NASA USLI 2020 Preliminary Design Review Presentation University of - PowerPoint PPT Presentation

NASA USLI 2020 Preliminary Design Review Presentation University of Alabama in Huntsville November 12th, 2019 1

2019-2020 CRW Team Faculty Advisor Mentor Faculty Advisor Bao Ha Jason Winningham David Lineberry Project Engineer Nick Roman Social Media & Chief Engineer Safety Officer Outreach Josh Jordan Jessy McIntosh Will Snyder Vehicle Safety Vehicle Lead Deputy Peter Martin Maggie Hockensmith Payload Safety Payload Lead Deputy James Venters Claudia Hyder Introduction - Nick Roman 2

2019-2020 CRW Team Team Detail ● 20 Students participating as part of UAH Senior Rocket Design Course - 1 Mentor - 1 Instructor - 8 Mechanical Engineers - 12 Aerospace Engineers ● 3 Students with prior rocketry experience through NAR Level Certifications Introduction - Nick Roman 3

Presentation Agenda ● Introduction - Team Introduction, Mission Statement, & Mission Objectives ● Vehicle - Upper Airframe, Lower Airframe, Recovery System, Mission Performance and Flight Trajectory, Subscale Rocket ● Payload - Chassis, Powertrain, Sample Recovery, Mass Budget, Deployment, Electronics, Test Plans ● Safety - Safety Officer, Safety Deputies, Analysis Matrix, Risk Assessment ● Management - Schedule, Budget, Outreach, & Requirements Validation ● Questions Introduction - Nick Roman 4

Mission Statement To give students an opportunity to gain experience with high-powered rocketry via the year-long system life cycle and share the knowledge gained with NASA and those in our communities through outreach programs. Introduction - Nick Roman 5

Mission Objectives This project consists of a series of objectives UAH will complete according to NASA requirements and derived requirements. ● Design and manufacture a vehicle that will deliver the payload to and altitude of 4500 feet above ground level ● Test various aspects of the vehicle and payload to ensure functionality ● Launch subscale and full-scale rockets prior to competition date ● Complete payload mission on competition day according to NASA requirements Introduction - Nick Roman 6

Vehicle Lead: Peter Martin Safety Deputy: Maggie Hockensmith 7

Vehicle Team Introduction Top-Level Requirements Vehicle Lead ● Vehicle shall reach an Peter Martin apogee of 4500 ft within ± 250 ft ● Launch Vehicle will Motor Simulations accelerate to a minimum Recovery Retention Roman Benetti Jeremy Hart velocity of 52 ft/s off the Jacob Zilke rail ● Each independent section of the launch vehicle will have Fin Design Material Electronics a maximum kinetic energy Rachel O’Kraski Rodney Luke Ben Lucke of 75 lb-ft at landing Status ● Trade studies conducted ● Preliminary designs for recovery, tracking, avionics, motor retention, fins, body tubes, and motor ● Preliminary test plan outlined ● Requires further analysis Vehicle - Peter Martin 8

Vehicle Characteristics Configuration 1 Vehicle - Peter Martin 9

Vehicle Characteristics Cont. Configuration 2 Vehicle - Peter Martin 10

Launch Vehicle Concept of Operations Con-Ops Diagram Vehicle - Peter Martin 11

Upper Airframe Overview Overview ● 24 in 4:1 Ogive nose cone ● 55 in upper airframe body tube length for configuration 1 ● Major inner diameter of 6 in ● Houses payload bay and main parachute (configuration 1) ● Tracker housed in nose cone ● Forward rail button located 66.5 in from tip of nose cone ● Configuration 1 diagram shown below Payload Main Parachute 6in Shoulder Rail Button Tracker Configuration 1 Upper Airframe Diagram Avionics Vehicle - Peter Martin 12

Upper Airframe Overview Cont. Overview ● 35 in upper airframe body tube length for configuration 2 ● Houses payload bay only ● Tracker housed in nose cone ● Configuration 2 diagram shown below Tracker 6in Shoulder Payload Configuration 2 Upper Airframe Diagram Vehicle - Peter Martin 13

Lower Airframe Overview Overview ● 40 in lower airframe length ● Major inner diameter of 6 in ● Houses drogue, avionics, and propulsion system ● 4 fins mounted with individual brackets ● Aft motor retention with thrust plate ● Configuration 1 diagram shown below Rail Button Drogue Parachute Motor Case Avionics Motor Configuration 1 Lower Airframe Diagram Vehicle - Peter Martin 14

Lower Airframe Overview Cont. Overview ● 60 in lower airframe length ● Houses main parachute, drouge, avionics, and propulsion system ● Forward rail button located 67 in from tip of nose cone ● Configuration 2 diagram shown below Rail Button Motor Case Drogue Main Avionics Parachute Parachute Configuration 2 Lower Airframe Diagram Motor Vehicle - Peter Martin 15

