PROJECT. The University of Akron. NASA Critical Design Review. 26 January 2018

Transcription

1 PROJECT The University of Akron NASA Critical Design Review 26 January 2018

2 Flawless Flight Motor detached during recovery during parachute inflation Detachment caused a fin to break off airframe Airframe after retrieval The University of Akron College of Engineering

3 Software Simulations 3,856 Ft Predicted Altitude from OpenRocket 4,345 Ft Predicted Altitude from RASAero OpenRocket RASAero 4,338 Ft Actual Altitude Reached

4 Total Mass: 37.9 Pounds Key Vehicle Dimensions Total Length inches Body I.D. 5 inches Body O.D inches Vehicle Wall Thickness inches Key System Dimensions Nose Cone inches Payload Bay 13.5 inches Electronics Bay 6.5 inches Parachute Bay inches Engine Bay 19.6 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 design was selected due to its optimal drag properties for subsonic flight. Design Highlights Carbon Fiber Body Aluminum Tip Length: with 7.25 shoulder Weight: 3.38 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 Drag Resistance 8 Root Chord 5-1/2 Semi Span 1/8 Thick Flutter Safety Factor: 1.6

10 Commercially purchased Aeropack system to retain the motor Thrust Plate distributes thrust force of motor Centering Rings to align motor concentrically Parts Composing Motor Retention Assembly of Motor Retention System

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 FEATURING Raspberry Pi 3 Rotates servo motor based on input from accelerometer and altimeter Enables target altitude to be reached with greater accuracy

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

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

15 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.

16 Drogue Parachute Diameter (in): 17.5 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): 112 Area (sqft): Estimated Fabric Weight (lb): 0.6 Design: Toroidal Material: Ripstop Nylon Drag Coefficient: 1.86 Terminal Velocity: ft/s

17 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)

18 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

19 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

20 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

21 Black Powder Ejection 1 system for drogue ejection 1 redundant system for drogue ejection Total of 2 ejection systems: 1.5 grams of black powder for ejection and 1.9 grams for redundant ejection charge Jolly Logic Chute Release 1 system for main release 1 redundant system for main release Ground tests and test launches will be done to verify the systems work

22 FEATURES RRC3 Missile Works Altimeters, Two Pole Rotary Switch, and 9 V Batteries A secondary back-up system is capable of deploying the drogue and main parachutes

23 RTx/GPS Telematics Navigator System Provides real-time bearing and distance View flight data in Google Earth Altimeter Missile Works RRC3 Output for main and drogue events

24 2 Wheeled Self Balancing IR Navigation Spring Actuated, Servo Released Solar Panel Arm

25 Black Powder and Spring Ejection System for Payload Ejection: 1 main black powder ejection (3g) 1 redundant black powder ejection (4g) Black powder amount will be verified during ground tests

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27 Designed with Raspberry Pi 3B Code written in Python Self balancing via MinIMU 9 v5 chipset Obstacle avoidance using IR

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

29 Post processing flight data Looking into student designed telemetry solutions IR Test Setup with Raspberry pi Circuit Analysis With/Without DC and Servo motor hats for raspberry pi

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

31 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

32 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.

33 Old style New Style

34 PDR phase had one FMEA table covering the whole team Moved to multiple tables where each one covers every component in an individual sub-system

35 Expanded the thought process and brought more creativity into the assessment after more detailed research into the environment in the launch area

36 QUESTIONS