University of Florida Rocket Team Preliminary Design Review Presentation
38
University of Florida Rocket Team Preliminary Design Review Presentation
description
University of Florida Rocket Team Preliminary Design Review Presentation. Outline. Overview Vehicle Design Motor Choice Flight Dynamics and Simulations Recovery Payloads Electronics Component Testing Future Work. Overview. Mass: 91.16 pounds Target Altitude: 10,000 feet. - PowerPoint PPT Presentation
Transcript of University of Florida Rocket Team Preliminary Design Review Presentation
University of Florida Rocket TeamPreliminary Design Review
Presentation
Outline
OverviewVehicle DesignMotor ChoiceFlight Dynamics and SimulationsRecoveryPayloadsElectronicsComponent TestingFuture Work
Upper Airframe
Upper Electronics Bay
Middle Airframe
Piston Hatch
Lower Electronics Bay
Heat-Coated
BulkheadBoattail
Lower Airframe
Baffles Centering Rings
Overview
Mass: 91.16 poundsTarget Altitude: 10,000 feet
Outline
OverviewVehicle DesignMotor ChoiceFlight Dynamics and SimulationsRecoveryPayloadsElectronicsComponent TestingFuture Work
Dimensions
About 135 inches longInner diameter: 6.0 inchesOuter diameter: 6.2 inches
Airframe
Four sections of airframe Upper Airframe (24 inches) Upper Electronics Bay (18 inches) Middle Airframe (18 inches) Lower Airframe (48 inches)
E-class fiberglass tubes rolled in house
Upper Electronics Bay
Features a hatch to allow for easy access to the electronics
L-shaped platform to maximize space
Lower Electronics Bay
Located in lower airframe just above motor
Lower plate with hole in center for wiring
Lower Airframe
Lower electronics bay, centering rings, and motor tube slide out as one pieceBulkhead above motor is heat coated to
protect electronicsThreaded rod lines up holes and transfers
thrust to the bulkhead and 2 centering rings
Bulkheads and Centering Rings
Machined from aluminum
Fasten to the airframe with 4 screws
PreciseRelatively thin and
lightweight
Boattail
To reduce base dragServes as motor
retention and motor centering
Houses the camera for ground scanning payload
Exposed length: 2.67 in
Outline
OverviewVehicle DesignMotor ChoiceFlight Dynamics and SimulationsRecoveryPayloadsElectronicsComponent TestingFuture Work
Motor Choice
0 0.5 1 1.5 2 2.5 3 3.5 4 4.50
100
200
300
400
500
600
700
800
900
Animal Works N2700BB-P Thrust Curve
Time (seconds)
Thru
st (
lbf)
Animal Works N2700BB-P SpecficationsTotal Impulse (lbf*s) 2551.6Average Thrust (lbf) 624.3Max Thrust (lbf) 791.3Burn Time (s) 4.09Launch Mass (lb) 21.9Empty Mass (lb) 11.3
• Chosen for consistency and geometry• Certified by National Association of
Rocketry (NAR)
Outline
OverviewVehicle DesignMotor ChoiceFlight Dynamics and SimulationsRecoveryPayloadsElectronicsFuture Work
Stability Characteristics
0 5 10 15 20 251.8
2
2.2
2.4
2.6
2.8
3 Stability Margin Movement
Time (seconds)
Stab
ility
Mar
gin
(cal
)
Rail Exit Velocity = 70 ft/sec
Thrust to Weight Ratio = 6.85
Flight Simulations
OpenRocket software used to simulate rocket’s flight
Wind tunnel testing in the near future will allow for more accurate drag coefficient values
Altitude versus Time
0 50 100 150 200 250 3000
2000
4000
6000
8000
10000
12000
Altitude vs. Time
Time (seconds)
Alti
tude
(ft
)
• Maximum altitude of 10,200 feet• Drogue parachute deployment at 25 seconds (apogee)• Main parachute deployment at 210 seconds, 700 feet of
altitude
Velocity and Acceleration versus Time
0 25 50 75 100 125 150 175 200 225 250 2750
200
400
600
800
1000
Velocity vs. Time
Time (seconds)
Velo
city
(ft
/s)
0 5 10 15 20 25 30 35 40 45 500
50
100
150
200
250
300
350
Acceleration vs. Time
Time (seconds)
Acce
lera
tion
(ft
/s2)
• Peak velocity of 892 ft/s at 4 seconds
• Shows drogue and main parachute deployment at 25 and 210 seconds respectively
• Peak acceleration of 292 ft/s2 at 1.5 seconds
• Shows acceleration from drag and gravity up to apogee at 25 seconds
• Constant velocity under drogue, zero acceleration
Outline
OverviewVehicle DesignMotor ChoiceFlight Dynamics and SimulationsRecoveryPayloadsElectronicsComponent TestingFuture Work
