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

Transcription

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

2 Air brake deployment just after rail exit as rocket fishtailed Corkscrew flight up to ~900 feet 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 ~900 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 > 2.2 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 Raspberry Pi3 Determines Deployment

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

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

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

16 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

17 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.

18 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.

19 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

20 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)

21 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

22 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

23 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-lbf) Upper Rocket Body Lower Rocket Body System Total

24 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

25 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

26 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.

27 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

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

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

30 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

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

32 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

33 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

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

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

36 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

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

38 QUESTIONS