Madison West SLI '06 New TeamMadison West SLI '06 New Team

VehicleVehicle

Mission Statement

● Successfully launch rocket to 5,280 feet.● Capture multiple simultaneous images in

the standard and infrared spectrums.● Directly compare synchronized images

via photo editing software to determine foliage health and density.

● Compare the amount of detail vs. area covered for different altitudes

Mission Scheme

Design Evaluation The Yin-Yang Unstoppable Piercing Orbit Prime

Our vehicle is 132 inches in length, 7.6 inches in width (diameter) and weights approximately 20 kilograms when fully loaded.

● Nosecone: LOC Precision, LOC PNC-7.51 Plastic nose cone.

● Body: The body tube will be made out of phenolic tubing reinforced with fibreglass sunk into a epoxy matrix.

● Fins: The fins are made of G10 fiberglass to prevent any damage during flight and/or landing. Through The Wall (TTW) construction techniques will be employed.

● Motor: Contrail L1428 (hybrid), retained using a active retention system.

Components of Design

Flight Profile Simulations

MotorWind

[mph]

Ballast

[lbs]

Max. Speed

[mph]

Max.

Acceleration

[g]

Altitude

(no ballast)

[ft]

CP/CG

[calibres]

Contrail L1428 0

2.4

446 13.2 5533 3.59

Contrail L1428 5 2.2 448 13.3 5523 3.56

Contrail L1428 10 2.1 449 13.3 5496 3.55

Contrail L1428 15 1.6 458 13.5 5455 3.47

Contrail L1428 20 1.2 457 13.6 5402 3.54

Altitude vs. Time

Propulsion Subsystem

● We plan to use the Contrail L1428 Hybrid motor for our propulsion system. A hybrid motor is composed of three chief components: an oxidizer tank; a combustion chamber and a nozzle.● The purpose of an oxidizer tank is to provide N2O as an oxidizer in the combustion for the propulsion of the rocket. Various sizes of the oxidizer tank produce different impulse classes. All L-Level Contrail motors use 3200cc oxidizer tanks.

L1428 Motor Thrust Curve

Recovery SubsystemPayload Recovery: The Payload Recovery System will allow the

payload to descend horizontally. The parachute (60in, 15fps descent rate, deployed at apogee) will be placed in and ejected from the compartment behind the nosecone. It has two anchor points on the side of the rocket, 180 degrees away from the direction the cameras are facing. To do this, a line will be running along the side of the payload section from the anchor points to the nosecone. The parachute will eject at apogee and allow the rocket to descend with the cameras facing towards the ground.

● Vehicle Recovery: The Vehicle Recovery System will utilize dual deployment to prevent the vehicle from needlessly drifting off into far distances. The drogue parachute will be 25 in. in diameter to allow the vehicle to descend at 73 feet per second (fps), and will eject at apogee. The main parachute will be 90 in. in diameter to allow the vehicle to descend at 15 fps and will eject once the vehicle is 700 feet above ground (all values are approximate). Both booster parachutes will be fired by a couple of MAWD altimeters (primary and backup).

Dual Deployment

500ft: main parachute deployedApogee: drogue deployed

Ejection Charge Calculations

The size of ejection charges will be based on the formula:

Wp = dP * V / R * T

where:

dP ejection charge pressure in psi.R combustion constant, 22.16 (ft- lbf/lbm for FFFF black powder)T combustion gas temperature (3307

degrees farenheit).V free volume in cubic inchesWp charge weight (pounds)

Verification matrixKey• T1-Scale Model Launch Test.• T2- Drop Test from 20 ft.• T3- Acceleration Test (using centrifuge).• T4- Vacuum Test (to simulate pressure/altitude changes).• T5- Ground Test (to test proper function, sending and reception of data).• T6- Ignition Test.• T7- Tension Test.• T8- Drag Test.

