1. Georgia Tech NASA Preliminary Design Review Teleconference
Presented By:
Georgia Tech Team ARES

2. Agenda Team Overview (1 Min) Changes Since Proposal (2 Min)
Educational Outreach (1 Min)
Safety (2 Min)
Project Budget (4 Min)
Launch Vehicle (20 min)
Flight Systems (15 Min)
Questions (15 Min)

3. Project KRIOS - PDR
TEAM OVERVIEW

4. Georgia Tech Team Overview
15 person team composed of undergraduate students
Highly Integrated team across several disciplines

5. Work Breakdown Structure

6. PROJECT KRIOS - PDR
CHANGES SINCE PROPOSAL

7. Changes since Proposal
Launch Vehicle
Body Tube diameter increased from 5 in to 5.5 in due to sparse resources online to support 5 in frames.
Aerotech L1150R motor replacing Cessaroni
Roll-inducing mechanism changed from angling the entire fin surface to using a servo-driven aileron on each fin
Another Stratologger added for dual redundancy to ensure the parachutes are deployed
Sensors are replaced by a 6 Degrees of Freedom IMU Board
Project Plan
Outreach after school program to be done at Peachtree Charter Middle School
Georgia Space Grant Consortium has allocated $2000-$3000 to our project

8. Project KRIOS - PDR
EDUCATIONAL OUTREACH

9. Educational Outreach Peachtree Charter Middle School
Boy Scout Merit Badges
CEISMC GT
Atlanta Science Festival

10. PROJECT KRIOS - PDR
SAFETY

11. Risk Assessment & Launch Vehicle
Hazard Identification
What has the potential to become a safety hazard?
Risk and Hazard Assessment
What are the potential consequences of the hazard?
Risk Control and Mitigation
What can be done to mitigate the risk?
Reviewing Assessments
Are the mitigations working?

12. Project KRIOS - PDR
PROJECT BUDGET

13. Project Budget Summary
Section
Cost
Launch Vehicle
$2100
Avionics
$550
Outreach
$800
Travel
Test Flights
$1200
Total
$5450

14. PROJECT KRIOS - PDR
LAUNCH VEHICLE

15. Launch Vehicle Summary
Predicted apogee: ft (without using ATS system)
Motor: Aerotech L1150R
Max Mach 0.68
Total weight: 28 lb
Dual deployment
Stability margin: 2.22 calibers
CP = in
CG = in

16. Fins Variable Unit Speed of Sound, a 1105.26 ft/sec Pressure, P
13.19 lb/in^2
Temperature, T
48.32 Fahrenheit
Shear Modulus, G
425,000 psi
Taper Ratio,
0.3627
Tip Chord
3.5 in
Root Chord
7.87 in
Thickness
0.125 in
Fin Area
29.07 in^2
semispan
6.56 in
Flap Chord
1.14 in

17. Roll Control System Materials: Balsa, Aluminum, Fiberglass
Attachment: Nuts, Bolts, Epoxy, Brackets

18. Booster Section Materials: Cardboard, Plywood, Aluminum, Fiberglass
Attachment: Nuts, Bolts, Epoxy

19. Apogee Targeting System (ATS)
Materials: Fiberglass
Aluminum Plastic
Attachment: Nuts, Bolts, Brackets, Hinges

20. Motor Selection Aerotech L1150R Chosen Higher impulse
Performance
Aerotech L1150R
Aerotech L850W
Average Thrust: N
1, N
Peak Thrust:
1, N
1, N
Total Impulse: Ns Ns
Thrust Duration: s s
Aerotech L1150R Chosen
Higher impulse
Quicker burn out time

21. Avionics Bay Construction: ¼ in Plywood Sheet
2 x ¼ in plywood bulkheads
Fiberglass 5.5 in tube
2 x Steel threaded rods
Attachment:
Screws, Nuts, Epoxy

22. Payload Bay Construction: ¼ in Plywood Sheet
2 x ¼ in plywood bulkheads
Fiberglass 5.5 in tube
Attachment:
Screws, Nuts, Epoxy, Wood Glue

23. Recovery System
Main Parachute
Drogue Parachute

24. Mass Breakdown
Booster Section Drogue Chute Avionics Bay Main Chute Nosecone
System
Mass (lbs)
Recovery
0.69
Avionics
0.857
Booster Section
8.098
Tubing
18.332
Total
27.977

25. Barrowman’s Calculations Using openrocket Software
Stability Calculation
Variable
Value LN =
21.75 in d
5.5 in dF dR LT
0 in XP CR
7.87 in CT
3.50 in S
5.12 in LF
5.55 in R
2.25 in XR
4.37 in XB
66.5 in N
4 fins
Barrowman’s Calculations
Using openrocket Software
Results:
CP of in
2.24% error
Field
Value
Time to Rod Clearance s
Center of Pressure (CP) in
Center of Gravity (CG) in
Stability Margin Caliber
cal

26. Mission Performance – Flight Profile

27. Mission Performance - Drift Profile

28. Test Plan Overview Servos: Extension force test
ATS: Run (FEA?) simulations
Thrust Plate: Bend test and pressure test to test rigidity
Payload Bay: Payload retention force test
Avionics Bay: Altimeter performance test using vacuum chamber
Recovery System: Recovery system test fire
Fins: Roll robustness test

29. Project KRIOS - PDR
FLIGHT SYSTEMS

30. Flight System Responsibilities
Outline of Success Criteria
Requirement
Design Feature to Satisfy Requirement
Requirement Verification
Success Criteria
The vehicle shall not exceed an apogee of 5,280 feet
Drag from the ATS system
Full-scale flight test
Apogee within 1% of target
The vehicle will be tracked in real- time to locate and recover it
GPS module will be used in the vehicle and base station
The vehicle will be located on a map after it lands for recovery
The data of the vehicle’s flight will be recorded
Sensors will save data
The data will be recovered and readable after flight

31. Flight Systems: Avionics
Avionics Components
Part
Function
Stratologger CF x2
Altimeter - used to receive and record altitude and deploy ejection charges
ADXL345
Triple axis accelerometer used for rolling calculations. Part of 6 DoF IMU.
ITG-3200 gyro
Gyro sensor returns radial velocity used for rolling calculations. Part of the 6 DoF IMU.
Teensy 3.2
Microcontroller - used to receive sensor data to compute and control the ATS
Eggfinder TX/RX Module
GPS module -  used to track the rocket in real time
9V Alkaline Batteries
Used to power all Avionics components and ATS

32. Flight Systems: Avionics
General connection of main components

33. Flight Systems: Avionics
Eagle CAD schematic of main components

34. Flight Systems: Ground Station
Equipment:
Eggfinder TX (Transmitter)
Eggfinder RX (Receiver)

35. Flight Systems: ATS & Roll System Science
Dynamic drag adjustment by changing the geometry exposed to the flow to increase the vehicle’s aerodynamic properties.

36. Flight Systems: ATS Power
9-volt alkaline batteries will be used to power the ATS
DC motors will be used to create torque on the air-brake flaps

37. Flight Systems: Testing Overview
Wind Tunnel: Test Cd of flaps against simulation, and ability to withstand the given pressures
Flight Simulation: Forged flight data will be fed to the sensors and the response efficacy will be analyzed.
Power Consumption: Full charged power supply will be connected to flight systems to see its maximum lifespan.
Altimeter Testing: Will use vacuum chamber to ensure that altimeter readings are accurate

38. Questions
Questions?