UNIVERSITY OF FLORIDA INTIMIGATOR CDR
OUTLINE
Overview System Design Recovery Design Payload Design Vehicle Optimization Simulations and Performance Testing
PROJECT SUMMARY
Launch Vehicle The launch vehicle is designed to reach an
altitude of a mile It contains 3 separate payloads:
The Science Mission Directorate payload measures atmospheric conditions and allows the calculation of lapse rate
The Lateral Flight Dynamics payload collects data on the vehicle’s roll rate for analysis
The Flow Angularity and Boundary Layer Development payload aids the team in knowing the vehicle orientation
There is dual-deployment recovery, with separate drogue and main parachutes for the SMD payload lander and launch vehicle
OUTLINE
Overview System Design Recovery Design Payload Design Vehicle Optimization Simulations and Performance Testing
SYSTEM
VEHICLE DIMENSIONS Diameter: 6 inches Length: 115 inches Weight: 29 lbs
Component Weight (lbs)
Fins (2 with rollerons and 2 without) 5
Pneumatics Bay 1.5
Main Parachute/Shock Cord and Piston 3
Avionics Bay 3.25
Payload and Main Drogue Parachute Piston 0.25
Payload Main Parachute and Housing 4
Drogue Parachutes and Shock Cord 1.5
Nosecone and Pressure Payload 4.25
Body Tube 6.25
Total 29
Section Length (in)
Nosecone 24
Upper Airframe 44
Avionics Bay 3
Mid Airframe 16
Lower Airframe 28
Total 115
STATIC STABILITY MARGIN
The static stability margin is 3.03
CP = 91.1”
CG = 72.7”
Dimensions:
FINS
Fins and mount made from ABS plastic on a rapid prototype machine
Root Cord 11"Tip Cord 6”Span 6"Max Thickness .5"
MOTOR SELECTION
Cessaroni L1720 WT 1755 grams of propellant Total impulse of 3660 N-s 2.0 second burn time Altitude of 5280 feet
2.2 pound margin for error
OUTLINE
Overview System Design Recovery Design Payload Design Vehicle Optimization Simulations and Performance Testing
VEHICLE RECOVERY
Dual Deployment Drogue release at apogee Main release at 700 ft AGL
Drogue Parachute 36 inches in diameter Descent velocity of 65 ft/s
Main parachute 96 inches in diameter Descent velocity 18 ft/s
Recovery harness 5/8” nylon 25ft nosecone-upper 35ft lower-upper
VEHICLE RECOVERY SYSTEMS
Drogue parachute Directly below nosecone Released during first separation event
Main parachute Housed in middle airframe between avionics bay
and pneumatics bay Released during second separation event
Separation between pneumatics bay and middle airframe
SMD PAYLOAD RECOVERY
Dual Deployment Drogue release at apogee Main release at 700 ft AGL
Drogue Parachute 36 inches in diameter Descent rate of 25 ft/s
Main Parachute 36 inches in diameter Descent rate of 12.5 ft/s
Recovery harness 3/8” nylon 10-15 ft
SMD PAYLOAD RECOVERY SYSTEMS
Drogue parachute Released during first separation event Housed directly below vehicle drogue parachute
Main parachute Released from parachute housing during secondary
payload separation event stored in housing and ejected using a piston system
KINETIC ENERGY AT KEY POINTS
Launch Vehicle
SMD Payload Lander
OUTLINE
Overview System Design Recovery Design Payload Design Vehicle Optimization Simulations and Performance Testing
SCIENCE MISSION DIRECTORATE PAYLOAD – OBJECTIVES AND REQUIREMENTS
Objective To calculate the environmental lapse rate
Requirements Measure temperature, pressure, relative
humidity, solar irradiance, and UV radiation as a function of altitude
GPS readings and sky-up oriented photographs Wireless data transmission
SCIENCE MISSION DIRECTORATE PAYLOAD
Rests in the upper airframe on top of a piston
Ejects from the rocket at apogee
Dual deployment recovery
SCIENCE MISSION DIRECTORATE PAYLOAD
Payload legs spring open upon ejection
