von Karman Nose Cone 22 long Aluminum tip Von Karman vs Ogive vs Parabolic Ogive has a smaller fineness ratio Parabolic manufacturing difficulty
Motor Selection AeroTech K1999N-P Average Thrust: 424.3 lb Total Impulse: 571 lb-s Launch Mass: 6.59 lb Empty Mass: 3.96 lb Thrust to Weight: 17.7 Burn Time: 1.38 seconds
Recovery Subsystem Drogueless 55 inch annular main parachute Separation at apogee Main event at 600 feet Piston Ejection System Starting with 60 inch, resize two gores Less black powder Eliminates parachute protection More complex build Drift Calculations Descent time: 86 seconds Section Kinetic Energy (ft*lb) Nose Cone 40.7 Payload and Drogue 63.4 Motor Mount 72.1 Wind Speed Drift Distance (ft) 5 mph 324 10 mph 1247 15 mph 1871 20 mph 2495
Recovery Subsystem Two altimeter bays inside vehicle Four altimeters, two per bay Shielded by carbon fiber, copper tape Altimeters: Stratologger and AIM USB Each powered independently by 9V batteries Activated by external key switches Two in-flight separation points Apogee separation between airbrake bay and drogue bay Main parachute deployment between nose cone and main parachute bay
Airbrake Subsystem External Internal 2 bars, 4 panels, & 2 hinges each Mostly straight to Diamond shape Straight would not open Panels held on w/ screw Servo w/ cage and wire Strong Simple Bar Splits into internal and external Parts screw together Wire connected by wire collar
Airbrake analysis through CFD Four models analyzed during retraction and deployment Two with wind-redirectors Two without wind-redirectors Four without wind-redirectors Two with a covering plate
Avionics Overview
Avionics: Apogee Control Method Systems considered: Ballasting, PID Controller, Apogee Prediction Dynamically Deployable Air Brake System (DDABS) Less maintenance and assumption on launch day Reduced error Microcontroller predicts apogee continuously during flight Computer controls brakes through servo motor Brakes increase drag of the vehicle during coast phase Process repeats until desired apogee is predicted Brake actuation restricted using software
DDABS: Electrical Hardware
DDABS: Flight Computer Comparison Results Teensy 3.5 0.521 Raspberry Pi 3 B+ 0.283 Arduino Mega 2560 0.195 Criteria Processor Speed Physical Size Ease of Use All Consistency Indices are below the.1 standard
DDABS: Flight Computer Hardware Teensy 3.5 120 Mhz ARM Processor 192KB of RAM Runs Arduino-compatible software 2.5 x 0.7 x 0.2 inches Integrated SD card slot for data logging Acceleration, altitude, launch events, brake action https://sparkfun.com/products/14055
DDABS: Hardware Configuration
DDABS: Battery and Requirements Component Maximum Current Draw (ma) Current Draw after 4 hours (mah) Teensy 3.5 60 240 BMP280 1.12 4.48 BNO055 12.3 49.2 Micro SD Card (onboard Teensy) 50 200 Total 123.42 493.68 Battery: Lithium-Ion Polymer More compact and dense compared to NiMH Rated capacity: 1200 mah
DDABS: Software
DDABS: Interior Bay Rail-Sled system will be implemented instead of metal rods Avionics sled will hold all electronic components and batteries for DDABS Materials: plywood, aluminum rails, assorted Ease of access plastics, epoxy glue Batteries mounted on bottom, flight computer mounted on top Total Dimensions of sled: 1.47 inches tall, 3.37 inches wide, and a depth of 5 inches
Safety Overview
Safety Team Safety Officer Alex Sommers Responsibilities Compilation and maintenance of records of material safety data sheets hazard analysis risk mitigation methods Ensuring completion of safety and lab trainings Compliance with laws, policies, regulations
Personnel Hazard Analysis Analyzes the all possible risks to personnel Includes severity ranking and planned mitigation
Environmental Hazard Analysis Examines How the rocket can affect the environment How the environment can affect the rocket. Same format as PHA
Failure Modes and Effects Analyses Analyses to recognize and evaluate possible failures in order to mitigate all possible risks to acceptable probability levels. Conducted FMEA for rocket, payload, and avionics subsystems
Safety Manual Separate document containing: Build procedures Safety Guidelines NRA/TRA, FAA, and EPA regulations Local, state, and federal laws for high-powered rocketry Launch procedures Lab safety manual MSDS
Payload Overview
Payload Mission Success Criteria Handle in-flight forces during launch Handle landing impact forces with no damage to mechanical or electronic components Deploy from payload bay upon the receipt of manual trigger from base Drive ten feet (or more) from landing site Collect ten milliliters (or more) of soil after driving ten feet from landing site
Payload Deployment Subsystem Servo w/ disk and pins Minimum of six 4-40 Nylon Shear Pins as backup retention Black Powder Piston Ejection System Stiff, flexible material
