CRITICAL DESIGN REVIEW. University of South Florida Society of Aeronautics and Rocketry
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1 CRITICAL DESIGN REVIEW University of South Florida Society of Aeronautics and Rocketry
2 AGENDA 1. Launch Vehicle 2. Recovery 3. Testing 4. Subscale Vehicle 5. Payload 6. Educational Outreach 7. Safety 8. Project Plan
3 1. LAUNCH VEHICLE
4 LAUNCH VEHICLE AND PAYLOAD DIMENSIONS Diameter Length Projected Unloaded Weight Projected Loaded Weight (min ballast) Estimated Max Payload Weight Estimated Max Payload Length 5:1 Von Karman Nosecone 25 long, OD: in 111 in 27.2 lbs 37.3 lbs 10 lbs 15 in Booster Section 36 long OD: Rover Compartment Airframe long, OD: 5.148
5 KEY DESIGN FEATURES Aerotech L mm Motor Four Sections Nosecone Rover Compartment Main Altimeter Bay Booster Section Recovery One parachute for rover compartment and nosecone One parachute and one drogue for Main Altimeter and Booster Section Adjustable Ballast System Removable Ballast for Nosecone shoulder to manipulate flight path and apogee to launch day conditions Payload Deployable Rover
6 FINAL MOTOR SELECTION Aerotech L1420 Average Thrust 1420 N Maximum thrust 1814 N Total Impulse 4603 Ns Burn Time 3.2 s Case Info CTI Pro75-4G
7 ROCKET FLIGHT STABILITY Due to adjustable ballast system the stability has been calculated at minimum and maximum possible weight Configuration with Aerotech L1420 Ballast Max (2.71 lbs) Min (.375 lbs) Center of Pressure in inches Center of Gravity in inches Calibers 3.66 in 3.14
8 ROCKET FLIGHT STABILITY Maximum Ballast C G C P Minimum Ballast C G C P
9 FLIGHT CHARACTERISTICS Ballast Projected Apogee Minimum 6695 ft Thrust-to-Weight Ratio 9.12:1 Max Velocity Max Acceleration Exit Rail Velocity Exit Rail Stability 793 fps 298 fps^ fps 3.2 cal
10 MASS STATEMENT & MASS MARGIN System Name Projected Weight (pounds) Loaded Rocket (motor & max ballast) Nosecone (bulkhead & minimum ballast configuration) 2.99 Rover Compartment (airframe, payload altimeter bay & rover) Booster Section (airframe, motor mount & recovery equipment) Main Altimeter Bay (G12 coupler, bulkheads, altimeters & recovery equipment) Parachutes Aerotech 75mm L1420 Motor (Total / Propellant) 10.1
11 ADJUSTABLE BALLAST SYSTEM Loaded in either or both the Nosecone and/or the Main Altimeter Bay Layered modular elements Dimensions:.4 height Same diameter as launch vehicle Weight range of 1-74 ounces
12 Section 1 4 ounces per layer Section 2 6 ounces per layer Section 3 Holds no weights Final Assembly 14 stackable sections
13 Wind Speed (mph) Total Ballast Weight (pounds) Altitude Predictions with Various Ballast Projected Apogee (feet) Wind Speed (mph) Total Ballast Weight (pounds) Projected Apogee (feet)
14 2. RECOVERY
15 RECOVERY OVERVIEW 1. Drogue parachute: Attached to shock cord that is attached to a U-bolt 2. Booster Section parachute: Attached to shock cord that is attached to a U- bolt 3. Rover Compartment parachute: Directly attached to nosecone U-bolt and Payload Altimeter Bay U-bolt 3 2 1
16 Name SkyAngle Classic II 60 Recovery Fruity Chutes Iris Ultra 36 HP Compact Chute 20 inch SkyAngle Classic II drogue Deployed at 800 ft 950 ft Apogee Material Zero-porosity 1.9 oz. silicone-coated balloon cloth Lightweight 1.1oz Mil-spec calendared ripstop nylon Zero-porosity 1.9 oz. silicone-coated balloon cloth Surface Area (sq ft) Drag Coefficient Number of Lines Line Length (in) Line Material 3/8 tubular nylon (950 lbs) 1/4" Kevlar and 400# Spectra Nanoline 3/8 tubular nylon (950 lbs) Attachment Type Heavy-duty 1,500 lb. size 12/0 nickel-plated swivel No swivel, plan to purchase and equip a 500# ball bearing swivel Heavy-duty 1,500 lb. size 12/0 nickel-plated swivel Descent Rate (fps)
17 DRIFT ANALYSIS Booster Section and Altimeter Total descent time of 83 seconds Nosecone and Rover Compartment Total descent time of 84 seconds Booster Section and Altimeter Nosecone and Rover Compartment Wind Speed (mph) Wind Speed (ft./s) Drift (ft.) Wind Speed (mph) Wind Speed (ft./s) Drift (ft.)
