NASA USLI Flight Readiness

Review Presentation

1

University of California, Davis

Overview

• Compliance Matrix

• Project Plan

• Launch Vehicle Design

• Rocket Performance and Stability

• Test Plans and Procedures

• Moving

• Compliance Matrix

• Closing

2

Compliance Matrix (1/2)

3

Item Slide Numbers

Launch vehicle dimensions 11,12

Key design features 13,14

Motor Description 15

Flight stability + static margin 15

Thrust-to-weight and rail exit velocity 15

Mass statement 18

Parachute size, Descent rates 19

Kinetic energy at key phases of mission and landing

20-24

Compliance Matrix (2/3)

Item Slide Numbers

Predicted altitude in 5,10,15,20 MPH 26

Predicted drift in 5,10,15,20 MPH 26

Test plans and procedures 27

Full scale flight test 27

Recovery system tests 27,28

Requirements Verification 27,28

Payload design and dimensions 37

Key design features of payload 38

Payload integration 39

4

Compliance Matrix (3/3)

Item Slide Numbers

Interfaces with ground systems 41

5

PROJECT PLAN

6

Budget and Funding – on track

• Total Expenses of Rocket: $1363.97

• Rocket Expenses guaranteed

• Travel Expenses guaranteed

7

Current Sponsorship Money

University of California Davis College of Engineering: $1000.00

University of California Davis MAE Department: $1000.00

University of California Davis Club Finance Council: $1725.56

California Space Grant Consortium $10,000.00 Total Operating Budget $13,725.56

Milestones – on track

8

10-22-12 Web Presence Established Completed

10-29-12 PDR Report Posted Completed

11-16-12 PDR Presentation Completed Completed

1-5-13 Prototype Launch Completed

1-14-13 CDR Report Posted Completed

1-31-13 CDR Presentation Complete Completed

3-3-13 Initial Payload Testing Completed

3-9-13 Full Scale launch with payload Completed

3-18-13 FRR Posted Completed

3-30-13 Full Scale launch with payload (2) Completed

4-3-13 FRR Presentation Complete In Progress

4-17-13 LRR Conducted On Track

4-20-13 Launch Date On Track

5-6-13 PLAR Posted On Track

Educational Engagement

• Engaged 367 elementary and middle school students

• Conducted rocket launch demonstrations

• Led classroom rocket construction projects

• Led field trip/tour of U.C. Davis rocket team facilities

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Launch Vehicle Design

10

Launch Configuration Total Height 71.5”

Diameter 4”

Number of fins 4

Fin attachment Slotted body tube + Epoxy Fillets

Fin Span 14.43”

Total Launch Weight (without motor) 228 oz

Total Launch Weight (with motor) 281 oz

Rail Size 1” (Can be modified for larger)

11

Launch Dimensions

12

Key Design Features (1/2)

• Aerodynamics

– Modeled using RockSim software to ensure

stability, drift radius, and target altitude

• Structures

– Adjustable nosecone ballast system

– Custom fin jig for precise alignment

– West Systems 105/206 epoxy specification

13

Key Design Features (2/2)

• Structures cont.

– West Systems Epoxy with Colloidal Silica

• Propulsion

– Aerotech K550W motor • RockSim Calculations

• Full Scale Test

• Launch Operations

– Detailed set-up and prelaunch checklist

– Test launches

14

Motor Description

Manufacturer AeroTech

Mfr. Designation K550W

Motor Type Reload

Diameter 54.0 mm

Length 41.0 cm

Total Weight 1487 g

Prop. Weight 889 g

Average Thrust 396.8 N

Maximum Thrust 655.3 N

Total Impulse 1539.1

Burn Time 3.9 s

Rocket Flight Stability

• CG: 45.12 in from nose tip

• CP: 56.22 in from nose tip

• Static margin: 3.77 Calibers

Rocket Performance

• Thrust-to-weight Ratio: 5.04

• Rail exit velocity: 74 ft/s

• Reached an altitude of almost 4800 feet

• Overweight rocket (improvements being

made)

Mass Statement • Below is the weight of the rocket at the March

2nd full scale launch

• Mass margin to be presented

Component Weight (lbf)

Nose Cone 1.20

Forward Body Tube 1.48

Aft Body Tube (with fins and boat-tail) 4.00

Motor Casing 0.97

Main Parachute and Drogue Parachute 3.19

Payload 2.02

E-bay 1.56

Motor 3.34

Total: 14.41

19

Parachute Sizes and Descent

Rates

• Main parachute: Iris Ultra 72'' Parachute

• Drogue parachute: Classic Elliptical 18”

20

Descent Rates, KE (1/6)

Time (s)

Drogue charges fire Time: 17.20 s Altitude: 4425 ft

Main charges fire, no descent rate change Time: 78.0 s Altitude: 831 ft

Landing Time: 92.0 s Altitude: 60 ft

Alt

itu

de

(ft

AG

L), A

xial

A

cce

lera

tio

n (

G’s

)

