the candel project
DESCRIPTION
The CANDEL Project. CAN Sat DEL ivery Project Laura Lewis Jens Ramrath Cecil Strickland. Background. Idea originated at the 1998 University Space Systems Symposium Expected Launch Date - Fall 1999 Participating Universities Include: StanfordUniv. of Hawaii - PowerPoint PPT PresentationTRANSCRIPT
The CANDEL Project
CANSat DELivery Project
Laura Lewis
Jens Ramrath
Cecil Strickland
Background
• Idea originated at the 1998 University Space Systems Symposium
• Expected Launch Date - Fall 1999
• Participating Universities Include:Stanford Univ. of HawaiiUniv. of Tokyo Tokyo Inst. Of Tech.
Objectives
• Design a carrier to house 12 CanSats
• Eject 12 CanSats from carrier
• Use onboard camera to view activity during deployment
• Transmit pictures to specified location on Earth
• Reenter the Earth’s atmosphere
• Burn up on reentry
Initial Designs
•Brainstorm concept at conference
Our first design•
Final Deployment Design
• Use rotational velocity, , as primary means of deployment
• Assist deployment by light springs 30°
CanSat 2-D Design
382mm
200m
m142mm
70mm
Carrier Design
• Cylindrical case with a 382mm diameter
• Cylindrical burrows slightly larger than a “coke” can opening radially outward
• Cylindrical area in middle for housing of camera, power, and tracking device
• Thin wire covering CanSat openings
Can Attachment
• Attached to:– Carrier– Adjacent Cans
• Tether Joint
Subsystems Placement
Pressurized canister in the center of the carrier Provides protection from the space environment Reduces costs of subsystems
Pressurized canister in the center of the carrier Provides protection from the space environment Reduces costs of subsystems
Satellite Subsystems
• Camera Suggestions
• Tracking Device Suggestions– GPS– NORAD Tracking
• Picture Transmittal
• Requirements
CameraCMOS Active Pixel Sensor
• A single +3.3 V supply
• 11 pixel size - 512 x 512 pixel array
• Digital I/O
• Low noise
• Timing and control implemented in chip
• Low power (10mW at 1M pixels/sec)
• Radiation resistant compared to CCD’s
CMOS Active Pixel Sensor
http://csmt.jpl.nasa.gov/APS/features
Dycam Modular Digital Camera
• Camera consumes 5V-9V at peak current• Image organization 496 x 288 pixels• Transmits picture to host computer upon request• Camera has its own processor and memory (1 or
4 Megabyte)• In sleep mode camera draws 3.5mA, awake mode
125mA, image capture 650 mA for 15ms • Operated with Dycam’s Picture Viewer Software
Dycam Digital Modular Camera
Camera Size:
63 x 24 x 197 mm
Weight = 495 grams
Tracking Devices
• GPS Options– Simple receiver
• Contained in pressurized canister
• Determines when pictures will be transmitted to receiver on Earth
– Space-hardened• Expensive
• NORAD tracking
Picture from:www.sni.net
Transmittal Process
– GPS • Transmit signal from satellite to receivers on Earth
• Transmitter on Earth sends command to send pictures at appropriate time
– NORAD tracking• Orbital Elements from NORAD will determine
carrier location
• Transmitter from Earth sends signal to receiver
Transmittal
• Amateur band radio transmitter located on satellite
• Device will be used to determine best transmit time to Earth
• Various receivers will be placed all over the world to receive pictures
Requirements
• Camera Power – CMOS requires 10mW– Dycam requires 5-9 V at 500 mA peak current
• Ground Clock for picture transmittal
• GPS Power
• Power requirements will determine number of batteries needed
CanSat Deployment
• CanSats move to final circular position usingangular angular momentum and momentum and are restrained are restrained by tethersby tethers
CanSat Deployment
• Carrier is ejected from primary payload
• Wire is heated and allows CanSats to eject
• CanSats will receive
initial acceleration
from springs
Manufacturing of Dispenser
Three proposed materials:
• Carbon-Epoxy composites
• Aluminum
• Foam
Advantages of Foam
• Very light
• Easy to build satellite ourselves
• Can withstand vacuum
• Possible Temperature and radiation problems
• Several different kinds of foam available
Foam
• Expanded polystyrene– regular styrofoam– is permanently deformed by impacts
• Extruded polystyrene– hard foam
• Expanded polypropylene– rubber-like foam– can withstand impacts
Tether
There are several possible materials
• vectran– UV radiation resistant– zero creep
• parachute chord– cheap
Testing the dispenser
• Test model in 1-g environment
• Test in zero-g onboard NASA KC-135A aircraft (Vomit Comet)
Questions ?