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 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

• Predicted Altitude

from OpenRocket

4,242 Ft

• Predicted

Altitude from RASAero

4,325 Ft

• Actual Altitude

Reached

~900 Ft

RASAero OpenRocket

Software Simulations

Key Vehicle Dimensions Total Length 101 inches Body I.D. 5 inches Body O.D. 5.35 inches Vehicle Wall Thickness 0.175 inches Key System Dimensions

Nose Cone 26 inches Payload Bay 14.5 inches Electronics Bay 6.125 inches Parachute Bay 23.75 inches Engine Bay 20.5 inches

Total Mass: 38.7 Pounds

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

Stability Margin > 2.2

using all methods

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

FLIGHT CHARACTERISTICS

Design Highlights

Carbon Fiber Body PLA Tip

Length: 26’’ with 7.25’’ shoulder

Weight: 0.953 lb

The Von Karman wound nose cone with PLA nose cone tip.

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

Above Motor Bay

➢ 0.2 lb Incremental Weights of 0.125” Thick Aluminum Disks ➢ Secured by Nuts and Washers over Threaded Rods

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

FIBERGLASS DELTA FINS

ABS FIN CAN

➢ 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

➢3D Printed ABS Casing ➢In-flight Analysis with Raspberry Pi3 Determines Deployment

Air Brakes – Connected to the Stability Ballast above the Motor Bay

➢ 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

• ver 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.

Drogue Parachute deployed from the lower body tube of the rocket

Altitude: Apogee

Main parachute deployed from upper body tube of the rocket

• nce tender descender is
• pened

Altitude: 500 ft.

1. 2. 2. 1.

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

Drogue and Main

Wind Speed (mph) Time (sec) Drift (ft) 70.97 5 70.97 520.423 10 70.97 1040.917 15 70.97 1561.34 20 70.97 2081.763

Drift distance calculations ensure the rocket does not drift outside of the permitted launch field

Kinetic Energy Calculations at Apogee Component Weight (lb) Mass (slug) Kinetic Energy (ft-lbf) Potential Energy (ft-lbf) Upper Rocket Body 17.479 0.543 92,283 Lower Rocket Body 16.327 0.507 86,165 System Total 33.806 1.051 178,619 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 Main Deploy Component Weight (lb) Mass (slug) Kinetic Energy (ft-lbf) Potential Energy (ft-lbf) Upper Rocket Body 17.479 0.543 3909 8742 Lower Rocket Body 16.327 0.507 3650 8162 System Total 33.806 1.051 7567 16921 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 Component Weight (lb) Mass (slug) Kinetic Energy (ft-lbf) 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 Landing Kinetic Energy was calculated to ensure no single section of the rocket descends with a dangerous force

Number Part Name QTY Rated 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 8 Connection Line to Inner Shroud Lines 1 1400

Hardware and Ropes Used Connections Between Hardware and Ropes

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

Bulkhead Assembly for Drogue Attachment

Components

−U-bolt −Three holes for threaded rods for airbrakes

Bulkhead Assembly for Main and Drogue Attachment/Ejection

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

• n 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 length: 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

QUE

UESTIONS TIONS