Full-Scale Prototype Rocket Test Launch

21

• Drogue Descent for Full-Scale Prototype Test Launch • Descends for: 3594 ft • Apogee to main chute ejection charges: 60.80 s

• 59.87 s in simulation • Drogue descent rate: 59 ft/s

• 72 ft/s in simulation • Drogue descent KE: 676.7 ft-lbf

• Main Descent for Full-Scale Prototype Test Launch • Main chute did not deploy

Descent Rates, KE (2/6)

22

Time (s)

Drogue charges fire Time: 18.14 s Altitude: 4765 ft

Main charges fire Time: 82.77 s Altitude: 818 ft

Alt

itu

de

(ft

AG

L), A

xial

A

cce

lera

tio

n (

G’s

)

Backup charge fires and Raven stops collecting data

Final Competition Rocket Test Launch

Descent Rates, KE (3/6)

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0

200

400

600

800

1000

1200

1400

1600

1800

0 50 100 150 200 250

Alt

itu

de

(m

)

Time (s)

Altitude vs Time (Final Competition Rocket Test Launch)

Descent Rates, KE (4/6) Data from our Payload Controller:

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Descent Rates, KE (5/6)

• Drogue Descent for Final Competition Rocket Test Launch • Descends for: 3947 ft • Apogee to main chute ejection charges: 64.63 s

• 66.62 s in simulation • Drogue descent rate: 61 ft/s

• 78 ft/s in simulation • Drogue descent KE: 824.02 ft-lbf

• Main Descent for Final Competition Rocket Test Launch • Data point 1 during main decent: 527.72 ft, 92.91 s • Data point 2 during main decent: 325.23 ft, 106.69 s

• Main chute decent rate: 14.69 ft/s • KE at landing: 47.79 ft-lbf

25

Prototype Test Launch (01/05/13)

• KE at Burnout (max KE): 75,210 ft-lbf • Drogue descent rate: 59 ft/s • Drogue descent KE: 676.7 ft-lbf • Main descent rate: Main did not deploy • KE at landing (w/o main): 588 ft-lbf

Full Scale Competition Rocket Test Launch (03/02/13) • KE at Burnout (max KE): 103,911 ft-lbf • Drogue descent rate: 61 ft/s • Drogue descent KE: 824.02 ft-lbf • Main descent rate: 14.69 ft/s • KE at landing: 47.79 ft-lbf

Summary

Descent Rates, KE (6/6)

Drogue Chute: 18’’ Diameter Main Chute: 72’’ Diameter

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Simulated Altitude and Drift of Final Competition Rocket Using RockSim

5 mph Wind 10 mph Wind 15 mph Wind 20 mph Wind

Predicted Altitude

(ft) 4813.73 4732.49 4599.3 4422.04

Predicted Drift (ft) 73.93 346.16 565.45 567.91

Predicted Altitude and Drift (1/1)

27

Test Plans and Procedures

• First Test Launch

– Goal: Gain experience with launch procedure and

verify functionality of launch components

– Exposed configuration falws and gave real world

results

– Discrepancy between simulation and results

Altitude Projected Altitude

Launch 1 4400 ft 5137 ft

28

• Second Test Launch

• Goal: Implement changes made

• Payload integration

• Main chute, backup altimeter

• Improve launch operations

• Fly the K550 motor

Test Plans and Procedures

Altitude Projected Altitude

Launch 1 4763 ft 5450 ft

29

Simulation Discrepancies

• True cause of simulation discrepancy

• Plan to reach 1 mile 281 oz (-0)

(17.56 lbf)

276 oz (-5)

(17.25 lbf)

271 oz (-10)

(16.94 lbf)

266 oz (-15)

(16.63 lbf)

261 oz (-20)

(16.31 lbf)

Extreme High 4910.17 5039.2 5171.2 5306.1 5443.7

0 MPH Wind 4841.4 4979.0 5107.4 5238.5 5372.1

5 MPH Wind 4817.68 4955.5 5084.2 5215.5 5349.5

10 MPH Wind 4744.36 4888.9 5012.1 5144.2 5279.0

15 MPH Wind 4622.44 4761.7 4891.5 5024.4 5160.1

20 MPH Wind 4458.01 4597.6 4727.7 4861.1 4977.5

Extreme Low 4407.27 4527.6 4655.1 4784.48 4916.5

Weight Reduction/Mass Margin

30

Component Weight (lbf) Est. Reduction (lbf)

Nose Cone 1.20 -.188

Forward Body Tube 1.48 0

Aft Body Tube (with fins

and boat-tail) 3.80 0

Motor Casing 0.97 0

Main Parachute and

Drogue Parachute 3.19 -.156

Payload 2.02 -.500

E-bay 1.56 -.375

Motor 3.34 0

Total: 17.56 -1.219

Total after reduction: 16.33

Weight Reduction/Mass Margin

Weight [oz (lbf)]