Some atmospheric sensors mounted on the lid
Body made of blue tube for data transmission purposes
SCIENCE MISSION DIRECTORATE PAYLOAD DESIGN
Arduino Microcontroller Samples analog sensors and reads outputs from
Weatherboard and GPS Weatherboard
Senses atmospheric data and transmits to the microcontroller using synchronous communication
Analog sensors Compared to the pre-programmed output from the
Weatherboard XBee Pro 900
Sends data back to ground station Camera
Takes sky-up oriented video
LATERAL FLIGHT DYNAMICS (LFD)
Objectives Introduce a determinable roll rate during flight after
burn-out Derive ODEs of the rockets roll behavior Use linear time invariant control theory to evaluate roll
dampening using rollerons Determine percent overshoot, steady state error, and
settling time Requirements
Ailerons deflect with an impulse to induce roll Rollerons inactively dampen roll rate
LFD
Procedures (after burnout) Phase I
Ailerons impulse deflect Rollerons locked Rocket naturally dampens its roll rate
Phase II Ailerons impulse deflect Rollerons unlocked Rollerons dampen out roll rate
LFD FIN LAYOUT
Uses pneumatic actuators to unlock rollerons and deflect ailerons
Rollerons locked using a cager
Rolleron
Cager
Aileron
Aileron Actuator
LFD MANUFACTURING
All components locally manufactured
Wheel on Mill Finished Wheel Casing
LFD ANALYSIS
Roll data points analyzed using numerical methods Plots roll characteristics Derives an ODE
Linear Time Invariant Control Theory Governing equation -
ODE transformed into Laplace form (frequency domain)
Impulse function (R(s) = 1) is applied to the plant (Gp) From the plants denominator the frequency can be
determined
FLOW ANGULARITY Objectives
Take differential pressure readings from each transducer
Determine angularity and boundary layer properties
Requirements Pre-calibration in wind tunnel will result in non-
dimensional coefficients Can be compared to flight results to obtain angularity
Calibration involves testing probe at multiple angles and flow velocities
FLOW ANGULARITY SCHEMATICS
FLOW ANGULARITY ANALYSIS
Non-dimensional coefficients
OUTLINE
Overview System Design Recovery Design Payload Design Vehicle Optimization Simulations and Performance Testing
VEHICLE OPTIMIZATION
Objective Optimize rocket geometry to maximize
performance Create a robust design that can accommodate
any uncertainties in the EOM Requirements
Determine uncertainty in the EOM Perform parametric analysis
VEHICLE OPTIMIZATION
Vertical EOM:
Manufacturer Specifications
From RockSim
Mass variance during thrust; Low uncertainty
Standard Atmosphere
Design Space Variable
VEHICLE OPTIMIZATION
Cost Function:
Want to maximize delta drag coefficient while still attaining target altitude
VEHICLE OPTIMIZATION
Design Space:
Span (in) = [4, 7, 10, 13]Root chord (in) = [5, 8, 11, 14, 17, 20]
Tip chord (in) = [4.5, 5, 5.5, 6, 6.5, 7, 7.5, 8]Fin location longitudinally (in) = [85, 90, 95,
100]
Determined based on minimum required dimensions for rolleron payload
VEHICLE OPTIMIZATION
Results: Fin location has no impact on vehicle drag and
can be altered to attain desired static margin Area of low sensitivity occurs at minimum values
of geometric design space Maximum drag capacity occurs at minimum
values of geometric design space
VEHICLE OPTIMIZATION
5
10
15
20
45
67
8-100
0
100
200
300
400
Root Chord (in)Tip Chord (in)
Co
st F
un
ctio
n
4
5
6
7
8
9
10
11
12
13
VEHICLE OPTIMIZATION
510
1520
45
67
84
5
6
7
8
9
10
11
12
13
Root Chord (in)Tip Chord (in)
Sp
an
(in
)
0.03
0.04
0.05
0.06
0.07
0.08
0.09
0.1
0.11
OUTLINE
Overview System Design Recovery Design Payload Design Vehicle Optimization Simulations and Performance Testing
