PROJECT NOVA II - FRR Auburn University Student Launch Team - - PowerPoint PPT Presentation

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PROJECT NOVA II - FRR Auburn University Student Launch Team - - PowerPoint PPT Presentation

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PROJECT NOVA II - FRR Auburn University Student Launch Team Introduction Team Size: 35 Mission Payload : Soil Sample Rover Altitude Goal: 4700 ft. Will have an altitude control system First full scale launch Feb. 9 th

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SLIDE 1

PROJECT NOVA II - FRR

Auburn University Student Launch

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SLIDE 2

Team Introduction

  • Team Size: 35
  • Mission Payload : Soil Sample Rover
  • Altitude Goal: 4700 ft.
  • Will have an altitude control system
  • First full scale launch – Feb. 9th
  • Second full scale launch – Mar. 2nd
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SLIDE 3

Mission Success Criteria

  • The vehicle ascends stably to the team’s target apogee of 4700 ft., arriving

within 20 ft. of the target altitude.

  • The vehicle descends under drogue until main deployment, and then

descends to the ground in the correct number of sections under the kinetic energy requirement.

  • Upon landing, the rover orientation system is able to orient the rover for

deployment and the rover is able to leave the rocket, travel 10 ft. and retrieve a soil sample.

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SLIDE 4

Vehicle Overview

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SLIDE 5

Vehicle

Adam Burkley

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SLIDE 6

Vehicle Dimensions

  • Vehicle Length: 123.8 inches
  • Vehicle Inner Diameter: 6 inches
  • Vehicle Outer Diameter: 6.06 inches
  • Mass of Rocket: 45.6 Ibs
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SLIDE 7

Aerotech L1420R Motor 4x Clipped Delta Fins Inner Diameter: 6” Outer Diameter: 6.25” External dimensions Nosecone with separate recovery system Rover and rover

  • rientation system

Recove ry Avionic s Nosecone: 24 in. Internal

  • verlap

Nosecone shoulder: 6in Avionics Bay: 8 in Rover Section: 25 in. Main Parachute Compartment Drogue parachute Compartment Altitude control system Motor mount Overall Length: 124 in. Avionics external wrap: 2 in. Altitude Control Coupler: 14 in. Main Parachute: 26in. Drogue: 12 in. Booster Section: 35 in. Mid-Coupler: 14 in.

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SLIDE 8

Stability Margin

  • Static Stability Margin of 2.26 Calibers at rail exit
  • Static Stability Margin of 4.26 Caliber at burnout
  • CG located 71.541 inches from the nose cone
  • CP located 85.146 inches from the nose cone
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SLIDE 9

Materials Used

  • Carbon Fiber(Most of Vehicle Body)
  • High strength to weight ratio
  • Rated Highest in Team Trade Study
  • Fiber Glass(Rover Tube and BAE)
  • Can transmit radio frequencies through

material

  • High strength to weight ratio
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SLIDE 10

Clipped Delta Fins

  • Easy to manufacture
  • Proven design
  • Performs well in subsonic

flight

  • Team experience
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SLIDE 11

Ogive Nose Cone

  • Low Coefficient of Drag
  • Easy to manufacture
  • Rated highest by team trade study
  • 4:1 ratio
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SLIDE 12

Booster Section

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SLIDE 13

Full Rocket Assembly

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SLIDE 14

Motor Selection and Performance Predictions

  • Initial Motor Selection: Aerotech L1420R
  • Simulated altitude of 5081 ft without airbrakes
  • Thrust to weight ratio is 6.9 : 1
  • Provides rail exit velocity of 72.3 ft/s
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SLIDE 15

Aerotech L1420R Motor Thrust Curve

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SLIDE 16

Aerotech L1420R Motor Specifications

Manufacturer Aerotech Motor Designation L1420R Diameter 2.95 inches Length 26.2 inches Total Impulse 1038 Ib-sec Total Motor Weight 10.1 Ib Propellant Weight 5.69 Propellant Type Solid Average Thrust 326 Ibf Maximum Thrust 374 Ibf Burn Time 3.18 seconds

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SLIDE 17

Recovery

Ben Creel

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SLIDE 18

Stage 2: Apogee – Drogue Deploys

Recovery Overview

Stage 1: Launch Stage 3: 700 ft – Nosecone Separation Drogue Parachute Drogue Parachute Nosecone Nosecone Parachute Stage 3: 500 ft – Main Deploys Main Parachute Drogue Parachute Drogue Tube Nosecone Parachute Nosecone

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SLIDE 19
  • Three parachutes are being used
  • Drogue –Circular – 31 inch diameter
  • Main – Hemispherical – 107.28 inch

diameter

  • Nosecone – Hemispherical – 29.96 inch

diameter

  • Both the Main and Nosecone

parachute have a spill hole

Parachutes

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SLIDE 20

Parachutes

Descent Rates

Calculated Measured Drogue 92.45 ft/s 106.4 ft/s Main 13.37 ft/s 14.5 ft/s Nosecone 21.44 ft/s 22.6 ft/s

