University Student Launch Initiative (USLI)

Florida Institute of Technology

April 2, 2009

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Alex Berta, Jiten Chandiramani, Esteban Contreras, Niroshen Divitotawela, Robert Geuther, David Jarkey, Justin LaFountain, Philip Meyer, Scott Perry

Dr. Hector Gutierrez, Dr. Daniel Robert Kirk, H. Greg Peebles III

Successfully compete in 2008-2009 USLI competition: Design/build/recover a model rocket to fly to one mile apogee

Perform a NASA-relevant science experiment during flight: Use rocket flight to simulate and obtain slosh behavior during low-gravity maneuvers

Acquire full 6-Degree of Freedom rocket trajectory data: Facilitate benchmarking of NASA’s Universal Control Analysis Tool (UCAT)

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Motivation: Upper-stages of rockets undergo orbital maneuvers that may lead to large propellant slosh motions which may adversely impact performance Example: NEAR spacecraft interrupted its

insertion burn when fuel reaction was larger than anticipated. Prevented NEAR from orbiting Eros and delayed mission

Example: Does new NASA Orion spacecraft need baffles?

Problem to be addressed by science experiment: Lack of experimental data to benchmark and anchor advanced computer simulations of liquid propellant slosh

Florida Tech has extensive slosh dynamics research program including ground testing and multiple experimental flights on NASA’s Low-Gravity Research Aircraft

Utilize USLI competition as opportunity to conduct NASA-relevant science experiment aimed at acquiring vital slosh dynamics data which can be shared with researchers around the world!

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Delta IV Heavy Rocket

6 DOF trajectory modeling and analysis essential for launch approval University and industry need to supply reliable preliminary trajectory

analysis Trajectory verified by Air Force 45th Space Wing

SPLASH: Only “low-end and affordable” 6 DOF trajectory analysis programs on market

Air Force 45th Space Wing has deemed SPLASH not adequate for preliminary safety evaluation of trajectory

Space Florida is contracting for SPLASH upgrade SPLASH has “a long way to go before adequate”

NASA KSC Mission Analysis Group has developed 6 DOF Universal Control Analysis Tool (UCAT)

Currently used by KSC to simulate large launch vehicle dynamics, trajectory and mission profile verification

Florida Tech working with KSC to upgrade UCAT and develop generic models appropriate for university or industry use

Input of thrust stand motor data into UCAT for flight analysis NASA KSC interested in extending UCAT use for preliminary trajectory

analysis for CCAFS university or industry launch customers

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Basic layout guided by over 10 years of high powered model rocket experience at Florida Tech

Detailed Pro|Engineering CAD model developed to aid design, predict exact mass properties (Mcg, Iij matrix) and input to NASA UCAT

Overall Dimensions (L = 12.5 ft, W = 25 lb)

Materials used: G10 Fiberglass Main and

coupler tubing Bulkheads Aluminum reinforced

bulkheads

Payload

Main Recovery

Drogue

Motor/Fins

Nosecone

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Multi-DOF motor thrust measurement and statistical sampling critical to flight performance prediction

Florida Tech has unique 6-DOF thrust stand capable of measuring thrust misalignment and motor torques

Thrust curve provided by most manufactures (e.g. Loki Research) is insufficient for accurate modeling Nominally only provide 1 axis of thrust – neglects thrust

misalignment which can be significant! Provides no estimate for test-to-test repeatability and

statistical deviations (propellant mass, nozzle manufacture and alignment, etc.)

Such limited manufacture data would be insufficient for a rocket launch from Cape Canaveral Air Force Station as mandated by US Air Force 45th Space Wing – Florida Tech has launched student built rockets from CCAFS and provided high-fidelity thrust vs. time motor data

Thrust to Weight Ratio for minimum projected vehicle weight of 25lbs.

Thrust to Weight Ratio for maximum projected vehicle weight of 30lbs.

Thrust curve provided by Loki Research on Rocksim database for Loki L930 motor

Shows approximate weight can generate enough velocity to remain stable

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10,000 lb capability Measurement of all 6 degrees of freedom using

state-of-the art instrumentation No comparable facility in the world! Capable of obtaining thrust misalignment data to

compare to industry-given data

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•Average Thrust = 199 lbs•Peak Thrust = 275 lbs•Burn Time = 3.61 s•Impulse = 795.7 lb· s

Rocket Motor

Thrust data in axial direction confirms given Loki Research given data

Thrust in non-axial directions can be used for thrust misalignment calculations

Rocket needs certain speed by end of launch rail to produce aero-forces on fins to overcome any unforeseen thrust misalignment forces thus ensuring that rocket flight is within 30 deg of nominal flight trajectory

With known solid motor thrust vs. time history, speed of rocket along rail is calculated to be ~86 ft/s.

