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PDR Presentation

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• Eric Po Team Leader o Payload Manager o Documentation Manager

• Michael Bo Building Team Manager o Safety Manager

• Sean Ko Outreach o Materials Manager

• Jacob Eo Launch Manager o Budget Manager

• Mike Po Technology Manager o Equipment and Facility Manager

• Michael Go Recovery Manager o Communications Manager

• Brian Go Technical Manager o MSDS Manager

The Lake Zurich Rocketry Team and Responsibilities

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Length Diameter FinSpan Mass (with motor)

100.00 in 6.16 in 15.16 in 388.0091 Oz

Motor CG CP Stability Margin

K1050W 58.5723 in 71.0949 in 2.05

Component Justification Materials

Nose Cone Part of payload - needs to be durable

Fiberglass ogive with short shoulder for more room in payload tube.

Payload Need to be lightweight and relatively durable

coupler and containmentt tube are made from kraft phonelic

Payload Tube Needs to be lightweight and durable - to resist zippers. 6" Carbon Fiber - fiberglass too heavy.

Avionics Bay Can't block the signal from the GPS 14" kraft phonelic coupler

Avionics Bay CollarHolds the arming switches - can be easily armed from outside of LV.

2" collar is adequate for arming switches and for vent hole for altimeter.

Drogue ChuteDesign to eject with payload and allow LV to descend with wind.

18" Nylon chute that is attached with quick links to eyebolts in bulkplate on Avionics Bay.

Vehicle dimensions, materials, and justifications

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Component Justification Materials

Main Chute Designed to slow the LV down to safe landing velocity.

78" Nylon chute that deploys at 1,000' to reduce impact of winds.

Booster Tube Needs to be lightweight and durable to resist zippers.

6" Carbon Fiber - fiberglass was too heavy for the motor requirement.

Motor Mount Standard kraft phonelic motor mount system for 54 mm motor.

Using a K1050W motor from Aerotech which is a long motor requiring extra length in the booster tube.

Bulkplates and Centering Rings

Strong, lightweight, and easy to glue All bulkplates are made of 1/4" birch plywood

FinsEasily attached to motor tube, and sized to provide stable flight.

Fiberglass fins provide durable system, and easily shaped for accuracy in predicting flight stability.

• Carbon Fiber airframe was selected due to weight concerns of the total rocket, and the required durability to reduce damage and ‘zippers’.• Special epoxy will be used wherever a bond to the carbon fiber airframe is required.

Vehicle dimensions, materials, and justifications – cont.

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Static Stability Margin

Component Weights Oz. Stability Data  

Launch Vehicle 134.14 Stability Margin 2.05

Payload 46.00 Center of Pressure 71.09

Avionics Bay 81.02 Center of Gravity 58.57

Motor System 83.50The CG and CP are 12.1 " from each other, with

the CG being 58.57" from the nose tip.Recovery Systems 43.45

Total 388.11

Static Stability Margin

The team has used RockSim to arrive at a safe Stability Margin, and will also use physicalMeasurements to verify these results.

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Vehicle Safety Verification and Testing

Systems and Subsystems to be tested and verified:• Airframe Structural Strength – Flight testing and analysis• Fins – Flight testing and analysis• Rocket Stability – RockSim and physical measurements• Motor Selection – RockSim, and manufacturer specs.• Ejection System – low pressure ground testing and flight testing• Recovery System – (chutes and shock cords) stress testing and flight testing• Payload – analysis, weather balloon testing, and flight testing

Test Dates:• Ejection and Recovery Systems: 1/17/2012, 2/25/2012, 3/3/2012, 3/17/2012• Test Flights – Sub-scale: 1/17/2012• Test Flights – Full-scale: 3/17/2012, 4/07/2012• Payload testing: in December and January – as weather permits

Team Safety Managers will be briefing the team every other week on safety issues and training. They will also be responsible for executing the team safety plan, and maintaining a safe environment.