FLIGHT SIMULATIONS
Used RockSim and MATLAB to simulate the rocket’s flight
MATLAB code is 1-DOF that uses ode45 Allows the user to vary coefficient of drag for
different parts of the rocket After wind tunnel testing, can get fairly
accurate CD values that can be used in the program
PERFORMANCE
MATLAB code is compared with RockSim Led to design changes
Maximum altitude predictions separated by 71 ft maximum altitude predicted by RockSim of 5352 ft
Room for unexpected mass or drag due to the simulations reaching over one mile
PERFORMANCE
Thrust-to-weight ratio 12.98 Need above 1 for lift-off
Rail exit velocity 76.8 ft/s
DRIFT CALCULATIONS
Windspeed (MPH) Rocket Drift (ft) Payload Drift (ft)0 0 05 292.9 304.510 603.8 873.315 912.6 1273.220 1538.9 1513.1
OUTLINE
Overview System Design Recovery Design Payload Design Vehicle Optimization Simulations and Performance Testing
COMPONENT TESTING SUMMARY
All components of the launch vehicle and three payloads have planned tests 21 tests outlined in detail in CDR report Ensure all design details will work as expected Allow the team to make necessary adjustments Make sure the vehicle has a successful
competition launch
COMPLETED TESTSTest # Components
TestedTesting Details Reason For Test Results
2 Body Tube Determine the strength of the charge necessary to separate
the different sections of the rocket by trying different sized
charges
Defer any complications during flight and ensure the rocket
can separate
Ejection charges were more than adequate to separate the rocket tube
10 Sub-Scale Motor
Determining the thrust curve of the motor
Determine whether the rocket motor has enough force to
launch rocket and its components to desired height
Motor test was successful, and had enough thrust to get the rocket to
required height
12 Analog Readings,
Temperature, Humidity, Solar, Pressure, UV
Sensors will be placed in the payload to record data.
Compare outputs with the digital weatherboard reads to
ensure accuracy
Humidity and Temperature Sensors tested and function properly others to
be tested during January
14 XBee's Send sensor data and receive it on computer
Required for USLI competition Successful was able to send 9 Degrees of Freedom data back to the ground station during Subscale
launch
SUBSCALE RESULTS – DEC 10TH
Launched with Aerotech J500 Payload ejected at apogee and both payload
and rocket drogue parachutes deployed Rocket drogue became entangled and only
partially opened IntimiGATOR main parachute deployed at
700 ft upper airframe became detached from the
middle airframe Payload main parachute did not deploy until
landing No damage sustained
SUBSCALE FLIGHT AND SIMULATIONS Altitude data gathered from the flight was compared to both
RockSim and MATLAB simulations The motor has a higher initial thrust than expected causing the
discrepancy for the first 5 seconds Altitude reached: 1921 ft.
RockSim predicted: 1896 ft. 9 degree launch angle led to the higher predicted altitude of the
1DOF MATLAB code
NEXT SUBSCALE LAUNCHES
February 11th, Bunnell, FL 1st Flight
Components tested Fin mount assembly SMD Payload main parachute deployment Dual separation Live data transmission
2nd Flight Components Tested
LFD payload system
QUESTIONS?
COMMUNITY OUTREACH
Gainesville High School 400 students throughout the school’s 6 periods Interactive PowerPoint Presentation covering the
basics of rocketry Derivations of relatable equations Model rocket launches
COMMUNITY OUTREACH
PK Yonge Developmental and Research School 150 6th grade students Interactive PowerPoint Presentation with videos Model rocket launches