Preliminary Payload Design Unique, side-oriented design Expanding drive train that doubles as orientation mechanism Aluminum chassis design that conforms to existing mechanism No component exists beyond a 1.75 in radius of the center of the rover Tentative weight: 2.16 lb
Soil Collection Mechanism consists of an scoop attached to a Servo Scoop made of aluminum Micro Servo MG90S Servo will lower scoop into ground Soil will be collected via driving forward Scoop will also double also double as the soil container Scoop will be raised into a cap within the chassis Tentative weight estimate:.107 lbs or 1.71 oz
Drivetrain Small rocket diameter 3-3.75 limits drivetrain size Treads fold out to support rover and orient Two sided timing belt used for grip Powered by HiTEC HS - 485HB servos and 12V DC Motor Electronic components protected by triangular aluminum support Tentative weight: 1.32 lb
Drivetrain Rigid support system for servos and treads Pulleys attached to treads are free spinning on shaft Motors are free spinning as well; attached to pulleys Supports only attached to servo Solves problem of stationary treads and moving motor on same shaft
Chassis The chassis will be made of 6061 aluminum The chassis will hold all the electrical components of the rover The pieces of the chassis will be machined and then fastened together Triangular design Tentative weight: 0.51 lb
Payload Electronics Pixhawk 4 GPS Rangefinder Transmitter and receiver Motor Servo Power rail Battery
Pixhawk 4 Open-hardware controller Contains enough ports for all electronic connections Capable of providing autopilot to the rover Utilizes the ArduRover software User-friendly interface Reliable results Open source
GPS Pixhawk 4 GPS Module Specifically designed for compatibility with the Pixhawk 4 Combined GPS and compass Embedded safety switch
Rangefinder TFMini - Micro LiDAR Module 12in to 39ft range detection Wide angle of view Time of Flight LiDAR
Transmitter and Receiver Micro Transceiver Telemetry Radio Set Used to start the rover after the rocket lands Ground control transmitter and rover receiver Configurable through ArduRover Mission Planner
Motor Brushless DC Motor with Encoder Used to move the treads Build-in motor driver Directional control, pulse-width modulation speed control and speed feedback output Small in size
Servo Drivetrain HiTEC HS-485HB Capable of supplying enough torque to control the folding tread system Soil Collection Micro Servo - MG90S High Torque Metal Gear Capable of supplying enough torque to control the scoop
Power Rail HobbyKing Matek Micro PDB w/bec (5V and 12V) Used to distribute power from the battery to the motors and servos Contains four ESC
Payload: Deployment Adafruit Feather M0 with RFM95 Radio https://www.adafruit.com/product/3178 Adafruit Ultimate GPS selected for our design. Used to communicate to ground station Receive commands for rover deployment License free signal (920MHz): does not require amateur radio certification. Small size: Will report the current coordinates at a rate of 1Hz Stacks with Feather Dual radio deployment for rover Deactivate failsafe servo for payload housing Deploy rover using controlled charge? https://www.adafruit.com/product/3133
Payload Battery Budget Rover Battery Budget Estimation Mission Stage Component Pixhawk 4 Standby Max Current Draw (ma) Run Time (hr) Quantity Power Density (mah) 100 1 2.000 200.000 GPS 0 1 2.000 0.000 Rangefinder 0 1 2.000 0.000 25 1 2.000 50.000 Motor 0 2 2.000 0.000 Servo 8.8 5 2.000 88.000 Power Rail 25 1 2.000 50.000 Receiver
Payload Battery Budget (cont.) Rover Battery Budget Estimation Mission Stage Component Pixhawk 4 System Boot Max Current Draw (ma) Run Time (hr) Quantity Power Density (mah) 2500 1 0.013 31.250 GPS 500 1 0.013 6.250 Rangefinder 250 1 0.013 3.125 25 1 0.013 0.313 Motor 700 2 0.013 17.500 Servo 600 5 0.013 37.500 Power Rail 100 1 0.013 1.250 Receiver
Payload Battery Budget (cont.) Rover Battery Budget Estimation Mission Stage Component Pixhawk 4 Mission Execution Max Current Draw (ma) Run Time (hr) Quantity Power Density (mah) 2500 1 0.167 416.667 GPS 500 1 0.167 83.333 Rangefinder 250 1 0.167 41.667 25 1 0.167 4.167 Motor 700 2 0.167 233.333 Servo 600 5 0.167 500.000 Power Rail 100 1 0.167 16.667 Total 1,781.0208 Receiver
Battery Blomiky 11.1V 3S 2200mAh LiPo Battery Easily capable of powering all the electronics in case of launch delays Pixhawk recommends LiPo batteries for power Rechargeable
Payload Preliminary Weight Buildup
Requirements Compliance Plan
Requirements Compliance Plan List of all NASA requirements for SLI competition and how we plan to achieve them. Table is included in PDR and each verification plan Is classified with a verification method.
Requirements Compliance Plan (cont.) List of team derived requirement List for each sub-team
Questions?