Preliminary Design Review. Cyclone Student Launch Initiative

Transcription

1 Preliminary Design Review Cyclone Student Launch Initiative

2 Overview Team Overview Mission Statement Vehicle Overview Avionics Overview Safety Overview Payload Overview Requirements Compliance Plan

3 Team Structure

4 Team Organization

5 Website & Social Facebook: ISUcysli Instagram: cyclonestudentlaunchinitiative

6 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.

7 Vehicle Overview

8 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.

9 Vehicle Dimensions 11 feet 2 inches long lbs with motor (20.7 lbs without) 4 Outer Diameter

10 OpenRocket Diagram Main Parachute Bay Nose Cone & Fore Altimeter Bay Payload Bay Aft Altimeter Bay Drogue Bay Motor Mount Avionics Bay

11 Stability CG: 90.4 from nose cone CP: 102 from nose cone Stability Margin: 2.8 cal

12 Mass Statement Independent Sections under Drogue: Independent Sections under Main: Motor Mount: 8.47 lbs Motor Mount: 8.47 lbs Rest of Rocket: 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)

13 Performance Predictions Rail exit velocity 99.6 fps Maximum velocity 756 fps Maximum acceleration 614 ft/s^2 Apogee: 5641 ft

14 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

15 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

16 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

17 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

18 Motor Selection AeroTech K1999N-P Average Thrust: 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

19 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 mph mph mph 2495

20 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

21 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

22 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

23 Avionics Overview

24 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

25 DDABS: Electrical Hardware

26 DDABS: Flight Computer Comparison Results Teensy Raspberry Pi 3 B Arduino Mega Criteria Processor Speed Physical Size Ease of Use All Consistency Indices are below the.1 standard

27 DDABS: Flight Computer Hardware Teensy 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

28 DDABS: Hardware Configuration

29 DDABS: Battery and Requirements Component Maximum Current Draw (ma) Current Draw after 4 hours (mah) Teensy BMP BNO Micro SD Card (onboard Teensy) Total Battery: Lithium-Ion Polymer More compact and dense compared to NiMH Rated capacity: 1200 mah

30 DDABS: Software

31 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

32 Safety Overview

33 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

34 Personnel Hazard Analysis Analyzes the all possible risks to personnel Includes severity ranking and planned mitigation

35 Environmental Hazard Analysis Examines How the rocket can affect the environment How the environment can affect the rocket. Same format as PHA

36 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

37 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

38 Payload Overview

39 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

40 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

41 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

42 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

43 Drivetrain Small rocket diameter 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

44 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

45 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

46 Payload Electronics Pixhawk 4 GPS Rangefinder Transmitter and receiver Motor Servo Power rail Battery

47 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

48 GPS Pixhawk 4 GPS Module Specifically designed for compatibility with the Pixhawk 4 Combined GPS and compass Embedded safety switch

49 Rangefinder TFMini - Micro LiDAR Module 12in to 39ft range detection Wide angle of view Time of Flight LiDAR

50 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

51 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

52 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

53 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

54 Payload: Deployment Adafruit Feather M0 with RFM95 Radio 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?

55 Payload Battery Budget Rover Battery Budget Estimation Mission Stage Component Pixhawk 4 Standby Max Current Draw (ma) Run Time (hr) Quantity Power Density (mah) GPS Rangefinder Motor Servo Power Rail Receiver

56 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) GPS Rangefinder Motor Servo Power Rail Receiver

57 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) GPS Rangefinder Motor Servo Power Rail Total 1, Receiver

58 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

59 Payload Preliminary Weight Buildup

60 Requirements Compliance Plan

61 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.

62 Requirements Compliance Plan (cont.) List of team derived requirement List for each sub-team

63 Questions?