Flight Readiness Review Presentation

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1 Flight Readiness Review Presentation THE UNIVERSITY OF MISSISSIPPI ROCKET REBELS UNIVERSITY STUDENT LAUNCH INITIATIVE

2 The Launch Vehicle 3/9/ 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.

3 Vehicle Layout and Dimensional Data Structure and Propulsion Total Length 105 in Outer Diameter 6.2 in Dry Weight Wet Weight 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/ USLI FLIGHT READINESS REVIEW 3

4 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/ 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 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/ USLI FLIGHT READINESS REVIEW 5

6 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/ USLI FLIGHT READINESS REVIEW 6

7 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/ USLI FLIGHT READINESS REVIEW 7

Motor Description Loki Research L840 Cocktail

low average thrust and long burn time Ensures

8 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/ USLI FLIGHT READINESS REVIEW 8

9 Stability Margin Stability Margin vs. Time at 0.4 s Launch Rail Exit at s Motor Burnout Time (s) 3/9/ USLI FLIGHT READINESS REVIEW 9

10 Additional Data THRUST TO WEIGHT RATIO Wet Weight of Rocket: 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/ USLI FLIGHT READINESS REVIEW 10

11 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 ( lb) Pre-burnout 518 oz ( lb) Post-burnout 3/9/ USLI FLIGHT READINESS REVIEW 11

12 Kinetic Energy Calculations Section Weight (lbf) Kinetic Energy at Main Parachute Deployment Kinetic Energy on Ground Impact (ft-lbf) (ft-lbf) Booster Section (postburnout) Avionics Section Payload Section Drogue Descent Speed 70 ft/s Main Descent Speed 20 ft/s 3/9/ USLI FLIGHT READINESS REVIEW 12

Drift Predictions Wind Speed (mph) Lateral Drift Distance (ft) Predicted Altitude (ft) 0 9 5279

13 Drift Predictions Wind Speed (mph) Lateral Drift Distance (ft) Predicted Altitude (ft) /9/ 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

14 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 ft 3/9/ 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.

15 Avionics Schematics and Ejection Specs. Primary Altimeter PerfectFlite StratoLoggerCF Drogue Bay Volume in 3 Backup Altimeter Missile Works RRC3 Xtreme Main Bay Volume 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 psi 3/9/ 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

16 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/ USLI FLIGHT READINESS REVIEW 16

17 Recovery System Testing 3/9/ USLI FLIGHT READINESS REVIEW 17

18 1st Presidium Full-Scale Test Flight 3/9/ USLI FLIGHT READINESS REVIEW 18

19 Footage 3/9/ USLI FLIGHT READINESS REVIEW 19

20 Actual vs Projected Flight Data 3/9/ USLI FLIGHT READINESS REVIEW 20

21 Additional Data Retrieved 3/9/ USLI FLIGHT READINESS REVIEW 21

(ft) 6242 6234.1% Max Velocity 715 720.7% (fps) Max 254 260 2.

6% Descent Speed (fps) Main Descent Speed (fps) 16.2 17.4 7.

22 Projected vs. Actual Data and Error Analysis Simulated Flight Data Actual Flight Data Percent Difference Apogee (ft) % Max Velocity % (fps) Max % Acceleration (ft/s 2 ) Flight Time (s) % Drogue % Descent Speed (fps) Main Descent Speed (fps) % 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/ USLI FLIGHT READINESS REVIEW 22

FMPA Payload Fragile Material Protection Apparatus Hydraulic system of shock

design, outer and inner ring assembly Easy accessibility, screw off top and large

cargo can be easily loaded within FMPA FMPA cargo survives entirety of vehicle flight

23 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/ USLI FLIGHT READINESS REVIEW 23

24 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/ USLI FLIGHT READINESS REVIEW 24

25 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? Y N Y N Y N Y N 3/9/ USLI FLIGHT READINESS REVIEW 25

Carbon Fiber Stress Testing Sample Area (in 2 ) Max Load

Load (lb) Ultimate Shear Stress (psi) 1.0343 359.1 7862.

26 Carbon Fiber Stress Testing Sample Area (in 2 ) Max Load (lb) Ultimate Shear Stress (psi) Average Sample Area (in 2 ) Max Load (lb) Ultimate Shear Stress (psi) Average /9/ USLI FLIGHT READINESS REVIEW 26

27 Nose Cone and Fin Stress Analysis 3/9/ 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

28 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/ USLI FLIGHT READINESS REVIEW 28

29 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/ USLI FLIGHT READINESS REVIEW 29

NU HOPE. Northeastern University. High-altitude Object Protection Experiment

NU HOPE. Northeastern University. High-altitude Object Protection Experiment NU HOPE Northeastern University High-altitude Object Protection Experiment Agenda Overview of Vehicle Properties Stability Analysis Launch Vehicle Sections and Systems Booster Stage Interstage system Payload