• T9- Test Flight

System T1 T2 T3 T4 T5 T6 T7 T8 T9

Main Parachute ♦ ♦ ♦

Drogue Parachute ♦ ♦ ♦

Payload Parachute ♦ ♦ ♦

RDAS ♦ ♦ ♦ ♦

Telemetry System ♦ ♦ ♦

GPS System ♦ ♦ ♦

Altimeter ♦ ♦ ♦

Couplers ♦ ♦ ♦

Shock Cords ♦ ♦ ♦

Fins ♦ ♦ ♦

Engine/ Engine Retention

♦ ♦ ♦ ♦ ♦

Safety and Experimental Risk

Approach to Workmanship

● Proper construction procedure will be strictly adhered to so as to ensure the structural integrity of the rocket.● Construction sessions will be held in the school Engineering Lab. Times of construction sessions will depend on the availability of team members.● For maximum efficiency organization and division of labor is overseen by the vehicle key manager.● Materials and tools utilized in the process of construction include: phenolic tubes, glassed wood, epoxy, fiberglass, sandpaper, razor, paint, wood.

Payload Integration• Payload is enclosed in its own section, for easy coupling with the

booster part of the vehicle and to prevent the hot ejection gasses from damaging the payload.

• Payload has its own deployment electronics, independent on the deployment electronics for the booster.

• Payload has its own independent power sources (rechargable NiMH battery packs and non-rechargable 9V batteries).

• Payload its own tracking devices.• All payload electronics has external arming switches on the external

side of the payload body tube.

PayloadPayload

Experiment

● Use IR aerial photography to determine the concentration of various plant species and their health.

● Compare the IR aerial photos with the standard color aerial results to determine the amount of additional information gained from the use of IR photography.

● Determine the optimal altitude for this experiment (amount of details vs. area covered)

IR vs. Standard Pictures

Comparison of a color photograph (the left frame) and an IR photograph (the right frame) of a same scenery. Note that the trees on the far left shore and the far right shore look very similar (green) on the color photograph, but have quite different shades of gray on the IR photograph.

Color Picture Infrared (IR) Picture

Experiment SchemeColor picture

Infrared picture

Sick foliage

Healthy foliage

Simulated difference between a normal color photograph and an IR photograph (both are aerial pictures of a group of trees pictured on the right).

Payload Section Scheme

Payload Deployment

A scheme of payload deployment A photo of a deployed payload(from a test flight)

Payload Camera System

● Cameras will be set parallel to each other with lenses facing sideways. Parallax error is negligible.

● Nikon D70s are set on identical settings, apart from one camera's IR blocker being removed to allow the IR lengths to be recorded.

● Cameras will be set to begin taking photos at launch via a synchronized circuit (two synchronized pictures each 5 seconds).

● Photos will be stored on camera memory cards for later download, comparison and analysis.

Cameras and Accessories

Hoya Infrared Filter R-72

Nikon D70 SLR Digital Camera

● Nikon D70 DSLR cameras to be used in design.

● Identical lenses will be used to assure images will be comparable.

● Hoya R-72 Infrared Filter● 2GB SD memory cards● Electronic synchronized

IR LED trigger triggers both cameras

Camera Trigger Circuit(based on LM555 chip)

1: Ground, 2: Output, 3: Trigger, 4: Reset, 5: +VCC, 6: Discharge, 7: Threshold

Camera Control Continued

● Synchronized Dual ML-L3 Remotes● Periodic Shutter Release● Adjustable Trigger Interval● Adjustable Trigger Duration● Infrared Camera Control● Built Around LM555 Circuit● Watchdog Circuit Considered to Improve

Reliability

Payload ElectronicsROCKET DATA ACQUISITION SYSTEM

Telemetry Module

GPS

Transmitter

Receiver

Payload Electronics System

● GPS equipment will include an active antenna, module, and 900MHz transmitter. Transmitter and GPS antenna will >24in apart to prevent RF interference and GPS antenna jamming.

● RDAS will record altitude via accelerometer as well as other flight data (including GPS coordinates).

● Nosecone will contain an AM Radio beacon (in case GPS fails to transmit data) as well as a 140dB screamer.

Camera Testing

● Upon receiving both cameras pictures will be taken of similar objects w/o IR filter applied to assure both cameras perform as expected

● After IR filter is applied, pictures will be taken of varying health and species of plant (from varying distances) to determine what sort of data will be gathered and become familiar with the sensor response to IR light.

● Electronic trigger circuit will be tested rigorously to ensure its flawless functionality during the actual flight.