Flight Readiness Review Presentation THE UNIVERSITY OF MISSISSIPPI ROCKET REBELS UNIVERSITY STUDENT LAUNCH INITIATIVE
The Launch Vehicle 3/9/2017 2016-2017 USLI FLIGHT READINESS REVIEW 2
Vehicle Layout and Dimensional Data Structure and Propulsion Total Length 105 in Outer Diameter 6.2 in Dry Weight 32.34 Wet Weight 36.94 lb Motor Choice Loki Research L840CT Motor Impulse 3888 Ns Average Thrust 844 N Burn Time 4.6 sec Drogue Chute Design: Recovery System Hemispherical Main Chute Design Annular w/ Pilot Chute Drogue Chute Diameter 26 in Main Chute OD-ID 9.7 ft 5.93 ft 3/9/2017 2016-2017 USLI FLIGHT READINESS REVIEW 3
Structural Materials Item Airframe Bulkheads Centering Rings and Fins Nose Cone Couplers and Motor Mount Tube Avionics Sled Material HexPly 6376 Prepreg Carbon Fiber/Resin Sheet 5H Plain Weave Carbon Fiber Plate Stock ABA Plastic Filament ABA Plastic Filament Blue Tube ABA Plastic Filament 3/9/2017 2016-2017 USLI FLIGHT READINESS REVIEW 4
Body Tube Specifications Body Tube Section Lengths Fiber Orientation 100% handmade carbon fiber airframe Section Length (inches) Ply Layer Payload Bay 18.5 Ply #1 (28 mil) Main Bay 37 Ply #2 (28 mil) Avionics Ring 3 Ply #3 (14 mil) Drogue Bay 24 Booster 18 Orientation 0 Degrees +45 Degrees 90 Degrees Two thick inner plies serve for structural integrity in both normal and shear stress Thin outer ply allows for smooth outer surface that allows for uniform powder coat Caul plate made prior to airframe layup to ensure smooth outer surface 3/9/2017 2016-2017 USLI FLIGHT READINESS REVIEW 5
Features and Dimensions Fin Specifications Type Root Chord Tip Chord Sweep Length Height Trapezoidal 9 in 4.5 in 2.25 in 7.5 in Nose Cone Specifications Nose cone shape Length Wall thickness Nose cone material Base Diameter Shoulder Length Tangent Ogive 8 in.25 in ABA plastic filament 6.2 in 1.5 in 3/9/2017 2016-2017 USLI FLIGHT READINESS REVIEW 6
Motor Mount Assembly Blue tube motor mount tube Will house 75mm motor Features a 3-finned configuration 2 part retainer assembly Metal ring mounts to aft centering ring Polymer screw on cap 3-D printed Fin Configuration Includes fillets and centering rings Will print contours and sleeve to fit motor housing 3/9/2017 2016-2017 USLI FLIGHT READINESS REVIEW 7
Motor Description Loki Research L840 Cocktail High quality motor with easy assembly Relatively low average thrust and long burn time Ensures minimal stress on the payload. Motor Impulse Max Thrust Avg. Thrust Burn Time 3888 Ns 1190 N 844 N 4.6 s 3/9/2017 2016-2017 USLI FLIGHT READINESS REVIEW 8
Stability Margin Stability Margin vs. Time 4.5 4 3.5 3 2.5 2 1.5 1 0.5 0 3.1816 at 0.4 s Launch Rail Exit 3.9792 at 4.8212 s Motor Burnout Time (s) 3/9/2017 2016-2017 USLI FLIGHT READINESS REVIEW 9
Additional Data THRUST TO WEIGHT RATIO Wet Weight of Rocket: 36.94 lbf Average Thrust of Motor: 844 N = 190 lbf Thrust to Weight Ratio: 5.14 RAIL EXIT VELOCITY Provided through OpenRocket simulation software: 63.7 ft/s Rail exit velocity is above the 52 ft/s threshold. 3/9/2017 2016-2017 USLI FLIGHT READINESS REVIEW 10