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Motor Selection and Justification

Motor Selected: Aerotech K1050W• Total Impulse = 2522.038 Ns• Size= 54mm diameter x 62.7 cm length• Total Weight = 2203 g• Prop Weight = 1265 g• Maximum Thrust = 2172 N• Average Thrust = 1132.9 N• Burn Time = 2.1 sec

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Thrust to Weight Ratio and Rail Exit Velocity

Thrust to Weight Ratio• Rocket weight = 10.9999 kg• Thrust = 2522.038 Ns• Ratio = 23.378 to 1

Rail Exit Velocity• Launch Rail Length = 120”• Exit Velocity = 83.8321 ft/s

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Launch Vehicle Verification and Test Plan

Launch Vehicle Requirement Verification and Test Plan5,280 feet AGL RockSim analysis and LV test 1

Maximum total impulse of 2,560 Ns (K class) Aerotech testing results for K1050W motor

Remain subsonic RockSim and LV test 1

All sections to have GPS tracking device Test

Must be have a stabilty margin of between 2.0 and 2.50 (RockSim) RockSim analysis and inspection

Must have at least 1 sub-scale test flight Scheduled for 1-10-2012

Must have at least 1 test flight of full-scale LV Scheduled for 3-17-2012

Ready to launch within 2 hours of waiver Testing

Ready mode for one hour Testing

DERS - Drogue and Main chutes Inspection and Testing

PDR Requirements and Launch Vehicle Verification and Testing to Meet these Criteria

Team Safety Managers will be briefing the team every other week on safety issues and training. They will also be responsible for executing the team safety plan, and maintaining a safe environment

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Launch Vehicle Verification and Test Plan – cont.

Launch Vehicle Requirement Verification and Test Plan

Ejection Charges adequate for construction Low Pressure Ground testing, Sub-scale test flight

Separate Arming Switches - no higher than 6' above base Inspection and testing

Redundant Altimeter Systems Testing

Electronics protected from frequency interference Analysis and testing

Removable Shear pins Testing

No more than 75 ft/lbs of Kinetic Energy upon landing for each section RockSim analysis and LV Test

All sections within 2,500 feet of launch pad RockSim analysis

Ready for re-launch in same day - no repairs or modifications Testing

PDR Requirements and Launch Vehicle Verification and Testing to Meet these Criteria

Team Safety Managers will be briefing the team every other week on safety issues and training. They will also be responsible for executing the team safety plan, and maintaining a safe environment

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Major Components and Subsystems

• Launch System – the system to ignite the motor, the launch buttons, and the launch rail must all operate according to safe launch procedures.

• Launch checklist – all team members must complete their assigned tasks as outlined in the Launch Checklist.

• Motor System – the motor must operate as designed, and the structural system holding ht motor in the rocket must be secure and durable.

• Ejection System – the altimeters and ejection charges must fire as planned in order to ensure a safe deployment of the recovery system. This is a critical subsystem in our project, and impacts not only the mission outcome, but also the safety of the team and bystanders.

• Recovery System – the parachutes and shock cords must deploy correctly, and work to slow the LV to a safe velocity during descent.

• Recovery Checklist – each team member must perform their assigned checklist duties to ensure safe and reliable recovery of the rocket, components, and data.

Launch Vehicle Systems

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Major Components and Subsystems – cont.

Recovery System

Electronics Sled housed in the Avionics Bay

Forward and Aft Bulkplates

Avionics Bay Assembly

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Major Components and Subsystems – cont.

Recovery System

Ejection Charges

• Payload – Drogue Chuteo Free volume = 622.04 cio Charge size = 3 grams

• Booster – Main Chuteo Free volume = 235.62 cio Charge size = 3 grams

Parachutes

• Drogue Chuteo Weight = .6 oz.o Diameter = 18”o Descent Velocity = 115.34 ft/sec

• Main Chuteo Weight = 11 oz.o Diameter = 78”o Descent Velocity = 17.83 ft/sec

Recovery Note – The Launch Vehicle will descend without the payload and nose cone. This required a separate RockSim simulation to calculate for this different weight.