18 KINETIC ENERGY Drogue Deployment Main #1 Deployment Main #2 Deployment Kinetic Energy at Key Phases (ft lbs) Nosecone Rover Compartment Main Altimeter Bay Booster Section Touchdown
19 3. TESTING
20 Test Plan Type of test Reason Status Subscale Ground Test Subscale Launch Full Scale Ground Test Full Scale Launch 1 Full Scale Launch 2 Rover Drop Test To ensure enough black powder is used to successfully eject the components out of the airframe To ensure all systems perform as expected and verify that rocket can be recovered and reused To ensure enough black powder is used to successfully eject the components out of the airframe To ensure all systems perform as expected and verify that rocket can be recovered and reused and that the rocket can reach apogee of 5,280 feet To test payload deployment system reliability and performance as well as vehicle reliability with equipped rover Simulate vehicle landing by placing rover in fiberglass tube and testing impact forces at various drop angles and heights Complete d on 12/16/17 Complete d on 12/16/17 1/20/18 1/20/18 2/17/18 TBD Mobility Test Test mobility of rover on various terrain types and slopes TBD
21 4. SUBSCALE VEHICLE
22 SUBSCALE VEHICLE SUMMARY Components of the subscale model were resized to replicate a 4:5 diameter ratio: Launch Vehicle Diameter - 4 wide, 80% width of full scale Main Altimeter Bay - 8 long, 80% length of full scale Booster Section airframe - 30 long, 83% length of full scale Rover Compartment airframe - 39 long, 85% length of full scale Nose cone length - 20 long, 80% length of full scale Weight of Launch Vehicle lbs, 63% weight of full scale Thrust to Weight Ratio :1, as close to the thrust to weight ratio of the full scale, which was, at the time of subscale launch, 8.6:1 Launched twice on December 16 th 2017 at Varn Ranch
23 SUBSCALE RECOVERY Drogue Skyangle 30 Main Rover Compartment and Nosecone SkyAngle Cert 3 Large Main Alt Bay and Booster Section SkyAngle Cert 3 Medium Altimeter Main alt bay 2 Missile Works RRC3 (at apogee and 1000ft) Payload alt bay 2 Atlus Metrum Easymini (at 1000ft)
24 SUBSCALE FLIGHT SIMULATION Subscale Launch Simulation Minimal cloud cover 4mph winds 69.8 degrees Fahrenheit.04 psi Apogee Time to Apogee Max Velocity Max Acceleration Ground Hit Velocity Total Flight Time 3456 ft 14.9 s 505 fps 246 fps 10.4 fps 161 s
25 SUBSCALE GROUND TEST Ground Test for Nosecone Section Ground Test for Booster Section
26 LAUNCH #1 Subscale Launch #1 Analysis Motor Apogee Time to Apogee Max Velocity Descent Rate Total Flight Time Cesaroni 4G 54mm K ft 13.7 s 401 fps 33 fps 86.3 s
27 LAUNCH #1 ALTIMETER DATA
28 LAUNCH #1 RECOVERY Drogue and Rover Compartment Main parachute deployed successfully Main Altimeter Bay shear pins (4 x 4-40) did not break completely Main Altimeter Bay and Rover Compartment did not separate Main parachute for Booster Section and Main Altimeter Bay did not deploy
29 LAUNCH #2 Subscale Launch #2 Analysis Motor Apogee Time to Apogee Max Velocity Descent Rate Total Flight Time Cesaroni 4G 54mm K ft 12.3 s 362 fps 24 fps 79.2 s
