PROJECT The University of Akron NASA Critical Design Review 12 - PowerPoint PPT Presentation

PROJECT The University of Akron NASA Critical Design Review 12 March 2018

Air brake deployment Ballistic crash landing just after rail exit as Corkscrew flight up to ~900 feet near launch site rocket fishtailed The University of Akron – College of Engineering

Software Simulations • Predicted Altitude 4,242 Ft from OpenRocket • Predicted 4,325 Ft Altitude from OpenRocket RASAero RASAero • Actual Altitude ~900 Ft Reached

Total Mass: 38.7 Pounds Key System Dimensions Key Vehicle Dimensions Nose Cone 26 inches Total Length 101 inches Payload Bay 14.5 inches Body I.D. 5 inches Electronics Bay 6.125 inches Body O.D. 5.35 inches Parachute Bay 23.75 inches Vehicle Wall Thickness 0.175 inches Engine Bay 20.5 inches

Stability Calculations Stability Characteristic OpenRocket RASAero Hand 77.39 77.80 74.27 CP (in) 64.15 63.90 65.04 CG Wet (in) 60.975 60.90 57.74 CG Post Burnout (in) 2.57 2.66 2.66 Stability Margin on Launch Rail 3.47 3.28 3.01 Stability Margin Post Burnout Stability Margin > 2.2 using all methods

FLIGHT CHARACTERISTICS Flight Profile Calculations Open Rocket RASAero Thrust to Weight Ratio 7.2 7.2 52.8 53.4 8 Ft. Rail Exit Velocity (ft/s) 65.1 66.3 12 Ft. Rail Exit Velocity (ft/s)

The Von Karman wound nose cone with PLA nose cone tip. Design Highlights Length: Carbon 26’’ with Fiber PLA Tip 7.25’’ Body shoulder Weight: 0.953 lb

Above Motor Bay ➢ 0.2 lb Incremental Weights of 0.125” 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

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

➢ 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

Air Brakes – Connected to the Stability Ballast above the Motor Bay ➢ 3D Printed ABS Casing ➢ In-flight Analysis with Raspberry Pi3 Determines Deployment

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

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

➢ Chosen motor changed from the Cesaroni L1350 to the Cesaroni L1050 ➢ Motor Preparation Procedure − Responsibility - Akronauts Mentor: Jerry Appenzeller

➢ All students and non essential personnel will stay at a safe distance during and after installation. − Responsibility - Akronauts Mentor: Jerry Appenzeller ➢ If hang fire occurs, the proper procedure will be followed, which is detailed in the next slide. − Responsibility - Akronauts Mentor: Jerry Appenzeller

➢ Wait the NAR recommended 60 seconds (minimum) to approach rocket. ➢ Upon arrival to the rocket, disconnect ignition system & any other electronic systems for the rocket. ➢ Mentor will inspect and replace ignitor as necessary. − Determine is relaunch is a viable option, or if the rocket needs further maintenance. − If further assessment is needed, take the rocket back to base camp.

1. 2. 1. Main parachute Drogue Parachute deployed from upper deployed from the body tube of the rocket lower body tube of the once tender descender is rocket opened 2. Altitude: Altitude: Apogee 500 ft.

Main Parachute Drogue Parachute Diameter (in): 106.5 Diameter (in): 17 Area (sqft): 59.37 Area (sqft): 1.520 Estimated Fabric Weight (lb): 0.48 Estimated Fabric Weight (lb): 0.02 Design: Toroidal Design: Hemispherical Material: Ripstop Nylon Material: Ripstop Nylon Drag Coefficient: 1.86 Drag Coefficient: 1.30 Terminal Velocity: 16.05 ft/s Terminal Velocity: 120 ft/s

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) 0 70.97 0 5 70.97 520.423 10 70.97 1040.917 15 70.97 1561.34 20 70.97 2081.763

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 Mass Kinetic Energy Potential Energy Component Weight (lb) (slug) (ft-lb f ) (ft-lb f ) Upper Rocket 17.479 0.543 0 92,283 Body Lower Rocket 16.327 0.507 0 86,165 Body System Total 33.806 1.051 0 178,619

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 Mass Kinetic Energy Potential Energy Component Weight (lb) (slug) (ft-lb f ) (ft-lb f ) Upper Rocket 17.479 0.543 3909 8742 Body Lower Rocket 16.327 0.507 3650 8162 Body System Total 33.806 1.051 7567 16921

Landing Kinetic Energy was calculated to ensure no single section of the rocket descends with a dangerous force Kinetic Energy Calculations Component Weight (lb) Mass (slug) Kinetic Energy (ft-lb f ) Upper Rocket Body 17.479 0.543 69.97 Lower Rocket Body 16.327 0.507 65.36 System Total 33.806 1.051 135.33

Connections Between Hardware and Ropes Used Hardware and Ropes Rated Number Part Name QTY Force (lb) 1 U-Bolt 2 1075 2 Long Quick-Link 2 2400 3 Shock Cord 3 2375 4 Eye-to-Eye Swivel 2 3000 5 Bridle 2 6000 6 Short Quick-Link 6 1400 7 Shroud Lines 40 400 Connection Line to 8 1 1400 Inner Shroud Lines

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 − 1 Ejection charge hole for ejection wires to go through − 1 redundant ejection charge hole for ejection charge wires to go through

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.

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. ◦ This test showed that not only did the chute releases work, but it verified that the ideas that  were set up for redundancy worked flawlessly. This test made the team confident that the main parachute will be released at the desired altitude during flight,  and if for some reason one release fails, the redundant release will ensure that the main is released properly

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

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

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

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

 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

 Payload Rover: ◦ Continuing working on code ◦ Ground testing with test body ◦ Ejection testing from rocket ◦ Autonomous movement of rover verification  Airbrakes: ◦ Optimizing code ◦ Adding additional features and verifying the correct operation of code  More testing with RTx/GPS Navigator Telemetry System  Post processing data from full scale test launch ◦ Altimeter data ◦ RTx/GPS Data  Overlay with Google Earth

 Two wheeled  Self balancing  Ultrasonic navigation  Spring loaded, servo-driven latch released solar panel arm

 Rover wheel diameter: 4.70”  Rover length wheel to wheel: 11.47”  Rover body l ength: 8”  Rover body height: 2.57”  Rover body depth: 3.54”

 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

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

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