a rocket delivered small-scale earth observing...
TRANSCRIPT
A Rocket Delivered Small-Scale Earth Observing Instrument
Preliminary Design Review
New Team - Project EOI
http://eoi.westrocketry.com
November 7th, 2014 Begin work on Subscale Model
November 21st, 2014 Subscale model completed
November 22nd, 2014 Scale model test flight
December 12th, 2014 Begin work on full scale vehicle
February 1st, 2015 Full scale vehicle completed
January 24th, 2015 Full scale test flight #1 (half
impulse)
February 15th, 2015 Full scale test flight #2 (full
impulse)
March 14th, 2015 Full scale test flight #3 (with
payload)
April 4th, 2015 Flight hardware and safety
checks
April 11th, 2015 Launch day, full scale flight #4
at MSFC
May 23rd, 2015 Full scale flight #5 (tentative) at
Bong State Recreational Area
2. Burnout A = 610ft
T = 4.0s
1. Ignition A = 0ft
T = 0.00s
3. Coast
4. Apogee/ Drogue deployment A = 5,280ft
T = 16.10s
6. Main Parachute A = 700ft
T = 132.75s
5. Payload descent under drogue
8. Landing A = 0ft
T = 117.92s
9. Payload Landing A = 0ft
T = 365.13s
7. Payload Main Parachute A = 750ft
T = 131.0s
• Motor ignition • Stable flight • Altitude of 5,280 feet AGL reached but not
exceeded • Both drogue and main parachute deployed • Successful payload deployment
• Vehicle and payload return to the ground safely with no damage (both reflyable on the same day)
• Successful recovery of the booster and payload
Length [in]
Mass [lbs]
Diameter [in]
Motor Selection
Stability Margin
[calibers]
Thrust to weight ratio
106 11.4 4.0 CTI K400GR 2.77 7.7
Letter Part
A Nosecone
B Payload drogue parachute
C Payload main parachute
D Payload
E Deployment electronics
F Vehicle drogue parachute
G Vehicle main parachute
H Motor Mount (54mm/75mm capable)
I Fins (4, 3/32” G10)
Payload Drogue Main E-Coupler B-Coupler
Ø4
”
32.4”
9” 9”
9” 14.9”
14.1”
Motor Mount
7.874”
6.417”
Ø2
.16
5
”
106”
• Fins: G-10 fiberglass 0.093 (3/32) in
• Body: 4 in MagnaFrame tubing • Bulkheads, centering rings: PLA • Motor mount: 54mm kraft phenolic
• Nosecone: plastic nose cone • Rail buttons: standard nylon • Motor retention system: Aeropak
screw-on motor retainer
• Anchors: 1/4" stainless steel U-Bolts • Epoxy: West or Loctite epoxy
Motor Diameter
[mm]
Total
Impulse
[Ns]
Burn Time
[s]
Stability
Margin
[calibers]
Thrust to
weight
ratio
CTI K400GR 54 1595 4.00 2.46 7.7
CTI K671RR 54 1802 2.62 2.36 12.9
CTI K580 54 1851 3.09 2.53 11.0
• We have selected CTI K400GR as our primary motor. • Our backup choices are CTI K580 and CTI K671RR.
Parameter Value
Flight Stability Static Margin 2.77 calibers
Thrust to Weight Ratio 7.7
Velocity at Launch Guide Departure (8ft
launch rail) 47mph
• Our rocket currently has a mass of 11.4lbs, which includes a 3.41lbs CTI K400GR motor.
• This estimate of the mass comes from the OpenRocket database where our rocket is being designed.
• If the rockets gains 5lbs of weight it will only reach altitude of 4,500ft which we consider unacceptable performance.
• The rocket would have to weigh 17.6lbs for the thrust to weight ratio to drop under 5 (underpowered rocket).
Max. thrust: 475N
Burn time: 4 s
Apogee: 5316 ft at 16s
Max. Acceleration: 10g (92m/s2)
Max. Velocity: 250 mph
Wind Speed [mph]
Altitude [ft]
Percent
Change in Apogee
0 5316 0.00
5 5308 -0.15
10 5296 -0.38
15 5285 -0.58
20 5177 -2.61
Apogee 700ft Apogee 700ft
V
E
H
I
C
L
E
P
A
Y
L
O
A
D
Parachute Diameter
[in]
Descent
Rate
[fps]
Deployment
Altitude
[ft]
Descent
Weight
[lbs]
Impact
Energy
[ft-lbf]
Booster Drogue 24 50 5316 6.0 -
Booster Main 48 24 700 6.0 54
Payload Drogue 18 45 5316 4.3 -
Payload Main 36 23 700 4.3 35
• Wp - ejection charge weight [g] • dP - ejection pressure (15 [psi]) • V - pressurized volume [in3] • R - universal gas constant
(22.16 [ft-lb oR-1 lb-mol-1]) • T - combustion gas temperature
(3,307 [oR])
Order/Altitude [ft]
Parachute Charge
[g]
1 / Apogee
Nosecone 1.37
Payload Drogue 0.41
Booster Drogue 1.36
2 / 700ft AGL Booster Main 1.56
Payload Main 1.13
Ejection charges will be finalized during static testing
Main Parachute Drogue Parachute
Same redundancy
scheme is used both for
vehicle and payload
recovery deployment
Wind Speed [mph]
Drift [ft]
Drift [mi]
0 0 0 .00
5 812 0.15
10 1625 0.31
15 2438 0.46
20 3250 0.62
CLOUD AIDED TELEMETRY : Cloud-Aided-
Telemetry (CAT) system uses an on-board
Android device and app to transmit
flight, tracking and payload data from
an airborne rocket using any available
cellular network. The data travel along
orange route to our data cloud (located
in Houston, TX) from where they can be
retrieved via blue route by any
connected device (such as cell phone)
and aid the search for the rocket and
payload. CAT is an 'opportunistic
uploader' and can store gigabytes of
data on-board while searching for
available connection.
