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

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 • Second full scale launch – Mar. 2 nd

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.

Vehicle Overview

Vehicle Adam Burkley

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

Overall Length: 124 in. External Avionics Rover Section: 25 Drogue: 12 in. Nosecone: 24 in. Main Parachute: Booster Section: 35 in. dimensions external wrap: in. 26in. 2 in. Nosecone Avionics Bay: 8 Altitude Control Coupler: 14 Mid-Coupler: 14 in. Internal shoulder: Inner Diameter: 6” in in. overlap 6in Outer Diameter: 6.25” Aerotech Nosecone with L1420R Motor Motor mount separate recovery Main Parachute Recove Rover and rover Altitude control system ry Compartment Drogue parachute orientation system system Avionic Compartment 4x Clipped Delta Fins s

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

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

Clipped Delta Fins • Easy to manufacture • Proven design • Performs well in subsonic flight • Team experience

Ogive Nose Cone • Low Coefficient of Drag • Easy to manufacture • Rated highest by team trade study • 4:1 ratio

Booster Section

Full Rocket Assembly

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

Aerotech L1420R Motor Thrust Curve

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

Recovery Ben Creel

Recovery Overview Stage 2: Apogee – Drogue Deploys Drogue Parachute Stage 3: 700 ft – Nosecone Stage 3: 500 ft – Main Deploys Separation Main Drogue Parachute Parachute Drogue Tube Drogue Parachute Nosecone Parachute Stage 1: Launch Nosecone Nosecone Parachute Nosecone

Parachutes • 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 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

Kinetic Energy and Descent Time Kinetic Energy Drogue Tube and Booster Section Avionics Section Nose cone Coupler Calculated 41.63 ft-lb s 5.55 ft-lb s 49.96 ft-lb s 49.96 ft-lb s Measured 48.97 ft-lb s 6.53 ft-lb s 42.44 ft-lb s 55.52 ft-lb s Descent Times Calculated Measured Main 82.83 sec 14.5 ft/s Nosecone 75.92 sec 22.6 ft/s

Drift Rocket Body Nosecone Wind Wind Drift Under Total Drift of Wind Wind Drift Under Total Drift of Drift Under Drift Under Speed Speed Nose cone Nose cone Speed Speed Main Rocket Body Drogue(ft) Drogue(ft) (mph) (ft/s) Parachute (ft) (ft) (mph) (ft/s) Parachute (ft) (ft) 5 7.33 317.17 239.32 556.49 5 7.33 333.00 274.14 607.14 7.5 11.00 475.97 359.15 835.12 7.5 11.00 499.73 411.40 911.13 10 14.67 634.77 478.97 1113.74 10 14.67 666.46 548.66 1215.12 12.5 18.33 793.14 598.47 1391.61 12.5 18.33 832.73 685.54 1518.27 15 22.00 999.46 822.8 1822.26 15 22.00 951.94 718.30 1670.24 17.5 25.67 1110.74 838.12 1948.86 17.5 25.67 1166.19 960.06 2076.25 20 29.33 1269.11 957.62 2226.73 20 29.33 1332.46 1096.94 2429.40 • Drift during Full Scale Verification Flight was 1538.5 ft

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

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

Testing Nick Ratte

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

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

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

Altimeter Data

Rover Trevor Cavanaugh

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.

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

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

Testing • Three tests were conducted on the rover payload. • Rover battery tests • Rover retention system tests • Rover terrain performance evaluations

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.

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.

Altitude Control Austen LeBeau

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