Recovery
ObjectivesReusable without repairsKinetic Energy each piece is less than 75 ft-
lbfMain and drogue parachute manufactured by
teamGPS tracking deviceMinimal crosswind drift
Recovery System
DrogueDeployment at apogee60 inches in diameterSemi-ellipsoid canopy
shapeCharge baffle ejection
systemDescent velocity: 48.1
ft/s
MainDeployment at 700ft168 inches in
diameterSemi-ellipsoid canopy
shapePiston Ejection
SystemDescent velocity:
12.4ft/s
Parachute Manufacturing
Ripstop nylonGore designHem tapeShroud lines
Charge Baffle
Two discs with non overlapping circular patters of holes
Cools gasses from ejection charges and removes particulates
Used to protect drogue parachute
Kinetic Energy
Component Descent Rate (ft/s) Mass (slugs) Kinetic Energy (ft-lbf)
Nosecone 12.4 0.0544 4.199
Piston 12.4 0.0162 1.248
Upper Airframe 12.4 0.619 47.81
Lower Airframe 12.4 0.817 63.11
Outline
OverviewVehicle DesignMotor ChoiceFlight Dynamics and SimulationsRecoveryPayloadsElectronicsComponent TestingFuture Work
Ground Scanning System
Ground Scanning System to detect hazards in the landing area
Take an image of landing areaScan for potential hazards in real-timeSend scanned image to Ground Station in
real-time
Design Overview
Picture is taken and sent to Lower Computer Image is saved, then sent to Upper Computer
via onboard WiFiImage is run through custom color-mapping
hazard detection software Hazard is defined as the edge, corner or cliff of any
surface or area. Scanned image is sent to ground station via
RF signal
Camera Integration
Camera will mount in boattailTitanium Nitride Heat Coating on boattail
Payload Verification
Saved control image analyzed for hazards and quantified by team
Success criteria requires 75% of analyzed hazards to be detected by software
Boost Systems Payload
Enables characterization of realtime internal forces imparted by motor during burnout
Provides a novel way to calculate drag on the rocket
Enables in-flight, real time structural analysis of component assemblies
Bulk Head
Motor Tube
Strain Gage
Motor Casing
Triboelectric Effect Analysis
Substantial charge build up due to triboelectric effects can institute a Faraday cage hindering incoming and outgoing signals
Payload reveals a novel way to characterize the effects of triboelectric buildup on antenna signal power in a simple, low resource, recoverable, and easily instituted package
System Design Conductive paint is used to coat the payload bay which houses the antenna for the rocket. Fastened in contact to the conductive paint is a wire which is run down the length of the
rocket and connected to static wicks located on the trailing aft edge of the fins. A relay is located inline with the wire allowing connection to be made from the conductive
paint to the static wicks. During lift off the antenna communicates with a groundstation where the received power is
measured. The the relay is disconnected and charge is allowed to accumulate on the conductive
coating forming a Faraday cage disrupting the out coming signals to an extent. Once around 5,000 ft the relay is connected allowing charge to accumulate now on the
static wicks ridding the payload bay of the faraday cage. The sudden spike in signal power should be picked up by the groundstation and directly
related to the charge build up on the conductive paint.
Outline
OverviewVehicle DesignMotor ChoiceFlight Dynamics and SimulationsRecoveryPayloadsElectronicsComponent TestingFuture Work
Image Processing
Data Acquisition & Communication
Outline
OverviewVehicle DesignMotor ChoiceFlight Dynamics and SimulationsRecoveryPayloadsElectronicsComponent TestingFuture Work
Component Testing
Recovery TestingStructural TestingElectronics TestingMotor TestingPayload Component Testing
Outline
OverviewVehicle DesignMotor ChoiceFlight Dynamics and SimulationsRecoveryPayloadsElectronicsComponent TestingFuture Work
Future Work
Develop detailed, final designManufacture subscaleComponent TestingOrder all materialsSubscale Launch, Feb. 8th
