Exportar a BRIC. BRIC BUSINESS Presentación Rápida de Servicios BRIC.
Callisto - Auburn University · BRIC Final Build (Batteries Not Mounted) BRIC Flight Reliability...
Transcript of Callisto - Auburn University · BRIC Final Build (Batteries Not Mounted) BRIC Flight Reliability...
CallistoAUBURN UNIVERSITY
MARCH 16TH, 2020
Adam BurkleyVehicle Team Lead
Vehicle Dimensions•Total Length: 132 inches•Inner Diameter: 6 inches•Outer Diameter: 6.2 inches•Estimated Mass: 55 lb
Vehicle Overview132 inches
24 inchesNose Cone Payload Section Main Parachute SectionBAE DBAE Drouge
Sec. ACS Sec. Booster Section
23 inches 2 inches 30 inches 2 inches 12 inches 7 inches 33 inches
Stability Margin•Static Stability Margin at Rail Exit: 4.16
•Static Stability Margin at Burnout: 4.93
•Center of Gravity from Nose Cone: 78.606 inches
•Center of Pressure from Nose Cone: 104 inches
Material Used•Carbon Fiber
• Used For:• Bulkheads, Fins, Centering Rings• Motor Tube, Booster Tube, Drogue Tube, Main Parachute Tube
•Fiberglass• Used For:
• Payload Tube• Altitude Control System Tube• Nose Cone• Couplers
Fins•The team used the clipped delta fin design.
•The thickness of the fins is 0.12 inches
•Easy to manufacture
•Works well in subsonic flight
•Team Experience
Nose Cone•The team decided on using a 4:1 tangent ogive nose cone.
•Performs well in subsonic flight
•Low coefficient of drag
Booster Section
Full Rocket Assembly
Motor Selection and Performance Predictions and Thrust Curve
•Motor Selection: AeroTech L2200G
•Thrust to weight ratio: 10.3:1
•Rail Exit Velocity: 84.9 ft/s
•Simulated altitude of 4726 ft(0 Mph Wind)• In 5 MPH Wind: 4719 ft• In 10 MPH Wind: 4702 ft• In 15 MPH Wind: 4667 ft• In 20 MPH Wind: 4635 ft
AeroTech L2200 Motor SpecificationsManufacturer AeroTech
Designation L2200G
Diameter 2.95 inches
Length 26.2 inches
Total Impulse 1147 lbf-s
Total Motor Weight 10.55 lb
Propellant Weight 4.95 lb
Average Thrust 504 lb
Maximum Thrust 677 lb
Burn Time 2.3 seconds
Tim JordanRecovery Team Lead
Recovery OverviewTwo Events
Drogue- Apogee and one second backup
Main- 550ft and 500ft
ParachutesMain Parachute: LeftStyle- HemisphericalDiameter- 10.5ftRipstop Nylon and 5/8inch tubular nylon shroud lines
Drogue Parachute: RightStyle- CircularDiameter- 30inRipstop Nylon and paracordShroud lines
Both have 5/8inch tubular nylonFor the shock cord
Ejection SystemBlack Powder Charges
Planned Charge sizes:
Main: 5 and 5.5 grams
Drogue: 3 and 3.5 grams
3D Printed Charge Cups
E-Matches
BAE (Barometric Avionics Enclosure)
Design maturity from PDR
Weight savings led to a minimalistic design
Encounters negligible forces so design changes don't risk failure to rocket
Electronics• StratoLogger CF-PerfectFlite
• Four altimeters• Featherweight GPS Tracker
• One GPS in nosecone
Attachment HardwareShear Pins- 4-40
U-Bolts
D-Rings
Flange Lock Nuts
Swivel Joints
Altimeter mount and nuts
Mission Predictions
Descent Times: Kinetic Energy:
Under Drogue(97.1 ft/s)- 45.8s Section 1 (Payload)-49.8 ft-lbs
Under Main(12.75 ft/s)- 43.1s Section 2 (Recovery)- 17.2 ft-lbs
Total - 88.9s Section 3 (ACS/Booster): 43.9 ft-lbs
Drift Totals:
5mph – 652ft 15 mph – 1957.3ft
10mph – 1305.1ft 20mph – 2609.4ft
Carter DavisPayload Team Lead
BRIC • The Boring Rotary Instrument
Carrier (BRIC) is a UAV with anonboard auger designed to collectextraterrestrial soil samples.
• The system features a dual motordriven pulley arm releasemechanism and a retractable auger.
• It is lightweight but durable, beingprimarily 3D printed using a blendof PLA and Onyx.
• The BRIC has undergone very fewminor changes since CDR.
BRIC Auxiliary Board
BRIC Final Build (Batteries Not Mounted)
BRIC Flight Reliability•The BRIC has received many flight tests both on test stands and on the field.
•The BRIC has been tuned to fly stable using the built-in software.
•The BRIC has been stowed and deployed four times in house and two times during demonstration flights.
•The BRIC underwent a static battery test where the system was left for four hours to prove a factor of safety of 2 for battery life.
•The BRIC was also run at various throttle speeds until the batteries died. This gave a very reasonable flight time of 9.5 minutes
UAVES• The Unmanned Aerial Vehicle
Ejection System is designed as asolution to problems the team hasfaced in previous years regardingdeployment.
• Instead of relying on aerodynamicforces to release the nosecone, theUAVES System manually pushes thenosecone and payload from therocket, using 2 ACME lead screws.
• This is a deployment method whichhas already proven more reliable inlaboratory and field tests thanmethods used in previous years.
UAVES Electronics
UAVES Electronics Module Render
UAVES Deployment
UAVES Flight Reliability•The UAVES system is arguably the most reliable.
