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UNIVERSITY OF FLORIDA PDR PRESENTATION
OUTLINE
Project Organization Vehicle Design Payload Design Recovery System Simulations Future Work
PROJECT ORGANIZATION
OUTLINE
Project Organization Vehicle Design Payload Design Recovery System Simulations Future Work
MATERIAL AND DIMENSIONS Material: Reinforced Phenolic Diameter: 4 inches Length: 96.75 inches Weight: 22.55 lbs
Component Weight (lbs)
Fins/ Motor Mount 7.6
Electronics Bay 8.61
Recovery System 1.26
Nose Cone 1.54
Airframe/Paint 3.49
Total 22.55
Section Length (in)
Nosecone 15.75
Upper Airframe 28
Middle Airframe 13
Lower Airframe 40
Total 96.75
SYSTEM BREAKDOWN
Main Parachute
Main Piston
Avionics Bay
Aileron Deflection Package
Drogue Parachute
Drogue Piston
G10 Fins
LFD Fins
NoseconeFlight Computer
STABILITY CHARACTERISTICS
CG CP
• The center of pressure (CP) is located 79.427" from the nose tip
• The center of gravity (CG) is located 72.715" from the nose tip
• Static Stability Margin of 1.68 increasing to 2.20 at motor burnout
VEHICLE VERIFICATION
Vehicle verification focused on safe recovery and reliable platform for LFD payload
Testing will be done to allow triple redundancy for drogue and main separation events
Accurate Stress analysis for all components
OUTLINE
Project Organization Vehicle Design Payload Design Recovery System Simulations Future Work
LATERAL FLIGHT DYNAMICS PAYLOAD
Study of Lateral Dynamics of Rocket during flight
Attempts to quantify natural roll dampening of rocket
Compares natural roll dampening to dampening due to AIM 9M passive stabilization system
Determine resulting couple moment due to unlocked rollerons
Consists of LFD Fin, ADP, and Electronics
LFD FINS
PC Fin Halves
Trim Potentiometer
Rolleron
Linear Actuator G10 Mount
¼” Barrel Bolts
•G10 Mount epoxied to motor tube•2 fin halves bolted to permanent mount•Linear Actuator and Rolleron integrated separately
AILERON DEFLECTION PACKAGE
Aileron
Servo Motor
Bevel Gears
Torsional Springs
Gearbox
ELECTRONICS
Raspberry Pi Controls servo motor
for ADP Commands unlocking
of Rollerons Collects flight
dynamics data from gyros and trim potentiometers
PAYLOAD VERIFICATION
Ensure Launch Vehicle will be stable with integrated Payload.
Reliability of all systems allows for quality data acquisition.
OUTLINE
Project Organization Vehicle Design Payload Design Recovery System Simulations Future Work
RECOVERY
All payload systems remain with launch vehicle Drogue parachute released at apogee Wires unplug from LFD fins using umbilical
connection Main parachute released at 700 ft AGL
VEHICLE RECOVERY
Drogue parachute 24 inches in diameter (x-form)
Descent velocity: 65 ft/s Main parachute 96 inches in diameter
(circular) Descent velocity: 17 ft/s
Component Descent Velocity (ft/s)
Mass (slugs) Kinetic Energy (ft-lbf)
Nosecone 17 1.51 6.776242236Upper Airframe 17 10.16 45.59378882Lower Airframe 17 14.07 63.14021739
Kinetic Energy at Landing
RECOVERY SYSTEM INTEGRATION
Drogue parachute housed in lower airframe, below electronics bay
First separation event utilizes piston ejection and drag generated by fins for reliable separation
Main parachute housed in upper airframe, above electronics bay
Second separation event utilizes piston ejection
Shear pins prevent premature separation of nosecone and of lower airframe
RECOVERY REDUNDANCY
Dual PerfectFlite StratoLogger altimeters Two-way communication via Raspberry Pi
allows use of manual charge detonation system.
System will be tested thoroughly before put into use.
Ground/Software Testing Flight Testing
OUTLINE
Project Organization Vehicle Design Payload Design Recovery System Simulations Future Work
FLIGHT SIMULATIONS
OpenRocket and MATLAB used 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 Wind tunnel testing and full-scale
demonstration will allow more accurate Cd values
PRELIMINARY RESULTS MATLAB code is compared with OpenRocket Maximum altitude approximately 190 ft.
lower than OpenRocket but still near target High target altitude to account for drag due
to LFD Payload
MOTOR CHOICE
Cesaroni L1720 Max Thrust 394 lb Impulse 831 lb-s Powerful motor allows altitude to be met with
increased drag due to LFD Payload. Gives a thrust to weight ratio of 13.1
OUTLINE
Project Organization Vehicle Design Payload Design Recovery System Simulations Future Work
FUTURE WORK
Refine designs and tolerance all components Successfully fulfill subscale flight
requirements while testing flight software Begin manufacturing of rollerons, LFD fins,
and ADP Continue community outreach and
educational engagement functions Name Rocket