This system has been successfully tested
at LDRS 33 launch during 8K+ flight.
Tested Components • C1: Body (including construction techniques) • C2: Altimeter • C3: Parachutes • C4: Fins • C5: Payload • C6: Ejection charges • C7: Launch system • C8: Motor mount • C9: Beacons • C10: Shock cords and anchors • C11: Rocket stability
• V1 Integrity Test: applying force to verify durability.
• V2 Parachute Drop Test: testing parachute functionality.
• V3 Tension Test: applying force to the parachute shock cords to test
durability
• V4 Prototype Flight: testing the feasibility of the vehicle with a scale
model.
• V5 Functionality Test: test of basic functionality of a device on the ground
• V6 Altimeter Ground Test: place the altimeter in a closed container and
decrease air pressure to simulate altitude changes. Verify that both the
apogee and preset altitude events fire. (Estes igniters or low resistance
bulbs can be used for verification).
• V7 Electronic Deployment Test: test to determine if the electronics can
ignite the deployment charges.
• V8 Ejection Test: test that the deployment charges have the right amount
of force to cause parachute deployment and/or planned component
separation.
• V9 Computer Simulation: use RockSim to predict the behavior of the
launch vehicle.
• V10 Integration Test: ensure that the payload fits smoothly and snuggly
into the vehicle, and is robust enough to withstand flight stresses.
V1 V2 V3 V4 V5 V6 V7 V8 V9 V10
C1 P P P P
C2 P P P
C3 P P P P P
C4 P P
C5 P P P
C6 P P P P
C7 P P
C8 P P
C9 P P P
C10 P P P
C11 P P P P
P = planned
C = successfully completed
Image the ground at five
spectral bands and use
a classification algorithm
to identify the ground
features
• Data collected by the
payload is accurate
• No hardware failures
• Payload is recovered and
undamaged
We believe that our land
observing instrument
payload will be able to
precisely tell us various
statistics about ground
cover of the observed
land.
Camera array of Earth
Observation Instrument
(EOI). Five different
cameras capture
synchronized images in
five different spectral
bands – red, green, blue,
near infrared and
thermal.
Image analysis and
classification will be used
to identify the ground
features.
Raspberry Pi camera,
one of the five cameras
Payload block scheme – Raspberry Pi computer collects image data from cameras, attitude data
from compass and gyroscope, 3D location data from altimeter and GPS. The image data are
processed on-board and then transmitted with all other data using C. A. T. (Cloud Aided Telemetry) transmitter via cellular network to our datacloud.
Nose
cone Shock
Cord
Drogue
Parachute Payload
E-bay
Drogue
Ejection
Charge
Shock
Cord
Main
Parachute
Main
Ejection
Charge
Drogue
Tube
Main
Tube
EJECT
EJECT
EOI
Field
of View
Bulkhead
Deployment
Electronics
• Independent variables z Probe Altitude
X GPS location
• Dependent Variables R Intensity of pixels in red band
G Intensity of pixels in green band B Intensity of pixels in blue band T Intensity of pixels in thermal band (LWIR)
IR Intensity of pixels in infrared band (SWIR)
• We will use commercially available
accelerometers, altimeters,
gyroscopes, GPSs, transmitters
• The sensors will be calibrated
• We will do extensive testing on the
ground prior to the rocket launch
Test Measurement
Acceleration Accelerometer
Attitude Gyroscope
Direction Compass
Altitude Altimeter
RGB intensity Raspberry Pi Camera
SWIR intensity Pi NoIR Camera
LWIR intensity FLIR Lepton Camera
Recording Device
Bytes Per
Data Point
Number of Sensors/
Axes
Data Points Per Second
Total Bytes Per
Second
Gyroscope (3D) 2 × 3 × 50 = 300
Compass (3D) 2 × 3 × 50 = 300
Camera array 15M × 5 × 0.2 = 15M
TOTAL BYTES PER MISSION ~2gb
Estimated Maximum Amount of Memory Needed: 2 Gb, we will use 4GB
SD card to prevent memory overruns.
• C1: Camera array • C2: Accelerometer
• C3: Altimeter • C4: Gyroscope • C5: GPS
• C6: Transmitter • C7: EOI Container • C8: Parachutes
• V1 Functionality Test: Test of basic functionality
of a device on the ground
• V2 Integrity Test: Applying force to verify
durability
• V3 Calibration Test: Calibration and test of
accuracy and precision
• V4 Battery Test: Test for sufficient amount of
battery power
• V5 Connection Test: Test of proper connection
of components
V1 V2 V3 V4 V5
C1 P P P
C2 P P P P
C3 P P P
C4 P P
C5 P P
C6 P P P
C7 P
C8 P P
P = planned
C = successfully completed
Date School Outreach # of People
Oct. 10, 2014 Randall Elementary School Homecoming Parade 200
Oct. 18, 19, 2014 Wisconsin Science Festival
Alka-Seltzer Rockets, Pneumatic Rockets 2000
Nov. 1, 2014 Science Saturday Pneumatic Rockets, Interactive Payloads 500
Nov. 15, 2014 Kids Express Alka-Seltzer Rockets 50
Feb. 21, 2015 Physics Open House Displays, Presentations 200
Mar. 7, 2015 O’Keefe Middle School- Super
Science Saturday
Alka-Seltzer Rockets, Pneumatic Rockets 80
Mar. 14, 2015 Franklin and Randall Elementary- Super Science Saturday
Alka-Seltzer Rockets, Pneumatic Rockets
100
Total: 3130
Wisconsin
Science
Festival
Raking
Homecoming
Parade