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