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Payload Design

Payload System

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R/C Signal ComponentsComponent Function

HiTec Optic 2.4

Transmits the commands for

movinig the fins and power to the

fan

HiTec-Minima 6T

Receives the fan and fin movement information from the tramsmitter

HiTec-HS-45HB

Moves the directional fins per

the signal received

Payload Design – cont.

Telemetry ComponentsComponent Function

HTSS-Blue

transmits the telemetry data to the HTS-Navi-

USB

HTS-GPS

Calculates GPS and altitude

information every second

HTS-Navi-USB

Enters the telemetry data into grounnd based laptop

Additional Payload ComponentsComponent Function

WiVid L-5801-B Transmits positioning video to Payload Pilot

Garmin Astro 220Assists in recovery of Payload - back up for

GPS data

E-Flite 300 EFLM1150

Adjustable speed fan for forward movement

E-Flite 300 EFLM1150

powers all of the R/C controls on the Payload

Horizon R/C landing gear

Moves the camera to the desired view point

for pilot control

LOC Precision / Custom-made

Custom vents to propel the Payload forward

Custom MadeAdjusts the air flow to turn the Payload on

descent

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Payload Verification and Testing

Payload Verification

System and Subsystems Performance Characteristics Verification

Payload• Will be controlled to within 50 feet of a designated landing site• Will send data back to the ground station

• If the payload lands within 50 feet of a designated location• If the payload sends wireless information to the ground station during flight

Brushless Motor with a Propeller and Fins

• Will propel the payload forward.• Will alter the outgoing airflow from the payload to generate thrust in a specific direction

• If we are able to alter the payloads trajectory while in flight

The HiTEC GPS Sensor and Sensor Station

• Will send information to the ground station such as speed, GPS location, flight path, and altitude

• If we receive information from the payload during the payload’s flight

The WiVid Lightweight Video Camera

• Will send video telemetry to the ground station to give us a perception of what direction the payload is traveling in

• If we receive video telemetry from the payload during the payload’s flight

Requirement Design

The payload's trajectory will be controlled The payload contains a remote controlled fan and several fins to allow changes in the payload's descent.

The payload will send wireless telemetry to the ground station while in flight

The payload will utilize a GPS sensor to transmit position from the payload to a monitor on the ground

The payload will send video telemetry to the ground station while in flight

The payload will utilize a video camera to transmit video telemetry to a monitor in the ground station

The payload will land at a designated point on the ground

Utilizing systems, the payload will land within 50 feet of a designated location

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Payload Verification and Testing – cont.

Payload Testing

Test ProceduresDrop Test The payload is dropped from a helium balloon at 250 feet to test for

accuracy of steering and structural integrity

Battery Connection Test The batteries are connected to the various subsystems to test for functionality

GPS Location Test (GPS Unit) GPS is tested in various locations for verification of accuracy

Altitude Test (GPS Unit) GPS unit is taken to various heights to test for accuracy

Speed Test (GPS Unit) GPS unit is moved at various speeds for verification of accuracy

Flight Path Test (GPS Unit) GPS unit’s flight path is tested during the drop test to verify accuracy

GPS Location Test (Garmin Astro)

GPS is tested in various locations for verification of accuracy

Altitude Test (Altimeter) Altimeter is taken to various heights to test for accuracy

R/C Transmitter and Receiver Operating Distance Test

R/C Transmitter and Receiver are taken to their furthest operating distance to verify that the will operate at over 1 mile

Thrust Test The payload is placed on a scale and has its thrust steadily increased to verify that it can propel the payload in flight

Wiring Test The subsystems are connected to corresponding wire connections to test if each responds accordingly

Stress Test The payload is run for an hour to verify that it can withstand the stresses of flight

Camera Test Camera images are compared to known ground features to ensure that the camera is functioning

Final Test The completed payload is tested for functionality

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Thank you!

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