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SLIDE 21

Kinetic Energy and Descent Time

Descent Times

Calculated Measured Main 82.83 sec 14.5 ft/s Nosecone 75.92 sec 22.6 ft/s

Kinetic Energy

Booster Section Drogue Tube and Coupler Avionics Section Nose cone Calculated 41.63 ft-lbs 5.55 ft-lbs 49.96 ft-lbs 49.96 ft-lbs Measured 48.97 ft-lbs 6.53 ft-lbs 42.44 ft-lbs 55.52 ft-lbs

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SLIDE 22

Drift

Rocket Body

Wind Speed (mph) Wind Speed (ft/s) Drift Under Drogue(ft) Drift Under Main Parachute (ft) Total Drift of Rocket Body (ft) 5 7.33 333.00 274.14 607.14 7.5 11.00 499.73 411.40 911.13 10 14.67 666.46 548.66 1215.12 12.5 18.33 832.73 685.54 1518.27 15 22.00 999.46 822.8 1822.26 17.5 25.67 1166.19 960.06 2076.25 20 29.33 1332.46 1096.94 2429.40

Nosecone

Wind Speed (mph) Wind Speed (ft/s) Drift Under Drogue(ft) Drift Under Nose cone Parachute (ft) Total Drift of Nose cone (ft) 5 7.33 317.17 239.32 556.49 7.5 11.00 475.97 359.15 835.12 10 14.67 634.77 478.97 1113.74 12.5 18.33 793.14 598.47 1391.61 15 22.00 951.94 718.30 1670.24 17.5 25.67 1110.74 838.12 1948.86 20 29.33 1269.11 957.62 2226.73

  • Drift during Full Scale Verification Flight was

1538.5 ft

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SLIDE 23

BAE

  • 2 PerfectFlite

Strattologger CF’s

  • 2 Key Switches
  • 2 Threaded Rods
  • 1 Altimeter Mount
  • 2 9v batteries and

battery clips

  • 2 Bulk Plates
  • 1 U-Bolt
  • 4 Lock-nuts
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SLIDE 24

Nosecone Recovery System

  • 2 PerfectFlite

Strattologger CF’s

  • 2 Adafruit Trinket

Microcontrollers

  • 2 HS-485HB Servos
  • 4 Pull-Pin Switches
  • 1 Altimeter Mount
  • 1 Locking Tab

Assembly

  • 2 Threaded Rods
  • 4 9v batteries and

battery clips

  • 1 Bulk Plate
  • 1 U-Bolt
  • 12 Lock-nuts
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SLIDE 25

Testing

Nick Ratte

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SLIDE 26

Recovery Testing

  • Shear pin materials testing
  • Full-scale separation testing
  • Battery testing for all recovery systems
  • Main altimeters
  • Nose cone altimeters
  • Nose cone release system servos
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SLIDE 27

Summary of Completed Tests

  • Materials testing for all structural material

used for construction of the launch vehicle

  • Rover maneuvering and terrain crossing

capabilities evaluation

  • Rover active retention system evaluation
  • CFD analysis of the launch vehicle for

calibration of the Altitude Control System

  • Battery testing for the Altitude Control

System, and for the deployable rover

  • Subscale proof of concept launch
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SLIDE 28

Full Scale Vehicle Flight Demonstration

  • Vehicle Demonstration flight occurred March 2, 2019
  • Vehicle Apogee: 4947 ft
  • Max Velocity: 692 ft/s
  • This flight certified:
  • The launch vehicle in its entirety
  • All recovery systems
  • The deployable rover retention and propulsion systems
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SLIDE 29

Altimeter Data

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SLIDE 30

Rover

Trevor Cavanaugh

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SLIDE 31

Payload Design and Dimensions

  • The rover is a tracked vehicle

with a soil collection arm.

  • The arm remains

stowed over the rover to not add any length until its deployed. Once deployed the arm rotates 230 degrees to come into contact with the ground.

  • The rover’s size is 11.5 x

4 x 2.5 inches.

  • The rover weighed 1

pound 8 ounces.

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SLIDE 32

Payload integration with vehicle

  • The rover is integrated into

the launch vehicle with the rover’s sled.

  • The sled is fastened to the

launch vehicle via a bulkhead connected to the recovery bay.

  • The rover stays connected to

the sled with its ARS and PRS.

  • The sled is 12.75 inches with a

diameter of 5.9 inches

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SLIDE 33

Interfaces with ground systems

  • The rover is controlled by the rover

remote.

  • The remote has 3 buttons
  • Open ARS
  • Close ARS
  • Open ARS and Begin

Autonomous Operation

  • The remote communicates

with the rover using 2 Digi XBee Pro S3B RF modules

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SLIDE 34

Testing

  • Three tests were conducted
  • n the rover payload.
  • Rover battery tests
  • Rover retention system tests
  • Rover terrain performance

evaluations

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SLIDE 35

Payload Demonstrations

  • The rover payload has been flight proven twice.
  • The first flight, the rover orientation system was kept

from moving, so after landing, the rover section was positioned so the rover could exit right side up. The rover successfully exited the rover tube.

  • The last flight, all components of the rover worked

successfully except the spinning of the soil recovery

  • belt. Unforeseen circumstances made the soil

recovery belt not ready for launch.