Mass Statement Booster Section (Body and Coupling Tube, Ballast 2, Fins, Motor Mount Assembly w/ motor) Avionics Section (Main and Drogue Body Tube, Avionics Bay and Sled, Drogue Chute Package) Payload Section (Nose Cone, Payload Body Tube and Coupler, FMPA, Ballast 1, and Main Parachute Package) Total 226 oz (Pre-burnout) 153 oz (Post-burnout) 190 oz 175 oz 591 oz (36.625 lb) Pre-burnout 518 oz (32.063 lb) Post-burnout 3/9/2017 2016-2017 USLI FLIGHT READINESS REVIEW 11
Kinetic Energy Calculations Section Weight (lbf) Kinetic Energy at Main Parachute Deployment Kinetic Energy on Ground Impact (ft-lbf) (ft-lbf) Booster Section (postburnout) 9.56 608.04 43.91 Avionics Section 11.88 755.59 54.6 Payload Section 10.94 695.8 50.26 Drogue Descent Speed 70 ft/s Main Descent Speed 20 ft/s 3/9/2017 2016-2017 USLI FLIGHT READINESS REVIEW 12
Drift Predictions Wind Speed (mph) Lateral Drift Distance (ft) Predicted Altitude (ft) 0 9 5279 5 100 5248 10 220 5192 15 355 5051 20 640 4948 3/9/2017 2016-2017 USLI FLIGHT READINESS REVIEW 13
Recovery Expectations and Parachute Sizing Projected Drogue Descent Speed 70 fps Projected Main Descent Speed 20 fps Hemispherical Drogue Parachute Canopy Annular Main Parachute Canopy Led by Small Pilot Chute Attached to 7/8 tubular nylon shock cord Grommets control deployment speed to reduced chance of ripping Drogue Parachute Configuration Hemispherical Main Parachute Configuration Drogue Parachute Diameter 26 in Main Parachute Outer Diameter Drogue Suspension Line 39 in Main Parachute Vent Length Diameter Shock Cord Length 30 ft Main Parachute Canopy Height Shock Cord Material 7/8 Tubular Nylon Main Suspension Line Length Annular with Pilot Chute 9.7 ft 5.93 ft 2.95 ft 12.125 ft 3/9/2017 2016-2017 USLI FLIGHT READINESS REVIEW 14
Avionics Schematics and Ejection Specs. Primary Altimeter PerfectFlite StratoLoggerCF Drogue Bay Volume 466.95 in 3 Backup Altimeter Missile Works RRC3 Xtreme Main Bay Volume 778.25 in 3 Shear Pin Type 4-40 Nylon Drogue Black Powder Mass 1.81 g (rounded to 2 g) Shear Pins per Separation Point 3 Main Black Powder Mass 3.04 g (rounded to 3.5 g) Shear Strength of Pins 50-76 psi 3/9/2017 2016-2017 USLI FLIGHT READINESS REVIEW 15
Packing and Harnesses ¼ Steel Quick Links, ¼ swivel links, and 3/8 U-bolts serve as attachment points for shock cord and risers Canopy packed in deployment bags; suspension lines and risers packed in sleeve outside bag PAI-C-7219B type III para-pak cloth Packages shielded from ejection charge gases with 18 Nomex blankets 3/9/2017 2016-2017 USLI FLIGHT READINESS REVIEW 16
Recovery System Testing 3/9/2017 2016-2017 USLI FLIGHT READINESS REVIEW 17
1st Presidium Full-Scale Test Flight 3/9/2017 2016-2017 USLI FLIGHT READINESS REVIEW 18
Footage 3/9/2017 2016-2017 USLI FLIGHT READINESS REVIEW 19
Actual vs Projected Flight Data 3/9/2017 2016-2017 USLI FLIGHT READINESS REVIEW 20
Additional Data Retrieved 3/9/2017 2016-2017 USLI FLIGHT READINESS REVIEW 21
Projected vs. Actual Data and Error Analysis Simulated Flight Data Actual Flight Data Percent Difference Apogee (ft) 6242 6234.1% Max Velocity 715 720.7% (fps) Max 254 260 2.3% Acceleration (ft/s 2 ) Flight Time (s) 134 160 17.7% Drogue 81.1 57.2 34.6% Descent Speed (fps) Main Descent Speed (fps) 16.2 17.4 7.1% Drogue Descent Speed Manufacturer s predictions more accurate Estimated 65 (fps) Successful Flight Vehicle left the pad and came back undamaged FMPA was undamaged No cargo was flown Initial Altitude Discrepancy Fin Design Solution: Ballasts 6.5 lbs 3/9/2017 2016-2017 USLI FLIGHT READINESS REVIEW 22