Worst conditions 253.0 (15.8125)

Best conditions 268.0 (16.75)

31

To achieve 5,280 ft:

Ideal mass margin: 15oz (.9375lb)

32

Recovery System Tests

• Ejection charge tests

• Altimeter testing

33

Structural Test

• Epoxy Testing

• Improve technique and test strength

• Combined fin jig testing

34

Summary of Requirements Verification

Deliver payload to 5280ft Designed (4763ft max thus far)

Carry at least one altimeter Verified

Obtain altitude by beeps Verified

Remain subsonic Verified

Recoverable and Reusable Verified

Maximum 4 independent sections Verified

Preperation time of 2 hours Verfied

Capable of remaining in launch config for 1 hour

Verified

Compatible with 8ft, 1 in launch rail Verified

Launched by a 12 volt DC system Verified

Criteria for full scale flight met Verified

Maximum budget of $5000 Verified

No prohibitions violated Verified

PAYLOAD DESIGN

35

Design: Electronics • ArduPilot 2.0 with MediaTek GP

• Embedded MPU-6000 Gyroscope and Accelerometer

• Embedded MS5611 Barometric Pressure Sensor

• Includes MediaTek MT3329 GPS Daughter Board

• TSL250R Light to Voltage Sensor

• LM61CIZ Analog Temperature Sensor

• HIH-5030 Analog Humidity Sensor

• 3DR Radio Transmitter and Antenna

• 3DR USB Receiver and Antenna

• Ground Station computer

36

ArduPilot

Analog Inputs

+ADCs

External Analog Sensors

TSL250R

Light-to-

Voltage

Analog

Temperature

and Humidity

Sensors

Integrated Sensors on ArduPilot

3DR Radio

Transmitter +

Antenna

3DR Radio USB

Receiver +

Computer

Design: Flow Chart

5V

2600mAh

Lithium

Battery

+5v

GND

MPU-6000 3-axis

gyro and

accelerometer

37

MediaTek

MT3329 GPS on

Daughterboard

MS5611

Barometric

Pressure Sensor

Design: Measurements

38

Acceleration MPU-6000 3 Axis Gyro and Accelerometer

Flight path MediaTek MT3329 10 Hz GPS

Solar Irradiance TSL250R Light to Voltage Sensor

Barometric Pressure MS5611 Barometric Pressure Sensor

Temperature LM61CIZ Analog Temperature Sensor

Humidity HIH-5030 Analog Humidity Sensor

Angular Rotation MPU-6000 3 Axis Gyro and Accelerometer

Design: Features • Automatic pre-launch board reset

capability.

• Light weight construction utilizing G10

fiberglass, aluminum, and lithium

polymer cells.

• Vibration dampening mounts for APM

2.0.

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• Multi-level dense electronic packing for easy installation/removal.

• Payload bay kraft casing providing a high strength to weight ratio.

• Steel rods distributing the load axially along payload bay.

Payload Integration • Location:

– Above the motor casing and below the drogue parachute

• Assembly: – Forward bulkhead attached to drogue parachute a steel u-bolt

and a chute quick link.

– The payload bay is secured using four removable nylon rivets. The rivets breach the fiberglass rocket shell and anchor to the internal payload bay. The simplicity allows for ease of integration/removal.

• Static Ports: – Two 180 ° drilled holes through rocket body tube and payload

bay allowing for ambient pressure readings.

• Sunlight: – Drilled hole for the allowance of sunlight on the TSL250R

40

Interfaces with Ground Station

• 3DR-

– The APM 2.0 directly transmits at a 57600 baud rate to the

ground control station.

– One way communication.

– Maximum transmit power of 100 mW with 1 mile range.

• Ground Control-

– QGoundControl: The ground station software receiving the live

data stream for all the internal and external sensors.

– 57600 8N1 Serial protocol .

– Live data transmitted in the graphical interface is stored as log

files for post processing.

41

42

Compliance Matrix (1/2)

43

Item Slide Numbers

Launch vehicle dimensions 11,12

Key design features 13,14

Motor Description 15

Flight stability + static margin 15

Thrust-to-weight and rail exit velocity 15

Mass statement 18

Parachute size, Descent rates 19

Kinetic energy at key phases of mission and landing

20-24

Compliance Matrix (2/3)

Item Slide Numbers

Predicted altitude in 5,10,15,20 MPH 26

Predicted drift in 5,10,15,20 MPH 26

Test plans and procedures 27

Full scale flight test 27

Recovery system tests 27,28

Requirements Verification 27,28

Payload design and dimensions 37

Key design features of payload 38

Payload integration 39

44

Compliance Matrix (3/3)

Item Slide Numbers

Interfaces with ground systems 41

45

Moving Forward

• Second Full Scale Test Launch • Launch Operations Refinement • Performance Optimization

• Payload

• Complete assembly and integration • Complete firmware development • Complete ground station software development

Thank You!!!

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