  • Both launches the rover remained in the launch

vehicle until landing.

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SLIDE 36

Summary of requirements verification

Requirement Verification Method 4.3.1 All components of the payload that Auburn University can make in house were made in house. 4.3.2 The active retention system holds the rover in the launch vehicle and has been flight proven twice. 4.3.3 The rover will not begin autonomous operation until being wirelessly signaled to do so by our remote. 4.3.4 The rover will be coded to move at least 15 feet to exceed the 10 foot requirement. 4.3.5 The soil recovery system will work for a defined amount of time to collect the require soil. 4.3.6 After collecting soil, the soil recovery arm will close to cover the soil collection bay. 4.3.7 The batteries are contained on board in a safe location. The location and method of securing them have been flight proven twice. 4.3.8 The batteries are in an easily accessible position and are wrapped in red tape to easily distinguish them.

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SLIDE 37

Altitude Control

Austen LeBeau

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SLIDE 38

Altitude Control Design and Dimensions

  • Two 3D printed plates driven by a single DC

motor

  • Dimensions are 4H x 5.75W x 5.75L in.
  • 6.25 in. when plates are retracted
  • 9.75 in. when fully extended
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SLIDE 39

Altitude Control Integration with Vehicle

  • Bolted to the booster coupler with four 0.25

inch bolts.

  • Turned on at the launchpadvia a keyswitch.
  • Autonomous for complete duration of mission.
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SLIDE 40

Payload Demonstration

  • Unable to complete system in time for payload demonstration flights due to complications with

electrical system

  • Subscale flights were successful, however additional circuitry introduced to interface the

microcontollerwith the DC motor caused the microcontrollers to die.

  • Cause still unknown
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SLIDE 41

Summary of Requirements Verification

Requirement Verification Method 4.3.1 All components of the payload that Auburn University can make in house were made in house. 6.4.1 80 pounds of weight attached to drag plates. 6.4.2 Battery voltage tested for four hours at 30 minute intervals. 6.4.3 Drag plates sanded down to be flush with vehicle if not so. 6.4.4 No transmitters or receivers integrated into system.

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SLIDE 42

Safety Officer

Jackson Treesse

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SLIDE 43

RAC Criteria

Probability Level Descriptor Likelihood A Frequent >85% chance of occurring. B Probable 50% to 85% chance of occurring. C Occasional 15% to 50% chance of occurring. D Remote 1% to 15% chance of occurring. E Improbable <1% chance of occurring. Probability Level Severity Level 1 2 3 4 A 1A 2A 3A 4A B 1B 2B 3B 4B C 1C 2C 3C 4C D 1D 2D 3D 4D E 1E 2E 3E 4E

Severity Level Descriptor Example 1 Catastrophic: Immediate loss of mission or loss of rocket or significant safety risk to one

  • r multiple personnel or the

environment. A rocket motor is improperly constructed or assembled in such a way to cause a misfire. 2 Critical: Immediate threat to mission completion or likely harm to personnel or environmental destruction. The rocket must be recovered from power lines, an active roadway, or another active hazard. 3 Marginal: Immediate or delayed threat to partial

  • r total mission completion or

moderate threat to personnel or environmental concerns requiring attention. Sparks or exhaust from the rocket motor ignite a small brush fire on launch. 4 Negligible: Delayed threat to partial mission completion or minor environmental concerns; Minor or no threat to personnel. One nylon screw on the nose cone requires replacement.

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SLIDE 44

Failure Modes Example

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SLIDE 45

Environmental Analysis Example

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SLIDE 46

Checklist Example

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SLIDE 47

Educational Outreach

Kate Melsen

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SLIDE 48

Outreach Activities

  • Minority STEM Day
  • October 29th, 2018 & February 2nd, 2019
  • Auburn Junior Highschool EDAY
  • November 8th, 2018
  • Sanford Middle School STEM Day
  • November 9th, 2018
  • Local Career and Education Days
  • Auburn University Engineering Day
  • February 22nd, 2019
  • Drake Middle School Rocket Week
  • February 25th – March 1st, 2019
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SLIDE 49

Outreach Activities Totals:

Activity Type Total Participants Education/Direct Interaction 1162 Education/Indirect Interaction 11 Outreach/Direct Interaction 249 Outreach/Indirect Interaction 3613 Total Overall 5035

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SLIDE 50

Auburn Rocketry Certification Association (ARC)

ARC Membership Numbers for Tripoli Certifications In Process Level One 23 Level Two 4 Level Three 3 Completed (2018/2019) Level One 10 Level Two 2

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SLIDE 51

Final Budget

Funding Source Donation Alabama Space Grant Consortium $14,000 Dynetics $2,500 The Boeing Company $2,500 P3 Technologies $2,000 Barbara A Howell $25 Funding Subtotal $21,025 Subteam Expense V ehicle $2,527 Recovery $473 Rover $533.31 Altitude Control $467.44 Education/ Outreach $3,843 Lab Supplies and Launch Fees $938.10 Promotional materials $500.00 Hotel $3,404.08 Expense Total $12,685.33

Budget Balance +$8,339.68

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SLIDE 52

Questions?