university of florida intimigator frr
DESCRIPTION
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: - PowerPoint PPT PresentationTRANSCRIPT
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
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 5
Drogue Parachutes and Shock Cord 1.5
Nosecone and Pressure Payload 4.25
Body Tube 6.25
Total 30
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 2.78
CP = 91.1”
CG = 74.2”
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 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 140.01Airframe (Lower, Mid; shear pinned) 683.57Payload 58.54
Kinetic Energy at Landing (Under Main)Component Kinetic Energy (ft-lbf)Payload 18.9Nose Cone 14.9Top Body Tube 39.8Middle/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
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 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 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 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 713 ft due to Cd
value differences 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 CALCULATIONSLaunch Angle (deg) Wind (mph) Range (ft)
0 0 00 5 780.730 10 2335.40 15 2535.585 0 963.965 5 202.775 10 678.225 15 160810 0 188610 5 934.510 10 120.110 15 622.9
IntimiGATOR Drift
SMD Payload Drift
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 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 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
Thank You!
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