FMPA Payload Fragile Material Protection Apparatus Hydraulic system of shock absorbers Houses inner capsule filled with packing peanuts Simple yet functional design, outer and inner ring assembly Easy accessibility, screw off top and large outer ring opening Success Criteria: FMPA can be installed within payload bay Fragile cargo can be easily loaded within FMPA FMPA cargo survives entirety of vehicle flight FMPA and cargo are recoverable. FMPA is reusable. 3/9/2017 2016-2017 USLI FLIGHT READINESS REVIEW 23
Payload Integration FMPA will be epoxied within the payload bay as shown above. Easy maneuverability to install or extract fragile cargo from inner capsule. Screw on cap seals cargo snugly with packing peanuts for additional protection 3/9/2017 2016-2017 USLI FLIGHT READINESS REVIEW 24
FMPA Drop Test Objective inspect the receptiveness of the FMPA to shock. Motor impulse will be simulated as impulse from FMPA hitting the ground. Potential energy from specific heights will be synonymous to kinetic energy developed from motor ignition overtime. Fragile material loaded after preliminary testing. Independent variable height from which the FMPA is dropped Results Found that FMPA s full extent of strength could not be tested from this test. Partial impulse dissipation Height Dropped (ft) Projected Impulse Dissipate d (N-s) Survival of Cargo? Damage to FMPA? 5 20.8 Y N 10 29.4 Y N 15 36.1 Y N 20 41.6 Y N 3/9/2017 2016-2017 USLI FLIGHT READINESS REVIEW 25
Carbon Fiber Stress Testing Sample Area (in 2 ) Max Load (lb) Ultimate Shear Stress (psi) 1.1339 9512 71020 2.1326 10156 76733 3.1306 9674 74045 Average -- -- 73932 Sample Area (in 2 ) Max Load (lb) Ultimate Shear Stress (psi) 1.0343 359.1 7862.18 2.0352 365.2 7773.52 3.0348 345.5 7410.15 Average -- -- 7682 3/9/2017 2016-2017 USLI FLIGHT READINESS REVIEW 26
Nose Cone and Fin Stress Analysis 3/9/2017 2016-2017 USLI FLIGHT READINESS REVIEW 27
Interfaces Internal Interfaces Primary Bonds 9394 Epoxy Couplers to body tubes Motor mount assembly Fins to body tube FMPA to body tube Bulkheads to couplers Machine Screws Interface body tubes to flight ready configuration Retainer Assembly Interfaces with motor, aft centering ring, and body tube External Interfaces 3/9/2017 2016-2017 USLI FLIGHT READINESS REVIEW 28
Requirements Verification Status Vehicle Requirements 1 st Test Flight was well over projections but the root cause of the discrepancy has been resolved. FMPA flown with simulated cargo (non-fragile). Still deemed a successful flight. All vehicle subassemblies and components deemed flight ready. Projections of ballasted design have altitude almost exactly at 5,280 ft. 2 nd Test Flight planned for either February 18 th or 25 th. Payload Requirements FMPA deemed operational after drop testing and test flight. No signs of damage to apparatus after testing. 2 nd test flight will house a fragile cargo (egg). Design has been verified to allow easy access to install or extract cargo. 3/9/2017 2016-2017 USLI FLIGHT READINESS REVIEW 29