Mission Introduction Launch a 1-2 kg payload on a suborbital flight - - PowerPoint PPT Presentation

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Mission Introduction Launch a 1-2 kg payload on a suborbital flight - - PowerPoint PPT Presentation

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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

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Suborbital Atmospheric Balloon

Elevated

Rocket

Overview of the SABER Mission and Launch Vehicle Design

4/5/2018

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Mission Introduction

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Presenter: Benjamin Thompson

  • 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

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SABER System Overview

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Presenter: Benjamin Thompson

21 m 3 m

Person for scale,

  • approx. 1.8 m tall

Zero Pressure Balloon 1121 m3 helium 5,000 m3 volume Rocket Booster 3 m length 0.165 m diameter ~43 kg total mass 3-U payload capable Commercial propellant

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Concept of Operations

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Presenter: Benjamin Thompson

http://www.whiteeagleaerospace.com /operation-farside/

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Vehicle Simulations

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Rocket Simulations - Modeling Overview

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Presenter: Jared Fuchs

  • Coefficient of Drag

– Consider a CD(0) contributions from fins, nose cone, and body with small angles approximations – Uses USAF - Datcom methods

  • Coefficient of Normal Force

– Consider a CN(α) contributions from fins, nose cone, and body with small angle approximations – Barrowman formulations

  • Supersonic extension

– Extensions for compressible flow using Prandtl-Glauert approximation

  • Moments

– All moments modeled using Euler’s equations

  • Aerodynamic Torques

– CD(0) and CN(α) are split into normal and axial force within rocket body frame – Magnitude and angle of the total aerodynamic force (Axial and Normal) are used for torque calculations – Assumes constant CP and CG location (found from OpenRocket)

Example of velocity, force, and CD(0) terms for 0 AOA flight simulation (41kg @ 25km)

Coefficient Drag Rocket Velocity [m/s] SOURCE: http://cambridgerocket.sourceforge.net/AerodynamicCoefficients.pdf

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Rocket Simulations - Ascent Trajectory

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Presenter: Jared Fuchs

  • Burn Ascent Simulation

– Assumes vertical flight – Mass: 43 kg – Launch altitude: 25-30 km

  • Critical Values

– Max Acceleration: ~310-320 m/s2 – 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
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Rocket Simulations - Stabilization

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Presenter: Jared Fuchs

Expected thrust misalignment <0.01o Wind torque is negligible >25km Stability from fins is enough to provide a corrective moment

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Thermal Simulations - CFD

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Presenter: Jared Fuchs

  • Results

– Constant rise in temperature across surface – Rapid fall off in temperature following burnout

  • Aerothermal Simulation Overview

– SimFlow CFD tool – Integrated trajectory results to model changing pressure, temperature, and velocity – rhoPimpleFoam solver for transient solutions – 3-D

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Thermal Simulations - Transient 1-D

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Presenter: Jared Fuchs

  • 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

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Thermal Simulations - Flight Temp Profile

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Presenter: Jared Fuchs 9000

  • 1-D thermal model results

– Unpainted carbon fiber ~60oF – 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

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Vehicle Drift Simulations

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Presenter: Jared Fuchs

  • Considers wind data from the Black Rock desert in NV

– 3 m/s ascent – Linear balloon volume increase – Launch immediately at balloon float

Typical Flight Profile Month Flight Profiles

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Rocket System

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Rocket System Overview

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Presenter: Aaron Hunt

  • Minimum Diameter Booster

– Custom manufactured nose cone and fins – CO2 ejection system – Custom tracking and recovery avionics

  • CTI O-8000 Motor

– Specific Impulse: 224 s – Propellant Mass: 18.6 kg

3.175m

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Rocket System Overview

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Presenter: Aaron Hunt

Custom Fiberglass Nose Cone Carbon Fiber Fins 3U Payload Bay Drogue Parachute Main Parachute CTI Pro 150-40k Motor Case Motor Retention Bulkhead

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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

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Presenter: William Hankins

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Rocket System Recovery

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Presenter: Logan Anderson

  • Overview

– Two-stage recovery procedure – Actuated by commercial CO2 ejection system

  • Opening Force Equation

– based on dynamic drag-area equations taking into 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

  • Parachute Sizing & Descent Rates

– Drogue: ⌀ 0.6 m – Drogue descent rate: 44 m/s – Main: ⌀ 3.0 m – Main descent rate: 6 m/s

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Balloon System

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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 m3 – Helium Required: 1121 m3 – Gore Length and Width: 33.7 m; 1.45 m – Number of Gores: 50

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Presenter: Austin Mills

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Gondola Structure

  • Attachment

– The upper ring of the gondola will be secured to the balloon envelope by strips of paracord attached to the gore tape

  • Abort Procedures

– 3 independent modes

  • 1. Rocket can be released by the bottom hinge in case of

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 attached to the envelope

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Presenter: Grant Ransdell

Parachute Tubes Aluminum Ring 1515 T-Slot Rail Avionics Package Hinged Baseplate

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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.

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Presenter: Matthew Fletcher

Wooden Dowel E-matches Ignition Material

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Balloon System Avionics

  • Functions

– Tracks the vehicle during ascent providing real time telemetry data – Ignites the booster upon command – Abort mission if deemed unsafe

  • Mission Go/No-Go

– Flight data is sent to ground station for a human operator – Decision will be made by ground personnel whether to launch rocket or abort mission

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Presenter: William Hankins

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Ground Support Equipment

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Ground Station System Overview

  • Objectives

– Tracking, communication, and trajectory prediction of the launch vehicle throughout mission

  • Separate stations for the gondola and rocket

– Expect different trajectories for recovery between the rocket and gondola

  • Ground station antenna will track targets

– Servo operated system that will point to current location of the gonolda/rocket and predict location in event of communication loss

  • Two GS laptops used for live data processing

– Used for telemetry updates and location prediction – One for the rocket and one for the balloon

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Presenter: Oakley Copeland

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Downlink and Data Operations

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Direct connection to laptops for data processing Ground Station 1: Balloon/Gondola Ground Station 2: Rocket Backup Recovery Location off internet

Telemetry Balloon: Location, Altitude, Sway Speed, Voltage levels Rocket: Location, Inertial Altitude, Speed, Temperature, Voltage, Payload Data Spot Tracker Location backup for recovery Commands Balloon: Launch, Abort, Recover Rocket: Pre-Flight, Recovery, Abort

Radio ATC/FAA

Presenter: Oakley Copeland

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Conclusion

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Presenter: Jared Fuchs

  • Platform established to launch 1-2 kg payload to ~100 km
  • System simulations and verification close to complete

– Commercial options used where available – Custom options possible through prior Club experience – Cost and development time kept low

  • What’s next?

– Subsystem testing – Continue pursuing funding opportunities – Full scale flight in the next 1-1.5 years