PROJECT. The University of Akron. NASA Flight Readiness Review. 12 March 2018

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1 PROJECT The University of Akron NASA Flight Readiness Review 12 March 2018

2 Rail Exit velocity of 23 Ft/s Corkscrew flight up to 960 Ft Ballistic crash landing near launch site The University of Akron College of Engineering

3 Software Simulations 4,242 Ft Predicted Altitude from OpenRocket OpenRocket RASAero 4,325 Ft Predicted Altitude from RASAero 960 Ft Actual Altitude Reached

4 Total Mass: 38.7 Pounds Key Vehicle Dimensions Total Length 101 inches Body I.D. 5 inches Body O.D inches Vehicle Wall Thickness inches Key System Dimensions Nose Cone 26 inches Payload Bay 14.5 inches Electronics Bay inches Parachute Bay inches Engine Bay 20.5 inches

5 Stability Calculations Stability Characteristic OpenRocket RASAero Hand CP (in) CG Wet (in) CG Post Burnout (in) Stability Margin on Launch Rail Stability Margin Post Burnout Stability Margin > 2.5 using all methods

6 FLIGHT CHARACTERISTICS Flight Profile Calculations Open Rocket RASAero Thrust to Weight Ratio Ft. Rail Exit Velocity (ft/s) Ft. Rail Exit Velocity (ft/s)

7 The Von Karman wound nose cone with PLA nose cone tip. Design Highlights Carbon Fiber Body PLA Tip Length: 26 with 7.25 shoulder Weight: lb

8 Above Motor Bay 0.2 lb Incremental Weights of Thick Aluminum Disks Secured by Nuts and Washers over Threaded Rods Nose Cone Tip Hollow Nose Cone Tip with room for Weight Addition along Threaded Rod Secured by Fastening Tip to Nose Cone Body with Retaining Plate

9 ABS FIN CAN Three Piece Assembly 3-D Printed Location: Motor Bay Hardware Fastened To Centering Rings and Fins FIBERGLASS DELTA FINS 8 Root Chord 6 Semi Span 1/8 Thick Flutter Safety Factor: 1.3

10 Commercially purchased Aeropack system to retain the motor Thrust Plate distributes thrust force of motor Centering Rings epoxied to motor mount tube to align motor concentrically

11 Air Brakes Connected to the Stability Ballast above the Motor Bay 3D Printed ABS Casing In-flight Analysis with Arduino Determines Deployment

12 Features Arduino Uno to rotate a servo motor based on input from an accelerometer and altimeter Increase drag on launch vehicle Enables target altitude to be reached with greater accuracy

13 Shear and Compression Testing of Body Tubes Wind Tunnel Tests for 1:5 Scale Model with and without Airbrakes and Full Scale Fin

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15 Stress Analysis Body Tube Bulkheads Fins Fin Can Fluid Flow over Nose Cone

16 Chosen motor for test flight changed from the Cesaroni L995 to the Competition motor Cesaroni L1050 Motor Preparation Procedure Responsibility - Akronauts Mentor: Jerry Appenzeller

17 Drogue Parachute deployed from the lower body tube of the rocket Altitude: Apogee Main parachute deployed from upper body tube of the rocket once tender descender is opened Altitude: 500 ft. 2.

18 Drogue Parachute Diameter (in): 17 Area (sqft): Estimated Fabric Weight (lb): 0.02 Design: Hemispherical Material: Ripstop Nylon Drag Coefficient: 1.30 Terminal Velocity: 120 ft/s Main Parachute Diameter (in): Area (sqft): Estimated Fabric Weight (lb): 0.48 Design: Toroidal Material: Ripstop Nylon Drag Coefficient: 1.86 Terminal Velocity: ft/s

19 Drift distance calculations ensure the rocket does not drift outside of the permitted launch field Drogue and Main Wind Speed (mph) Time (sec) Drift (ft)

20 At apogee, the velocity of the launch vehicle is 0 ft/s. Here are the Kinetic Energy calculations at this key phase during flight. Kinetic Energy Calculations at Apogee Component Upper Rocket Body Lower Rocket Body Weight (lb) Mass (slug) Kinetic Energy (ft-lbf) Potential Energy (ft-lbf) , ,165 System Total ,619

21 At main deployment, the velocity of the launch vehicle is 120 ft/s. Here are the kinetic energy calculations at this key phase during flight. Kinetic Energy Calculations at Main Deploy Component Upper Rocket Body Lower Rocket Body Weight (lb) Mass (slug) Kinetic Energy (ft-lbf) Potential Energy (ft-lbf) System Total

22 Landing Kinetic Energy was calculated to ensure no single section of the rocket descends with a dangerous force Kinetic Energy Calculations upon Landing Component Weight (lb) Mass (slug) Kinetic Energy (ft-lbf) Upper Rocket Body Lower Rocket Body System Total

23 Number Part Name QTY Rated Force (lb) 1 U-Bolt Long Quick-Link Shock Cord Eye-to-Eye Swivel Bridle Short Quick-Link Shroud Lines Hardware and Ropes Used Connection Line to Inner Shroud Lines Connections Between Hardware and Ropes

24 Bulkhead Assembly for Drogue Attachment Components U-bolt Three holes for threaded rods for airbrakes Bulkhead Assembly for Main and Drogue Attachment/Ejection Components U-bolt 2 Ejection charge holes for ejection wires to go through

25 Black Powder Ejection 1 system for drogue ejection 1 redundant system for drogue ejection Total of 2 ejection systems: 2.1 grams of black powder for ejection and 2.75 grams for redundant ejection charge Jolly Logic Chute Release 1 system for main release 1 redundant system for main release Ground test performed with built in system for each to ensure full release prior to each launch.

26 Ground tests for the Jolly Logic Chute Releases were conducted to ensure that the releases worked properly and that redundancy worked. The two releases were wrapped around the main parachute. They were connected to each other, so a redundant system was formed. Both releases were turned on and set to do a ground test by putting the setting below the lowest altitude. This test proved to be very successful.

27 A secondary back up system capable of deploying drogue Features RRC3 Missile Works Altimeters, Two Pole Rotary Switch, and 9 V Batteries

28 RTx/GPS Telematics Navigator System Provides real-time bearing and distance Operates on Industrial, Scientific, and Medical (ISM) radio band (902MHz to 928MHz)

29 Two wheeled Self balancing Ultrasonic navigation Servo-driven latch releases spring loaded solar panel arm

30 Rover wheel diameter: 4.70 Rover length wheel to wheel: Rover body length: 8 Rover body height: 2.57 Rover body depth: 3.54

31 Black powder charges to pressurize payload bay and break shear pins Compressed springs to push payload out of the two sections 6 rods to secure the payload during flight Eye Bolts for ease of installation

32 Designed with Raspberry Pi 3B Code written in python Self balancing via MinIMU 9 v5 chipset Obstacle avoidance using ultrasonic sensor

33 WRC + Remote Control System by Missile Works 4 remote control outputs Operates on the license free ISM band Operational range of 20 miles

34 Updating of FMEA, PHA and Environmental Risk Assessment Tables Verification Column References Overhaul of NASA and Team Compliance Verification Final edits to Safety Procedures

35 QUESTIONS