Overview of the SABER Mission and Launch Vehicle Design S uborbital 4/5/2018 A tmospheric B alloon E levated R ocket
SABER: INSERT Presentation Name SABER: Suborbital Atmospheric Balloon Elevated Rocket 4/5/2018 Mission Introduction • Launch a 1-2 kg payload on a suborbital flight to an altitude of ~100 km • Use commercial systems and novel launch architecture – Balloon launched rocket system – Lower cost and development time – Commercial solid fuel single stage booster • Student education and STEM outreach – Undergraduate student run project – Payload opportunities: Upper-atmospheric research AIAA Conference 2018 2 Presenter: Benjamin Thompson
SABER: INSERT Presentation Name SABER: Suborbital Atmospheric Balloon Elevated Rocket 4/5/2018 SABER System Overview Rocket Booster 3 m length Zero Pressure Balloon 0.165 m diameter 1121 m 3 helium 21 m ~43 kg total mass 5,000 m 3 volume 3-U payload capable 3 m Person for scale, Commercial approx. 1.8 m tall propellant AIAA Conference 2018 3 Presenter: Benjamin Thompson
SABER: INSERT Presentation Name SABER: Suborbital Atmospheric Balloon Elevated Rocket 4/5/2018 Concept of Operations http://www.whiteeagleaerospace.com /operation-farside/ AIAA Conference 2018 4 Presenter: Benjamin Thompson
SABER: INSERT Presentation Name SABER: Suborbital Atmospheric Balloon Elevated Rocket 4/5/2018 Vehicle Simulations AIAA Conference 2018 5
SABER: INSERT Presentation Name SABER: Suborbital Atmospheric Balloon Elevated Rocket 4/5/2018 Rocket Simulations - Modeling Overview • Coefficient of Drag Coefficient Drag – Consider a C D(0) contributions from fins, nose cone, and body with small angles approximations – Uses USAF - Datcom methods • Coefficient of Normal Force Rocket Velocity [m/s] – Consider a C N(α) contributions from fins, nose cone, and body with small angle approximations – Barrowman formulations • Supersonic extension – Extensions for compressible flow using Example of velocity, force, and C D(0) terms for 0 AOA flight simulation (41kg @ 25km) Prandtl-Glauert approximation • Aerodynamic Torques • Moments – C D(0) and C N(α) are split into normal and axial force within rocket – All moments modeled using Euler’s body frame equations – Magnitude and angle of the total aerodynamic force (Axial and Normal) are used for torque calculations SOURCE: http://cambridgerocket.sourceforge.net/AerodynamicCoefficients.pdf – Assumes constant CP and CG location (found from OpenRocket) AIAA Conference 2018 6 Presenter: Jared Fuchs
SABER: INSERT Presentation Name SABER: Suborbital Atmospheric Balloon Elevated Rocket 4/5/2018 Rocket Simulations - Ascent Trajectory • Burn Ascent Simulation – Assumes vertical flight – Mass: 43 kg – Launch altitude: 25-30 km • Critical Values – Max Acceleration : ~310-320 m/s 2 – Max Q: ~27-30 kPa – Max Velocity: ~1200 m/s – Apogee: 100-106 km – Time to Apogee: ~150 s • Can reach 100 km with margin using an O-8000 motor at >25 km launch altitude AIAA Conference 2018 7 Presenter: Jared Fuchs
SABER: INSERT Presentation Name SABER: Suborbital Atmospheric Balloon Elevated Rocket 4/5/2018 Rocket Simulations - Stabilization Expected thrust misalignment <0.01 o Wind torque is negligible >25km Stability from fins is enough to provide a corrective moment AIAA Conference 2018 8 Presenter: Jared Fuchs
SABER: INSERT Presentation Name SABER: Suborbital Atmospheric Balloon Elevated Rocket 4/5/2018 Thermal Simulations - CFD • Aerothermal Simulation Overview – SimFlow CFD tool – Integrated trajectory results to model changing pressure, temperature, and velocity – rhoPimpleFoam solver for transient solutions – 3-D • Results – Constant rise in temperature across surface – Rapid fall off in temperature following burnout AIAA Conference 2018 9 Presenter: Jared Fuchs
SABER: INSERT Presentation Name SABER: Suborbital Atmospheric Balloon Elevated Rocket 4/5/2018 Thermal Simulations - Transient 1-D • Overview – A 1-D transient multi-mode heat transfer model – Utilized Modelica multi-domain physical modeling language – Final 550+ equation system was compiled into a Functional Mockup Unit (FMU) for use in Simulink • Assumptions/Approximations – Rocket fins were modeled from 1-D analytical equations – Custom submodels were coded for changing mass and heat capacity inside the rocket – Internal air was modeled as quasi-static with no forced or natural convective effects AIAA Conference 2018 10 Presenter: Jared Fuchs
