A Rocket Delivered Small-Scale Earth Observing...

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