Motor Retention Design ● Threaded retention ring ● Screws into thrust plate ● Purchased from Apogee rockets Retention ● Reloadable motor case Ring Cap Load Path Threaded ● Boost Retention - Motor Case Ring - Thrust plate - Body tube ● Coast Thrust Plate - Retention cap holds motor Alternatives Considered Motor Retention ● Forward retention Assembly ● Snap ring ● Retention plate Vehicle - Peter Martin 16

Fin Assembly Design Fins ● Material G-10 fiberglass sheet ● Fabricate in house ● Fixed to bracket with 4 bolts or screws (each) and 4 nuts (each) ● 4 trapezoidal fins ● Shape determined by OpenRocket Brackets ● Contain 4 brackets ● Full Scale: Connect to the body tube using 8 bolts or screws (each) and 8 nuts (each) Fin Assembly ● Subscale: Connect to the body tube using epoxy ● Fabricated in house using ABS plastic Alternative Considered ● Fin Can Design Vehicle - Peter Martin 17

Recovery Overview Recovery is in the process of determining the exact method to be used for the full-scale rocket ● Trade study done between a traditional recovery system or a system implementing a tender descender ● Trade study done between the payload having its own parachute for deployment or being attached to the main parachute of the rocket Parachute Tender Descender Vehicle - Jeremy Hart 18

Recovery Comparison Commonalities ● Drogue - Deploys at apogee - Fruity Chutes CFC-24 (CD = 1.5) - Recovery Harness: Tubular Nylon ● Main - Deploys at 600 feet above ground level - Fruity Chutes IFC-84 (CD = 2.2) if payload has own chute Tender-Descender - Fruity Chutes IFC-96 (CD = 2.2) if payload connected to main - Recovery Harness: Tubular Nylon Primary Differences ● Tender Descender - Drogue connected to the tender descender and upper airframe - Main connected to the tender descender and lower airframe ● Traditional - Drogue connected to the lower airframe - Main connected to the upper airframe Traditional Vehicle - Jeremy Hart 19

Drift and KE Calculations Drift Analysis ● Assumptions - Apogee is over launch rail - Horizontal wind speed is constant and unidirectional ● Max drift with 20 MPH wind is 2134 feet Kinetic Energy Analysis ● Estimated mass; calculations will be more accurate as mass is refined later. ● Lower Airframe hits ground first, reducing effective weight for succeeding sections ● Terminal velocity of vehicle is 12.77 ft/s and 19.3 ft/s for payload Body Section Mass (lbm) Kinetic Energy at Touch Down (ft-lbf) Upper Airframe 12.29 31 Lower Airframe 17.48 44 Payload 8.4 45 Vehicle - Jeremy Hart 20

Tracking Tracking ● CRW-developed XBee-Pro S3B with Antenova GPS ● Transmission distance up to 6 miles using free program called X-TCU ● Powered by CR123 3V Lithium Ion Battery ● Housed in nose cone, operates independently of main avionics ● Transmission frequency between 902 and 928 MHz XBee-Pro S3B Tracker Tracker with Antenna Vehicle - Jeremy Hart 21

Avionics Mounting Assembly Avionics ● Eye bolt on forward and aft bulkhead for chute shock cords ● 4x switch/port holes - SPST key switch for arming/disarming altimeters ● 2 Stratologger CF altimeters with discrete Key Switch power supplies ● 8x circuit barrier strips for quick starter connection to Stratologger CF altimeters ● 4x PVC wells for redundancy in chute deployment - redundant charge 115% size of original charge Avionics Housing Avionics Housing Vehicle - Jeremy Hart 22

Selected Motor Aerotech 1420R Hardware RMS-75/5120 Single-Use/Reload/Hybrid Reloadable Total Impulse (lbf*s)/(N*s) 1035/4603 Propellant Weight (lbm) 5.64 Loaded Weight (lbm) 12.30 Weight After Burnout (lbm) 6.66 Maximum Thrust (lbf) 408 Average Thrust (lbf) 319 Burn Time (s) 3.2 Vehicle - Peter Martin 23

Flight Profile Profile ● Maximum Speed: 553 ft/s Maximum Acceleration: 208 ft/s 2 , ● 6.46 g’s ● Apogee: 4427 ft ● Time to Apogee: 17.3 s Stability ● Static margin of 2.13 off the rail ● Calculated using average weather and launch day conditions - Average wind speeds of 5-6 MPH - Rail length 12 feet ● Values will change as the rocket mass estimates become better Vehicle - Peter Martin 24

Subscale Overview ● Producing two subscale rockets allowing all team members to participate and gain experience ● Intended to replicate the full scale rocket’s drag, CG, and CP ● Targeting November 9th launch date Vehicle - Peter Martin 25