SABER: INSERT Presentation Name SABER: Suborbital Atmospheric Balloon Elevated Rocket 4/5/2018 Thermal Simulations - Flight Temp Profile 9000 • 1-D thermal model results – Unpainted carbon fiber ~60 o F – Safe range for solid fuel motors – Passive solar heating during ascent • CFD simulations ( using SimFlow ) determined local air temperature to rise only during the motor burn and quickly fall AIAA Conference 2018 11 Presenter: Jared Fuchs
SABER: INSERT Presentation Name SABER: Suborbital Atmospheric Balloon Elevated Rocket 4/5/2018 Vehicle Drift Simulations • Considers wind data from the Black Rock desert in NV – 3 m/s ascent – Linear balloon volume increase – Launch immediately at balloon float Month Flight Typical Flight Profiles Profile AIAA Conference 2018 12 Presenter: Jared Fuchs
SABER: INSERT Presentation Name SABER: Suborbital Atmospheric Balloon Elevated Rocket 4/5/2018 Rocket System AIAA Conference 2018 13
SABER: INSERT Presentation Name SABER: Suborbital Atmospheric Balloon Elevated Rocket 4/5/2018 Rocket System Overview • Minimum Diameter Booster – Custom manufactured nose cone and fins – CO 2 ejection system – Custom tracking and recovery avionics 3.175m • CTI O-8000 Motor – Specific Impulse: 224 s – Propellant Mass: 18.6 kg AIAA Conference 2018 14 Presenter: Aaron Hunt
SABER: INSERT Presentation Name SABER: Suborbital Atmospheric Balloon Elevated Rocket 4/5/2018 Rocket System Overview Motor Retention Custom Fiberglass Nose Cone Main Parachute Carbon Fiber Fins Bulkhead 3U Payload Bay Drogue Parachute CTI Pro 150-40k Motor Case AIAA Conference 2018 15 Presenter: Aaron Hunt
SABER: INSERT Presentation Name SABER: Suborbital Atmospheric Balloon Elevated Rocket 4/5/2018 Rocket System Avionics • Functions – Deploying the parachutes – Recording position and transmitting to ground station – Provide interface for payload in flight – Transmitting and receiving information and commands for payload • Position Determination – Position is determined from GPS and an IMU through a Kalman filter • No remote commands will be necessary for recovery AIAA Conference 2018 16 Presenter: William Hankins
SABER: INSERT Presentation Name SABER: Suborbital Atmospheric Balloon Elevated Rocket 4/5/2018 Rocket System Recovery • Overview • Parachute Sizing & Descent Rates – Two-stage recovery procedure – Drogue: ⌀ 0.6 m – Actuated by commercial CO 2 ejection system – Drogue descent rate: 44 m/s • Opening Force Equation – Main: ⌀ 3.0 m – based on dynamic drag-area equations taking into – Main descent rate: 6 m/s account environmental factors and parachute parameters – Calculates inflation time and max forces sustained during the opening sequence • Data based on current parameters (main deployment) – Max Force: 196.17 lbs. – Inflation time : 2.677 s – Time of max force: 0.788 s AIAA Conference 2018 17 Presenter: Logan Anderson
SABER: INSERT Presentation Name SABER: Suborbital Atmospheric Balloon Elevated Rocket 4/5/2018 Balloon System AIAA Conference 2018 18
SABER: INSERT Presentation Name SABER: Suborbital Atmospheric Balloon Elevated Rocket 4/5/2018 Balloon System Overview • Zero Pressure Balloon – Filled from the crown – Vented at the base to equalize pressure – Gondola attached at base • Balloon Dimensions – Volume: 5185 m 3 – Helium Required: 1121 m 3 – Gore Length and Width: 33.7 m; 1.45 m – Number of Gores: 50 AIAA Conference 2018 19 Presenter: Austin Mills
SABER: INSERT Presentation Name SABER: Suborbital Atmospheric Balloon Elevated Rocket 4/5/2018 Gondola Structure • Aluminum Ring Attachment – The upper ring of the gondola will be secured to the balloon envelope by strips of paracord attached to the gore tape Parachute Tubes • Abort Procedures – 3 independent modes 1515 T-Slot Rail 1. Rocket can be released by the bottom hinge in case of Avionics Package launch abort 2. Balloon can be brought down using a servo controlled vent valve 3. In the event the servo can not operate, the balloon can be torn when the gondola releases by using a tear cord Hinged Baseplate attached to the envelope AIAA Conference 2018 20 Presenter: Grant Ransdell
SABER: INSERT Presentation Name SABER: Suborbital Atmospheric Balloon Elevated Rocket 4/5/2018 Rocket Ignition Method • Large motor core diameter requires ample heat energy to light motor – Ignition supplements • Thermite/Thermalite • Blue Thunder • Long motor core requires support – Wooden Dowel • Safety – Static wicks discharge excess charge – Dual Igniters allow for redundancy – Igniter shunt allows for physical disconnect during preparation. Wooden Dowel E-matches Ignition Material AIAA Conference 2018 21 Presenter: Matthew Fletcher
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