University of Florida Rocket Team Third General Body Meeting October 10, 2013
Preview:
Citation preview
- Slide 1
- University of Florida Rocket Team Third General Body Meeting
October 10, 2013
- Slide 2
- Todays Meeting Project Updates Design Opportunities Office
Hours Presentations Motor Basics OpenRocket Recovery
- Slide 3
- Hybrid Competition Propulsions Research Bringing 8 teams Six
highest altitude Two 2,000 feet Meeting yesterday Sugar Motors
Potential launch Updates
- Slide 4
- Static Motor Test Stand Variable motor diameter 24mm-98mm
Withstand 3000 N with reasonable factor of safety Operate upwards
and downwards Measure force over time (load cell) Clamp into
ground.
- Slide 5
- Static Motor Data Acquisition LabVIEW VI Measure and interpret
data from the load cell NI DAQ (OOTB or 6009) Needs to determine
Total Impulse Average Thrust Max Thrust Thrust Curve Burn Time
- Slide 6
- Fin Mount Apparatus Apparatus to help mount fins symmetrically
Multiple rockets Either 3 or 4 fins Multiple body diameters/motor
mount tubes Account for changing location of centering rings
- Slide 7
- Office Hours MAE A 211 Monday, 9:30 AM 12:00 PM Tuesday, 2:30
4:00 PM Friday, 9:30 AM 12:00 PM
- Slide 8
- BASICS OF ROCKET MOTORS Propulsion
- Slide 9
- How Rockets Work Newtons Third Law of Motion: For every action
there is an equal and opposite reaction Rocket motor = energy
conversion device - Matter (solid or liquid) is burned, producing
hot gases. - Gases are accumulated within the combustion chamber
until enough pressure builds up to force a part of them out an
exhaust port (a nozzle) - Thrust is generated by a pressure buildup
within the combustion chamber and by mass ejection through the
nozzle. - Combustion chamber geometry, throat diameter, and nozzle
geometry govern performance and efficiency (Conservation of
Momentum-Fluids)
- Slide 10
- Different Types of Motors
- Slide 11
- Solid Motor Basics
- Slide 12
- Bates Grains
- Slide 13
- Rocketry Model Rocketry Uses motors A-G Anyone can launch Class
1 Is made of paper, wood, or breakable plastic Uses a slow burning
propellant High Powered Rocketry Needs certifications Uses motor
more than 160 N-seconds of total impulse Uses motor more than 80 N
average thrust Exceeds 125 g of propellant Uses hybrid motor Rocket
weighs more than 1500 g Includes any airframe parts of ductile
metal Class 2
- Slide 14
- High Powered Rocketry Level Certifications Level 1- Uses H (320
N-seconds) or I motors (640 N-seconds) Level 2- J, K, L Level 3- M,
N, O Beyond O is Class 3 and requires waivers (total impulse
greater than 40,960 N-seconds) Numbers of Motor Example H64-8 H is
the total impulse (between 160-320 N-s) 64 N is the average thrust
8 seconds is the delay ejection charge To determine motor burn
divide total impulse by average thrust
- Slide 15
- INTRODUCTION TO FLIGHT DYNAMICS OpenRocket
- Slide 16
- AN INTRODUCTION TO THE RECOVERY SUBSYSTEM Recovery
- Slide 17
- A reliable system to safely land the rocket. Must be reusable
without repairs.
- Slide 18
- Goal Consistently return a rocket to the ground without damage
to the rocket or objects on the ground. Critical for continued
testing of payload
- Slide 19
- Possible Designs Featherweight Recovery Small rockets Flutter
down Tumble Recovery System induces tumble Nose-Blow Recovery
Nosecone induces tumble Parachute Ejected from rocket Increases
drag Glide Recovery Airfoil deployed
- Slide 20
- Possible Designs Continued Helicopter Recovery Blades deployed
Rocket autorotates
- Slide 21
- DUAL DEPLOYMENT
- Slide 22
- Rocket undergoes powered and unpowered ascension
- Slide 23
- Ascension During ascension rocket naturally orients itself into
wind Drifts an amount up range depending on wind speed
- Slide 24
- Altimeter detects apogee and sets off ejection charges. The
nose cone is ejected and the drogue parachute is deployed
- Slide 25
- Apogee Apogee is highest point the rocket attains Apogee is
detected by the altimeter Altimeter controls the ejection
charges
- Slide 26
- Ejection charges Forces the shear pins to break and deploys the
drogue parachute E-fuses are detonated by the altimeter Charge
Types Black Powder Substitutes CO2 Canister
- Slide 27
- Charge Testing
- Slide 28
- Drogue parachute Smaller X-Form Parachute Sufficiently lowers
the speed without a large horizontal drift Deployed at apogee
- Slide 29
- Selecting parachute size FD = (r)(Cd)(A)v 2 FG= mg FD=FG
(r)(Cd)(A)v 2 =mg A=D 2 /4 D = sqrt( (8mg) / (*r*Cd*v 2 ) ) V=
sqrt( (8 m g) / (*r*Cd*D 2 ) ) Cd=Coefficient of Drag r=density of
air v=velocity
- Slide 30
- At a preset attitude, around 700ft, the second ejection charge
will deploy the main parachute
- Slide 31
- Main Parachute Detonated by the altimeter at a specified
altitude Also uses ejection charges to deploy Allows for a much
slower descent rate
- Slide 32
- Rocket is located and recovered
- Slide 33
- Locating the rocket Transmits GPS coordinates to locate the
landed rocket
- Slide 34
- Meeting Begin the design phase of the recovery sub-system
Friday Oct, 11 5:00PM Library West Room 230
- Slide 35
- Upcoming Meetings Propulsions Research Right here, right now
(brief) CanSats Tuesday, Oct. 15, 6:30 at the Energy Park GBM
Thursday, Oct. 24, 6:15 in Little 121