Knowing speed of rocket provides dynamic pressure on fins, and fin area then checked to ensure adequate stabilizing force vs. thrust misalignment and wind

If necessary iterate on final fin sizing and rocket mass distribution

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Complete model parameters (payload and recovery dimensions, etc.) input into RockSim and UCAT

Static Margin: 2 Fins sized down after thrust misalignment altered

Rocket’s estimated altitude: 5200 ft

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cpcg

152.25” L x 4.00” D

Avionics package selected to deploy parachutes at appropriate points of flight

Avionics selected and tested: Ozark Aerospace ARTS 2 (left) G-Wiz Partners HCX (right)

Completely redundant system: Each recovery stage has an extra ejection

charge mortar Each mortar is blown by two electric matches,

controlled by each avionics board

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Flight computers tested to ensure firing of electric matches at appropriate times

Computers tested during test flight with dummy payload to ensure successful deployment

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G-Wiz Pyrotecnics Computer Test

ONE ejection charge mortar will have a prefabricated squib, covered with tape

Avionics section installed with shear pin and weighted

Charge remotely ignited Test repeated with

different squibs until optimal deployment achieved Main Charge – 9g Drogue Charge - 4g

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Ejection Charge Mortars

Ejection Avionics Board

Perfect Flight Altimeter

Ejection Avionics Batteries

Perfect Flight Battery

Extended microgravity time required for science experiment necessitates use of two parachute system

Drogue Parachute (left): RocketMan Enterprises 4ft Pro-

Experimental Timed deployment after reaching apogee Slows rocket to terminal velocity of 50ft/s

Main Parachute (right): RocketMan Enterprises 12ft Standard Deployed at altitude of 800ft. Slows rocket to terminal velocity of 16ft/s

Kevlar shock cord attached to U-bolts at both ends of drogue and main compartments connects parachutes to rocket

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Slosh Tank

Batteries

IR Camera (inside tube)

VCR (not shown here)

6 DOF Board

6 DOF boards connected to top bulkhead for easy data download

Bottom L-Brackets connect to a U-Bolt that passes through the large upper bulkhead

Focal length for camera

L-Brackets

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Single axis gyroscopeDual axis accelerometer

Two dual axial accelerometers that measure ±18g Three single axis gyroscopes that measure ±75º/sec Data collection rate of 1000 Hz Collected data used to benchmark NASA UCAT

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Electronics controlled by PIC (Programmable Interface Controller) Data collected on EEPROM (Electrically Erasable Programmable

Read-Only Memory) Board and sensors designed to fit within 3.75” diameter tube

PIC microcontroller

EEPROMs SensorsMounting Holes

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Same size, weight, and weight distribution as payload

Disposable Connects to upper

bulkhead in same fashion as payload

Used for Palm Bay test flight

Before payload is inserted into rocket payload systems will be turned on

System is triggered before engine ignition

After 60 seconds the system stops recording

Data recovered using a USB cable attached to sensor boards

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Pratt Hobby’s hybrid ground launch electronics will be used to start collecting data and ignite engine

First (normally fills tank) signal will turn on video recorder and sensor boards

Second signal on separate channel will ignite engine.

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Regulatory Compliance: The MSFC USLI competition safety requirements regarding ATF, DOT, EPA, FAA, OSHA, & TRA/NAR are already in place within existing Florida Tech Rocketry Program. All pyrotechnic testing has and will conform to these standards.

Material Hazard Analysis – Ongoing. Failure Modes and Effects Analysis –

Ongoing. Motor, Vehicle & Payload testing –

Ongoing.22

Height of 5144 ft Both parachutes

deployed successfully

All avionics recovered safely

Booster section lost Recovered week

later Unscrewed eyebolt

problem resolved

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Bayside HS Physics class Class discussion at time TBD

Sebastian River HS Science class Organized through teacher Cassandra Gonyer 2 Class discussions April 3rd

Focus on aerospace opportunities in college, careers, women in aerospace and international opportunities

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New booster completed Payload nearing completion Sebastian River outreach activity April 3rd Scheduled launch with full electronic

payload April 4th Complete verification of payload electronics

done beforehand

Prepare for trip to Huntsville!

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Panther II Heavy builds on previous high-powered model rocket experience to successfully compete in USLI competition

Panther II Heavy will advance NASA slosh dynamics research and provide benchmark data to NASA UCAT rocket modeling tool

Over 50 Florida Tech students and 3 faculty members participating

Project is on schedule and cost Questions?

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