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UNIVERSITY OF FLORIDA
INTIMIGATOR FRR
OUTLINE
Overview
System Design
Recovery Design
Payload Design
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
Simulations and Performance
Testing
SYSTEM
VEHICLE DIMENSIONS
Diameter: 6 inches
Length: 115 inches
Weight: 30 lbs
Section
Nosecone
24
Upper Airframe
44
Avionics Bay
3
Mid Airframe
16
Lower Airframe
28
Total
Component
Fins (2 with rollerons and 2 without)
Pneumatics Bay
Main Parachute/Shock Cord and Piston
Weight (lbs)
5
1.5
3
Avionics Bay
3.25
Payload and Main Drogue Parachute Piston
0.25
Payload Main Parachute and Housing
Drogue Parachutes and Shock Cord
5
1.5
Nosecone and Pressure Payload
4.25
Body Tube
6.25
Total
30
Length (in)
115
STATIC STABILITY MARGIN
CG = 74.2”
CP = 91.1”
The static stability margin is 2.78
FINS
Fins and mount made
from ABS plastic on a
rapid prototype machine
Dimensions:
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
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 and SMD Payload
Kinetic Energy During Decent (Under Drogue)
Component
Kinetic Energy (ft-lbf)
Nose Cone
140.01
Airframe (Lower, Mid; shear pinned)
683.57
Payload
58.54
Kinetic Energy at Landing (Under Main)
Component
Kinetic Energy (ft-lbf)
Payload
18.9
Nose Cone
14.9
Top Body Tube
39.8
Middle/Bottom Body Tube
57.4
OUTLINE
Overview
System Design
Recovery Design
Payload Design
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
Weatherboard
Compared to the pre-programmed output from the
Weatherboard
XBee Pro 900
Senses atmospheric data and transmits to the
microcontroller using synchronous communication
Analog sensors
Samples analog sensors and reads outputs from
Weatherboard and GPS
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 burnout
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 ASSEMBLED FIN
LFD AIR TANK SPECIFICS AND FAILURE
MODES
Ailerons fail in the neutral position
Loss of air pressure fails to the neutral position
Air Tank
Type
14.5 cu. In. AL 150psi pressure tank
Material
AL with sealed steel cap
Used for
providing pressure to the pneumatic cylinders
MEOP
150psi
Safety Factor
2
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 nondimensional 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
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
Maximum altitude predictions separated by 713 ft due to
Cd value differences
Led to design changes
maximum altitude predicted by RockSim of 5475 ft
MATLAB predicts 4772 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
IntimiGATOR Drift
SMD Payload Drift
Launch Angle (deg)
0
0
0
0
5
5
5
5
10
10
10
10
Wind (mph)
0
5
10
15
0
5
10
15
0
5
10
15
Range (ft)
0
780.73
2335.4
2535.58
963.96
202.77
678.22
1608
1886
934.5
120.1
622.9
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 FRR 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
SOME COMPLETED TESTS
Test #
2
Components
Tested
Body Tube
Testing Details
Reason For Test
Results
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
Full-Scale Static
Motor Test
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
Launched with Aerotech J500 3 separate times
1st subscale launch had a successful deployment
of the SMD mock payload
2nd subscale launch showed that the SMD Main
parachute housing was successful
3rd subscale launch included the LFD payload
fins with the rollerons unlocked
Rocket remained completely stable throughout flight
and visually showed no roll
FULL SCALE LAUNCH
Occurred on March 17, 2012
Launched with a Cesaroni L1720WT
Reached an altitude of 4294 ft.
Sustained some damage on impact due to no main parachute
deployment
FULL SCALE LAUNCH- LACK OF ALTITUDE
Upper airframe launched
was 4” longer than designed
Centering rings attached
with screw inserts that
sheared off
Motor impulse was not fully
transferred to the rocket
Coefficient of drag may be
higher than anticipated
A scale model of the rocket is
being rapid prototyped to
perform wind tunnel testing
FULL SCALE LAUNCH- RECOVERY
Separation did not occur at the main event at 700ft
AGL
Multiple further tests are being performed to ensure
separation
SPONSORS
NASA
Boeing
Millennium Engineering and Integration
Northrop Grumman
Pratt & Whitney
Acquip, Inc.
University of Florida
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