30 LAUNCH #2 ALTIMETER DATA
31 LAUNCH #2 RECOVERY Drogue and Rover Compartment Main deployed successfully Changed Main Altimeter Bay shear pins to 2 x 4-40 Main Altimeter Bay and Rover Compartment separated Shock cord entanglement and overly compact parachute storage prohibited successful deployment for Main Altimeter Bay and Booster Section Main
32 LAUNCH #2 RECOVERY CONTINUED
33 5. PAYLOAD
34 PAYLOAD SUMMARY Max Weight Height Max Length Motor Projected Motor Run Time Stall Torque 10 lbs 4.8 in 12 in 12V Brushed DC 53 min 42 kg-cm
35 DEPLOYMENT SYSTEM ELECTRONICS Two XBee RF transceivers Base station One XBee transceiver Computer connected by USB Onboard deployment system One XBee transceiver connected to a shield designed to be attached to an Arduino Manual switch used for backup activation method
36 PAYLOAD DEPLOYMENT SYSTEM Different design then PDR Sled and winch system
37 PAYLOAD INTERFACES Loading the Payload Situated on a precisely designed sled intended to discourage vertical movement and spinning within the rocket Rover and deployment system are located aft the Payload Altimeter Bay Payload Deployment Deployment system will start via a connection from a high gain antenna from a remote laptop to the microcontroller and Arduino inside the system Once activated the rover will move in a forward motion to exit open end of Rover Compartment Airframe
38 6. SAFETY
39 KEY SAFETY ISSUES
40 KEY SAFETY ISSUES
41 KEY SAFETY ISSUES
42 KEY SAFETY ISSUES
43 7. PROJECT PLAN
44 BUDGET AND FUNDING USF Student Government Funding $7,500 Total $7,500 Budget Rocket Materials $1,000 Launch Motors $400 Test Launch Motors $800 Subscale Materials $600 Subscale Motor $350 Payload $800 Miscellaneous Hardware $400 Travel $1,500 Total $5,850
45 REQUIREMENTS VERIFICATION STATUS NASA General Requirements Complete 14 NASA Vehicle Requirements Complete 18 Awaiting Completion 0 Awaiting Completion 8 NASA Recovery Requirements Complete 12 NASA Experiment Requirements Complete 2 Awaiting Completion 1 Awaiting Completion 4 NASA Safety Requirements Complete 4 Team Requirements Complete 0 Awaiting Completion 1 Awaiting Completion 9
46 TIMELINE PDR TO CDR Main tasks completed between PDR and CDR Subscale construction Subscale testing Subscale launch Finalize full scale design Finalize payload deployment system design Prototype rover construction
47 TIMELINE CDR TO FRR Tasks to complete before the Final Review Report: Full scale construction Full scale testing Full scale launch Rover prototype construction Deployment system fabrication Rover programming Final rover fabrication Rover testing
48 8. EDUCATIONAL OUTREACH
49 OUTREACH OVERVIEW 10/13 planned events completed 3 upcoming events - 1 TBD, 1 in January, 1 in February Reached 911 participants Student Count Table NASA Requirement Team Requirement Required Amount Amount needed to reach requirement Verification Status 0 89 COMPLETE
50 QUESTIONS?
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