•Through strength tests, UAVES has been proven to deploy a 55-pound load.
•Through tensile testing, the UAVES system was demonstrated to withstand a failure load of 300 pounds.
•Through battery testing, the UAVES was proven to have a factor of safety of 2 for battery life.
•UAVES was proven effective and reliable in the payload demonstration flight.
AOS / ARS• The Active Orientation System and
Active Retention System both aredesigned to assist with deployment ofthe payload.
• In past years, the payload has landedupside down, and a passiveorientation could not effectively andreliably counter this. The AOS isdesigned to automatically correct thepayload's orientation.
• The ARS is designed to retain therocket during flight and descent, toensure it only deploys when thepayload section is oriented andejected correctly.
AOS/ARS Electronics
AOS/ARS Control Board Render
AOSAOS/ARS Final Build
AOS/ARS Flight Reliability•The AOS/ARS system has been proven reliable from many in house and field tests.
•The AOS/ARS has undergone a full electronics and mechanical functionality test.
•This test proved the mechanical design was sound and there were no bugs in the electronics system.
•This system has been stowed and ejected more than 15 times through various testing of other systems without damage or malfunction.
•This system has been battery tested to a factor of safety of 2 in house.
•This system was successful during the payload demonstration flight.
Austen LeBeauAltitude Control Team Lead
ACS Components
ACS Electronics
ACS Flight Reliability•All internal components undamaged after both verification flights
•Grid fin torn off after first flight, most likely on touchdown
•Grid fin suffered scarring on surface after second flight
•Fins did not deploy due to bug in the code
•Vertical speed estimation algorithm did not perform adequately
•System is sensitive to vertical speed, Kalman filter will be implemented and tested at competition
Data Analysis• Data gathered from flight used to
implement a Kalman filter prototype• Simple, linear model• Newtonian kinematic equations• Not ideal, but much better estimations
Lindsey WaggonerTesting Team Lead
Completed TestsAltitude Control Tests◦ CFD analysis◦ Grid fin structural integrity test◦ Battery life test◦ Launch simulation
Payload Tests◦ AOS flip test◦ UAVES strength test◦ BRIC flight test/full system demonstration◦ Battery life test◦ Failure point analysis◦ Flight time test
Completed TestsStructures and Propulsion Tests◦ Materials testing
Recovery Tests◦ Ground separation tests◦ Full scale parachute test◦ Battery life test
Mission Tests◦ Sub-scale proof of concept launch (nominal, 4529 feet)◦ Full scale test launches (one failed; one nominal, 4665 feet)
Full-Scale Flight ResultsDemonstration Flight #1
• February 15
• Hopkinsville, KY (Music City Missile Club)
• Clear skies, 54 degrees, 10 mph winds
• Apogee: 4509 feet
• ACS inactive, main payload inert
• Failure due to main at apogee
Demonstration Flight #2
• February 22
• Samson, AL (SouthEast Alabama Rocketry Society)
• Clear skies, 57 degrees, 7 mph winds
• Apogee: 4665 feet (ACS set to 4400)
• All payloads active
• Successful launch, recovery, and payload demonstration
Full-Scale Flight Results
Vehicle Requirements Verification• Vehicle delivers payload to an apogee between 3500 and 5500 feet
• Validated using simulations and demonstration flight data
• Vehicle is recoverable and reusable• Vehicle was recovered with only slight damage after each demonstration flight
• Design follows all NASA requirements• Only three independent sections• Coupler/nosecone shoulders are within required range
• Vehicle can be assembled in 2 hours, and can remain launch-ready for 2 additional hours• Validated during demonstration flights and ground battery tests of all systems
• Vehicle uses a single stage, commercially-available solid motor with a 12V direct current firing system and is within the required impulse class
• Stability and velocity at rail exit are within required ranges• 2.754 calibers, 89.898 ft/s
• No prohibited features in use
Payload Requirements Verification• Required payload can be launched, recovered, and deployed to collect an ice sample
• Ground tests performed of all subsystems• Vehicle demonstration flight validated ability to be launched and recovered
• Additional payload has been documented thoroughly and tested to ensure safety
• All payload hardware is launched within vehicle
• Payload is registered with FAA and follows all local, federal, and NAR regulations
• Robust mechanical retention and deployment system in use
• No part of the payload is jettisoned
Example Test ProcedureUAVES Lead Screw Coupler Failure TestProcedure:1. Secure threaded rods to the carbon fiber flat plate in normal launch configuration.
2. The end of the threaded rod opposite the carbon fiber plate will be placed between the grips of the apparatus, and the worm drive gearmotor will be placed into the opposite grips of the apparatus.
3. The load and strain will be zeroed out on the computer interface and a tensile test will be initiated.
4. The data will be plotted until the maximum load is reached. The machine will automatically end the test.
5. If the maximum load is less than the required load, the test will be repeated with additional hardware securing the rod to the motor, including a knurled-tip worm screw and a notched motor drive shaft.
Example Test Procedure
Jackson TreeseSafety Officer
Safety SummaryFinalized personnel hazard analysis, FMEA, and environmental concerns tables with verifications and post risk assessment codes.
Finalized procedures for assembly of rocket on launch day.
No launch concerns.
Grant TurnerSTEM Outreach Lead
2019-2020 Outreach
Auburn University Engineering Day• E-Day is Auburn's largest engineering outreach event held annually.
• This year, it's estimated around 5,000 prospective engineering students came to campus for E-Day. The Rocketry team was able to interact with the majority of these students.
• Students were able to learn about the Auburn Rocketry team, and get hands-on interaction with this year's competition rocket.
Project Timeline
Budget and Funding
Questions?